SIKORSKY AIRCRAFT CORPORATION Patent applications |
Patent application number | Title | Published |
20160077523 | SYSTEM FOR CONTROLLING AND COMMUNICATING WITH AIRCRAFT - A ground-based aircraft control system including at least one data receiver/transmitter module configured to transmit aircraft control and data signals to an aircraft to control the flight of the aircraft and to receive data signals from the aircraft. At least one controller including a voice command recognition module configured to receive voice commands, to generate control signals based on the voice commands, and to transmit the control signals and command audio signals to the aircraft via the at least one data receiver/transmitter module. The at least one controller is configured to receive non-command voice audio signals and to transmit the non-command voice audio signals to the aircraft via the at least one data receiver/transmitter module. | 03-17-2016 |
20150308288 | IMPELLER RETENTION APPARATUS - An impeller retention apparatus is provided and includes a bearing element, a rotatable shaft, which is rotatably supported within an outer body by the bearing element, an impeller disposed about and coupled to the shaft to rotate with the shaft and a preload spacer disposed along the shaft between the impeller and the bearing element, the preload spacer comprising an elastic element which biases the impeller away from the bearing element in an axial direction along the shaft. | 10-29-2015 |
20150307203 | VERTICAL AXIS SOFT LANDING CONTROL - Embodiments are directed to obtaining data pertaining to at least: a rate of descent of an aircraft and a measured distance of the aircraft from at least one of an obstacle and the ground, processing, by a processing device, the data to obtain a flight envelope, generating a tactile cue corresponding to the flight envelope, and applying the tactile cue to an inceptor. | 10-29-2015 |
20150298818 | ROTOR INDEX SENSOR SYSTEM - An aircraft is provided and includes an airframe having main, pylon and tail sections, a rotor disposed at one of the pylon and tail sections and rotatable about a rotational axis to drive the airframe and a primary gearbox disposed within the main section of the airframe and a secondary gearbox disposed within one of the pylon and tail sections. The primary gearbox includes an outer housing rotationally fixed relative to the airframe and a driveshaft extending through the outer housing and coupled to the secondary gearbox to thereby drive rotation of the rotor relative to the airframe via the secondary gearbox. The aircraft further including a sensing system affixed to the outer housing and the driveshaft and configured to sense rotational characteristics of the driveshaft. | 10-22-2015 |
20150298803 | ADJUSTABLE SCISSOR CONTROL LINK - A control link disposed to transfer rotor shaft rotation from an elongate element rotatable with a shaft to a rotatable element is provided and includes a structure terminating at a first end thereof as a mating element, which is securable to the elongate element such that the elongate element is rotatable about an axis defined through the mating element and such that a moment reaction in opposition to structure rotation about the elongate element is generated and a rod coupled to the rotatable element being and configured to be coupled to a second end of the structure at variable distances relative to the rotatable element. | 10-22-2015 |
20150298801 | STIFF INPLANE ELASTROMERIC ROTOR HEAD - An aircraft rotor head is provided and includes a rotor hub including a central portion and radial arms extending outwardly from the central portion, blade retention yokes, each blade retention poke being pivotably coupled to a corresponding one of the radial arms at one end and to a corresponding blade at another end and a lag restraint star rotatable about and translatable along the central portion. The lag restraint star is coupled to each of the blade retention yokes to facilitate uniform blade lead/lag and uniform blade coning. | 10-22-2015 |
20150292901 | SCREEN SYMBOLOGY - A method and system for enhancing situational awareness in a rotary wing aircraft, includes receiving signals indicative of environmental information for the aircraft during a hover; determining signals indicative of a heading, course, and speed for the aircraft in response to the receiving of the environmental information; and displaying a composite symbology for heading, course, and speed on tactical display. | 10-15-2015 |
20150291288 | ENGINE INLET CONFIGURATION - An engine inlet assembly includes an inlet duct having a first inlet duct leg and a second inlet duct leg, the first inlet duct leg and the second inlet duct leg extending toward a common inlet duct outlet located at an engine inlet. The first inlet duct leg and the second inlet duct leg are fixedly secured to an airframe of an aircraft at an air inlet. The duct outlet has a floating interface with the engine inlet. | 10-15-2015 |
20150291277 | DECELERATION TO HOVER MODULATION - A system and method for controlling a deceleration profile of an aircraft, includes a processor and memory that receives a signal indicative of a deceleration command; receives signals indicative of a sensed velocity and a commanded heading rate; determines a commanded velocity in response to the receiving of the deceleration command and the commanded heading rate; determines an estimated deceleration command as a function of the commanded velocity; and determines an actual deceleration command in response to the determining of the estimated deceleration command. | 10-15-2015 |
20150286220 | ROTORCRAFT CONTROL LAWS FOR SEA-BASED OPERATIONS - A method and system of controlling a rotorcraft for sea-based operations includes receiving sensed information indicative of an operation of the rotorcraft; receiving operator commands, ship models and system constraints; and determining a solution to an optimization function that avoids violating the system constraints, the solution being representative of control command signals for augmenting a flight response of the rotorcraft to a ship. | 10-08-2015 |
20150286214 | TERRAIN ADAPTIVE FLIGHT CONTROL - A helicopter is provided and includes an air frame formed to accommodate a pilot, flight control elements disposed on the airframe to generate lift and thrust in accordance with control commands issued by the pilot and a current control mode, a sensor disposed on the airframe to sense helicopter proximity to terrain and obstacles and a flight computer configured to change the current control mode based on sensed helicopter proximity to the terrain and the obstacles. | 10-08-2015 |
20150284075 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH VARIABLE WING GEOMETRY - A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage, inboard wings extending from opposite sides of the fuselage to define a support plane and engine nacelles disposed along the wings. Each of the wings includes ground alighting elements and a variable geometry such that a portion of the ground alighting elements are alignable with the support plane during in-flight conditions and displaceable from the support plane. | 10-08-2015 |
20150276538 | ESTIMATION OF GROSS WEIGHT AND CENTER-OF-GRAVITY - Embodiments are directed to obtaining data from at least one sensor, the data pertaining to rotor loads and motion, processing, by a device comprising a processor, the data to obtain an estimate of at least one of gross weight (GW) and center of gravity (CG) for a rotorcraft, and outputting the estimate. | 10-01-2015 |
20150274288 | COMPLIANT WING CONTROL FOR AIRCRAFT - An aircraft includes a fuselage, and a wing extending from each lateral side of the fuselage. A rotor is secured to each wing; the rotor having a rotor tip path plane defined by rotation of the rotor about a rotor axis of rotation. When the rotor tip path plane is changed relative to the rotor axis of rotation, the wing twists in a direction of the rotor tip path plane change to reduce an angle of attack of the wing relative to a rotor wake of the rotor. A method of operating an aircraft includes changing a rotor tip path plane orientation relative to an axis of rotation of the rotor; the rotor secured to a wing of the aircraft. The wing is twisted to reduce an angle of attack of the wing relative to a rotor wake of the rotor. | 10-01-2015 |
20150253209 | MULTIFUNCTIONAL LOAD AND DAMAGE SENSOR - Embodiments are directed to obtaining at least one sample of load or load path data from at least one piezoelectric sensor associated with a structure, comparing the at least one sample of data to at least one prior sample of data obtained from the at least one sensor, and providing a status of a health of the structure based on the comparison. | 09-10-2015 |
20150232177 | FLY BY WIRE SERVOS WITH INTERNAL LOOP CLOSURE - Embodiments are directed to obtaining a first analog signal corresponding to a position error between a commanded gang output of a plurality of electro-mechanical actuators configured to be run in parallel with one another and a measured gang output of the plurality of electro-mechanical actuators, obtaining a second analog signal corresponding to an output torque, and processing, by a circuit, the first analog signal and the second analog signal to generate and output a discrete that indicates a status of the torque in terms of direction and magnitude. | 08-20-2015 |
20150219523 | ROTOR STATE SENSOR SYSTEM - A rotor state sensor system is provided for use with a rotor including a hub, a hub arm and a blade coupled to the hub by the hub arm. The sensor system includes sensors disposed on the hub arm to define a first plane, which emit emissions and receive reflected emissions, and which generate a signal according to the received reflected emissions, reflector plates disposed on the blade which define a second plane at locations where the emissions from the sensors are incident on the reflector plates and from which the reflected emissions are reflected towards the sensors and a computing device which receives the signal from the sensors, determines relative orientations of the first and second planes according to the received signal and determines a condition of the rotor based on the determined relative orientations. | 08-06-2015 |
20150210382 | RELATIVE ACCELERATION BLADE POSITION MEASUREMENT - Embodiments are directed to obtaining data from a plurality of sensors located on a rotorcraft, wherein a first plurality of the sensors is associated with a hub of the rotorcraft and a second plurality of the sensors is associated with blades of the rotorcraft, processing the data to isolate blade dynamics using the data from the sensors associated with the blade from rotorcraft maneuvering dynamics using the data from the sensors associated with the hub, obtaining at least one parameter associated with the blade dynamics based on the processing, and analyzing the at least one parameter to control at least one of the rotorcraft and the blades. | 07-30-2015 |
20150210381 | PITCH FEEDBACK CONTROL SPLITTING FOR HELICOPTERS WITH REDUNDANT ACTUATORS - Embodiments are directed to generating, by a processing device, a feedback command for an aircraft based on a reference input and an output response of the aircraft, and analyzing, by the processing device, the feedback command to allocate control to a plurality of control surfaces over a plurality of separate frequency bands. | 07-30-2015 |
20150203217 | COMPOSITE BONDED REPAIR METHOD - A composite bonded repair method for an aircraft is provided. The method includes generating a doubling patch of a portion of the aircraft from topographic data, filling damage at the portion of the aircraft with filler material, applying adhesive to the portion of the aircraft and the filler material and adhering the doubling patch to the adhesive. | 07-23-2015 |
20150203197 | POWER AND DATA TRANSFER TO HUB SENSORS - Embodiments are directed to a method comprising: providing, by a coil embedded in a structure of a rotor hub composed of a paramagnetic material, power to at least one sensor, and receiving, by the coil, data from the at least one sensor. Embodiments are directed to a system comprising: a coil embedded in a structure of a rotor hub composed of a paramagnetic material, and a plurality of sensors communicatively coupled to the coil and configured to receive power from the coil. | 07-23-2015 |
20150203189 | ROTOR MOMENT FEEDBACK FOR STABILITY AUGMENTATION - Embodiments are directed to obtaining at least one measurement of blade bending associated with at least one blade of at least one rotor of an aircraft, processing, by a device comprising a processor, the at least one measurement to obtain moment data, obtaining data from an inertial measurement unit (IMU), and processing, by the device, the moment data and the data from the IMU to generate a command configured to stabilize the aircraft. | 07-23-2015 |
20150202705 | MACHINE FOR MACHINING GEAR TEETH AND GEAR TEETH MACHINING METHOD - A machine for machining a workpiece having a central longitudinal axis is provided. The machine includes a chuck or fixture on which the workpiece is disposable, a grinding spindle to remove material from the workpiece, the grinding spindle having a central longitudinal axis about which the grinding spindle rotates and being disposed with the central longitudinal axes intersecting one another so as to create a continuous gear tooth on the workpiece and an electrochemical grinding (ECG) element configured to execute ECG processing on the grinding spindle and the workpiece to soften the workpiece as the gear tooth is being created by the grinding spindle. | 07-23-2015 |
20150198436 | TIP CLEARANCE MEASUREMENT - An aircraft is provided and includes an airframe, first and second main rotors rotatably supported on the airframe to rotate about a rotational axis in opposite directions, first and second emitters disposed on an emitter blade of the second main rotor, each of the first and second emitters being configured to emit an emission toward a detector blade of the first main rotor, a detector disposed on the detector blade of the first main rotor, the detector being configured to detect the emissions of the first and second emitters and a flight computer which determines a clearance between the first and second main rotors in accordance with detections of the emissions by the detector. | 07-16-2015 |
20150197332 | CONSTANT VELOCITY DRIVE FOR TILT ROTOR ASSEMBLY - A constant velocity drive includes a drive ring and a driven ring positioned around the drive ring. Drive links extend from the drive ring to the driven ring to transfer torque applied at the drive ring to the driven ring. Elastomeric bearings are positioned at the driven ring to transfer torque from a drive link of the plurality of drive links to the driven ring. Each elastomeric bearing includes both spherical bearing elements and planar bearing elements to allow for tilt of an axis of rotation of the driven ring with respect to an axis of rotation of the drive ring while ensuring a constant rotational velocity of the driven ring with respect to the rotational velocity of the drive ring. | 07-16-2015 |
20150191250 | IN-FLIGHT MECHANICALLY ASSISTED TURBINE ENGINE STARTING SYSTEM - An engine starting system for a rotary wing aircraft includes a controller that receives a signal indicative of a start command for an engine, a transmission input module that is mechanically coupled to a transmission system and an accessory gearbox and a starter motor that is mechanically coupled to a compressor drive shaft of the engine. Also, a method for restarting an engine in flight includes receiving by a controller a signal indicative of a start command for the engine, determining by the controller that an overrunning clutch is coupled to the engine, transmitting by a transmission system motive power to the engine in response to the determining that the overrunning clutch is coupled to the engine and driving via a compressor drive shaft a compressor section of the engine according to a design speed. | 07-09-2015 |
20150186244 | DATA RECORDER FOR FULL EVENT CAPTURE - Embodiments are directed to capturing data associated with an occurrence of an event via a battery-powered recorder, comprising: storing analog data in a delay circuit while a recording circuit is powered off, detecting, by a trigger circuit, the occurrence of the event while the recording circuit is powered off, powering-on the recording circuit based on the detection of the event, converting samples of analog data associated with the event provided by the delay circuit to a digital format while the recording circuit powers on, and storing the converted digital samples after the recording circuit has powered on, wherein a time delay associated with the delay circuit is greater than a time it takes for the recording circuit to power-on. | 07-02-2015 |
20150160303 | BATTERY LIFE TRACKING FOR WIRELESS SENSOR SYSTEMS - Embodiments are directed to predicting an amount of energy associated with a battery, by: storing, by a node, a value for an amount of energy drawn from the battery for each type of operation performed by the node, storing, by the node, a value for an amount of energy drawn from the battery when the node is active based on the stored amount of energy drawn for each type of operation, and transmitting, by the node, an indication of the amount of energy drawn from the battery in order to compute a prediction of the remaining battery energy. | 06-11-2015 |
20150158573 | IN-WING DEVICE RETENTION - A method of forming an in-wing device-retention assembly includes inserting a first plate into a wing, the wing having a wide end and a narrow end. The method includes inserting a second plate into the wing, inserting a wedge plate into the wing and positioning the wedge plate between the first plate and the second plate, and applying a force to the wedge plate in a direction toward the narrow end to fix the first plate, the second plate and the wedge plate within the wing. | 06-11-2015 |
20150152733 | BOUNDARY LAYER INGESTING BLADE - A boundary layer ingesting (BLI) blade having a span is provided and includes a root section connectable to a hub, a tip section disposable at a distance from the hub and having a pitch and a body extending in a spanwise dimension from the root section to the tip section. The root section has a local pitch from the root section to about a 70% span location, which is less than the pitch at the tip section, to thereby reduce local angles of attack in a boundary layer region defined in and around the root section. | 06-04-2015 |
20150151837 | PAYLOAD TOUCHDOWN DETECTION - Embodiments are directed to obtaining data associated with at least one aircraft flight parameter when an aircraft is being operated in flight; processing the data to determine that the at least one aircraft flight parameter indicates a change in value in an amount greater than a threshold; and decoupling a load from the aircraft based on determining that the at least one aircraft flight parameter indicates the change in value in the amount greater than the threshold. | 06-04-2015 |
20150149024 | LATENCY TOLERANT FAULT ISOLATION - A method of latency tolerant fault isolation is provided. The method includes receiving, by a maintenance data computer, evidence associated with a test failure. The maintenance data computer accesses metadata to identify a system failure mode associated with the evidence and other potential evidence associated with the system failure mode. The maintenance data computer determines a maximum predicted latency to receive the potential evidence associated with the system failure mode based on the metadata. The method also includes waiting up to the maximum predicted latency to determine whether one or more instances of the potential evidence associated with the system failure mode are received as additional evidence. The maintenance data computer diagnoses the system failure mode as a fault based on the evidence and the additional evidence. | 05-28-2015 |
20150147132 | HIGH SHEAR CAPABILITY INTERFACE - A connection between a first component and a second component is provided including a first hole formed in a portion of the first component and a second hole formed in a portion of the second component. The second hole is aligned with the first hole. A pin includes a through hole having a pin hole diameter. The pin extends through a portion of the first hole and into a first portion of the second hole. The pin is configured to absorb a shear load applied to the connection. A bolt extends through the second hole and the pin such that a clearance fit is formed between the bolt and the pin. The bolt is configured to absorb an axial load applied to the connection. A nut connected to the free end of the bolt limits movement of the bolt relative to the first and second component. | 05-28-2015 |
20150144495 | METHODS AND MATERIALS FOR ELECTROPLATING ALUMINUM IN IONIC LIQUIDS - A method of depositing aluminum onto a substrate is disclosed. In this method, the substrate is disposed as cathode in an electrochemical cell with an anode and a liquid electrodeposition composition comprising an ionic liquid and a source of aluminum, and aluminum is electroplated onto the substrate. Residual water content in the electroplating bath is controlled by exposure to light in the presence of a photo-oxidation catalyst to decompose the water or species associated with water. | 05-28-2015 |
20150144201 | ENGINE INLET DUCT INSTALLATION - A method of securing two components to each other includes locating a mounting strip at a first mounting flange of a first component. The mounting strip is slidably affixed to the first component and includes a plurality of strip openings and a tightening ramp located at each strip opening of the plurality of strip openings. A second component is located such that a second mounting flange of the second component abuts the first mounting flange. A plurality of fasteners are located at the second mounting flange. A fastener of the plurality of fasteners extends through each strip opening of the plurality of strip openings. The mounting strip is slid in a direction to increase tension on the plurality of fasteners via an increasing height of the tightening ramp under a fastener head of the fastener, thereby securing the first mounting flange to the second mounting flange. | 05-28-2015 |
20150139799 | COUNTER-ROTATING ROTOR SYSTEM WITH STATIC MAST - A coaxial, dual rotor system includes a first rotor assembly positioned at a rotor axis. A first rotor quill shaft is operably connected to the first rotor assembly at the rotor axis to drive rotation of the first rotor assembly about the rotor axis. A nonrotating static mast extends along the rotor axis through the first rotor quill shaft. A second rotor assembly is positioned at the rotor axis. A second rotor quill shaft is operably connected to the second rotor assembly to drive rotation of the second rotor assembly about the rotor axis. The second rotor quill shaft is coaxial with the first rotor quill shaft and disposed inside of the static mast. A second rotor bearing is positioned between the second rotor assembly and the static mast to transfer loads from the second rotor assembly to the static mast. | 05-21-2015 |
20150136308 | FIELD REPAIR KITS FOR STRUCTURAL PANEL - A kit for repairing an opening formed in a composite panel having a laminate skin arranged on opposing sides of a first core material is provided including a plug and a patch. The plug is formed from a second core material and has a cured filler material arranged within at least a portion of the second core material. The patch is formed from a plurality of cured first plies arranged in a stacked orientation. The plug is configured to be received within the opening of the composite panel and the patch is configured to cover the opening of the composite panel. | 05-21-2015 |
20150133016 | IMPACT RESISTANT COMPOSITE PANEL AND METHOD OF FORMING A COMPOSITE PANEL - A composite panel includes a support layer including a first plurality of prepreg plies wrapped around at least one mandrel; a mid-plane impact layer including a second plurality of prepreg plies, the mid-plane impact layer adjacent to the support layer; a upper skin layer including a third plurality of prepreg plies, the upper skin layer adjacent to the mid-place impact layer; and a lower skin layer including a fourth plurality of prepreg plies, the lower skin layer adjacent to the support layer; whereby each of the first, second, third, and fourth plurality of prepreg plies are co-cured to form the composite panel. | 05-14-2015 |
20150132131 | ROTOR BALANCING APPARATUS - A balancing apparatus for a rotary element is provided and includes a central hub portion and radial elements extending outwardly from the central hub portion. The balancing apparatus includes a conduit extending along the radial elements via the central hub portion, a mass movable within the conduit between the radial elements via the central hub portion and a mass balancing system which directs a movement of the mass within the conduit into and out of the central hub portion and along the radial elements. | 05-14-2015 |
20150129361 | Anti-Clog And Non-Metallic Debris Detector For Lubrication System Inlet - A contaminant detection system for use in a fluid distribution system includes a first detector assembly including an inlet housing and detector screen through which fluid in the fluid distribution system passes and a first sensor to detect a first type of contaminant caught in the detector screen; and a second detector assembly including a second sensor which activates when the inlet housing or detector screen is clogged to detect whether the fluid contains a second type of contaminant when the first sensor does not detect the first type of contaminant. | 05-14-2015 |
20150125661 | CORROSION MITIGATION FOR GEARBOX - A magnesium component of a rotary wing aircraft is provided including a groove including a first sidewall and a second sidewall arranged on opposing sides of a recessed opening. The first sidewall includes a deposit positioned adjacent the recessed opening. The deposit is formed by cold spraying one or more layers or powdered material within an area of the first sidewall from which material was removed. | 05-07-2015 |
20150125299 | COUNTER-ROTATING ROTOR SYSTEM WITH STATIONARY STANDPIPE - A rotor system includes a first rotor located at a rotor axis that imparts a first axial load and a first moment, and a first shaft connected to the first rotor at the axis. A first bearing connects a gearbox to the first shaft, transferring the first axial load from the first shaft to the gearbox. A second rotor located at the axis imparts a second axial load and a second moment. A second shaft is connected to the second rotor at the axis, the second shaft coaxial with the first rotor. A second bearing connects the gearbox to the second shaft, transferring the second axial load from the second shaft to the gearbox. A nonrotating standpipe is located at the axis radially between the first shaft and the second shaft. An intershaft bearing located at the standpipe reacts the first and second moments using the first and second bearings. | 05-07-2015 |
20150122954 | VARIABLE GEOMETRY HELICOPTER ENGINE INLET - A variable area engine inlet of a helicopter is provided and includes first inlet portions disposed to face one another in opposite directions and at a distance from one another and second inlet portions extending between the first inlet portions and being disposed to face one another in opposite directions and at a distance from one another. The first and second inlet portions define a capture area and at least one or both of the first and second inlet portions include a movable portion disposed to occupy and move between first and second positions. The first position is associated with a non-constricted condition of the capture area and the second position is associated with a constricted condition of the capture area. | 05-07-2015 |
20150122941 | COUNTER-ROTATING ROTOR SYSTEM WITH FAIRING - A coaxial, dual rotor system for an aircraft includes a first rotor assembly located at a rotor axis and a second rotor assembly located at the rotor axis. An aerodynamic fairing is positioned between the first rotor assembly and the second rotor assembly along the rotor axis. A planetary gear arrangement is operably connected to the fairing and operably connected to an airframe of the aircraft to maintain a selected rotational orientation of the fairing about the rotor axis relative to the airframe. | 05-07-2015 |
20150122079 | DAMAGE MITIGATION FOR GEARBOX - A component of a rotary wing aircraft is provided including a surface configured to contact another component of the rotary wing aircraft such that the surface is susceptible to corrosion and/or pitting. The surface has an area from which a portion of material was removed. A structural deposit is formed by cold spraying one or more layers of powdered material within the area. The structural deposit is configured to carry a load applied to the component. | 05-07-2015 |
20150114772 | ROTOR BRAKE - A brake disc of a rotor brake is provided including a generally cylindrical body having a first planar surface, a second, opposite planar surface, and a central opening extending there through. A plurality of first connection members extend generally outwardly from the first planar surface. The first connection members are generally equidistantly spaced about a diameter of the first planar surface. A plurality of second connection members extend generally outwardly from the second planar surface. The second connection members are generally equidistantly spaced about a diameter of the second planar surface. | 04-30-2015 |
20150112549 | LOCATIONAL AND DIRECTIONAL SENSOR CONTROL FOR SEARCH - A method of controlling a directional facing of a sensor mounted to a vehicle includes storing, by a sensor control computer, previously-searched locations of a terrain at which the sensor is directed. The method includes determining a likelihood of detecting a target at one or more points on the terrain and controlling a directional facing of the sensor onto the terrain based on the previously-searched locations and the likelihood of detecting the target. | 04-23-2015 |
20150107957 | SELECTIVE ELECTRICAL CONTROL OF ELECTROMECHANICAL CLUTCH ASSEMBLY - A clutch assembly of a vehicle includes a shaft configured to rotate around a rotation axis inside the shaft, a connection arm connected to the shaft, to a pilot-controlled mechanism, and to a mechanical servo that controls a movement of the vehicle, and at least two electromechanical actuators. The electromechanical actuators are configured to be selectively engaged with the shaft via an electromechanical clutch, such that the electromechanical actuators are disconnected from controlling a movement of the shaft and the connection arm when the electromechanical clutch is disengaged, and the electromechanical actuators are configured to control movement of the shaft and the connection arm when the electromechanical clutch is engaged. | 04-23-2015 |
20150105970 | GLOBAL AIRFRAME HEALTH CHARACTERIZATION - According to one aspect, a controller, including a processor, sets an initial vibration frequency to be applied to an airframe. The controller commands one or more force generators to apply a vibratory load to the airframe at the initial vibration frequency. The controller determines a vibration response of the airframe at the initial vibration frequency using sensors. The controller sweeps through a range of vibration frequencies to be applied to the airframe. The one or more force generators are commanded to apply a plurality of vibratory loads to the airframe over the range of vibration frequencies. The controller determines a range of vibration responses of the airframe over the range of vibration frequencies using the sensors. A global stiffness of the airframe is determined based on the vibration response and the range of vibration responses. The controller reports results of the determined global stiffness of the airframe. | 04-16-2015 |
20150102158 | Coaxial Rotor Yaw Control - A method includes determining, by a computing device comprising a processor, a value for at least one parameter related to an operation of a coaxial rotary wing aircraft; processing, by the computing device, the at least one parameter to determine control power available from one or more flight controls comprising a differential cyclic; and establishing, by the computing device, a value for the differential cyclic to create a net yaw moment for the rotary wing aircraft based on the determination of the available control power. | 04-16-2015 |
20150100181 | Electrified Rotorcraft - An electrified propulsion system for a rotary wing aircraft includes a flight control computer that receives a signal indicative of a power demand on an engine; an engine control system that is in communication with the engine and is configured to control operation of the engine at a selected operating point; a generator that is in mechanical communication with the engine and is configured to receive mechanical power from the engine and convert the mechanical power to electrical power; an electric motor that is in electrical communication with the generator and is configured to receive the electric power; and a rotor that is in mechanical communication with the electric motor; wherein the electric motor is configured to control rotation and provide the mechanical power demand of the rotor at the selected operating point in response to the received signal. | 04-09-2015 |
20150097075 | YAW CONTROL OF CO-AXIAL ROTOR - A method for controlling rotor blades of a co-axial rotor assembly of an aircraft including a first rotor co-axial with a second rotor includes identifying a first zone of rotor rotation angles of the co-axial rotor assembly. The first zone defines a range of rotor rotation angles corresponding to an up-flow of air to the coaxial rotor assembly, and the remainder of the rotor rotation angles other than the first zone of rotation angles is defined as a second zone. The method includes receiving a yaw command to adjust a yaw moment of the aircraft and applying a different rotor blade angle change to rotor blades in the first zone than a rotor blade angle change applied to rotor blades in the second zone to adjust the yaw moment of the aircraft according to the yaw command. | 04-09-2015 |
20150097074 | DUAL-FREQUENCY ACTIVE VIBRATION CONTROL - A system for active vibration control includes an actuator configured to reduce the impact of a vibratory load imposed on an airframe of a rotorcraft to an amount that is less than a threshold; and a controller configured to determine the vibratory load based on the data, and set an eccentric rotational speed of an actuator at a first frequency and modulate the eccentric rotational speed by a second frequency based on the vibratory load. Also a method includes obtaining, by the controller, data; determining, by the controller, a vibratory load based on the data; and setting, by the controller, an eccentric rotational speed of an actuator at a first frequency and modulating the eccentric rotational speed by a second frequency based on the vibratory load. | 04-09-2015 |
20150097073 | Self Scavenging Gear Shield - A gearbox assembly includes a gearbox housing and a gear located in the housing and rotatable about a central axis. One or more gear shields are fixed in the housing and at least partially surround the gear. The one or more gear shields define a cavity between the gear and the one or more gear shields. The one or more gear shields are configured such that a pumping action is created by the gear rotation to direct gearbox lubricant out of the cavity. A method of scavenging lubricant from a gearbox includes pumping a flow of lubricant circumferentially around a cavity defined between a gear and a gear shield at least partially surrounding the gear via rotation of the gear about a central axis. The flow of lubricant is urged from the cavity into a lubricant outlet. The lubricant is urged through a lubricant channel in an axial direction. | 04-09-2015 |
20150097072 | ACTIVE VIBRATION CONTROL ACTUATOR - A vibration control actuator includes a housing having a length between ends and a rotatable shaft located in the housing and extending along a housing length and which rotates about a shaft axis substantially parallel to the length. An inertia wheel assembly is operably connected to the rotatable shaft and configured to rotate therewith about the shaft axis. The inertia wheel assembly is in frictional contact with an inner wall of the housing and translatable to travel within the housing between the ends along at least a portion of the shaft axis. | 04-09-2015 |
20150096382 | ULTRASONIC SCANNING FIXTURE ASSEMBLY - An apparatus for use in scanning a material includes a top member having a first body with a first plurality of holes; a bottom member having a second body with a second plurality of holes; and an interconnecting member connecting the top member and the second member to provide a gap between the top member and the bottom member. Each hole in the top member is aligned with a corresponding hole in the bottom member to form a hole-pair. | 04-09-2015 |
20150093541 | COMPOSITE STAPLE - A laminate design is provided and includes a substrate formed to define through-holes, an initially uncured pre-preg laminate disposed proximate to the substrate and an initially uncured pre-preg staple. The staple includes a main member and legs extending from the main member and being disposable with the legs extending through the through-holes to pierce the laminate. The staple is co-curable with the laminate. | 04-02-2015 |
20150093057 | PITCH BEARING - A pitch bearing for connecting first and second articles is provided. The first article includes a first curved outer surface and the second article includes a second curved outer surface opposite the first curved outer surface. The pitch bearing includes an axisymmetric structure interposed between the first and second curved outer surfaces. The axisymmetric structure includes compliant layers and stabilizing layers interleaved between the compliant layers. The compliant layers and the stabilizing layers proximate to the first article haves a curvature matching that of the first curved outer surface. The compliant layers and the stabilizing layers proximate to the second article have a curvature matching that of the second curved outer surface. A shear stiffness of each of the stabilizing layers is greater than a shear stiffness of each of the compliant layers. | 04-02-2015 |
20150088435 | GEAR FAULT DETECTION - Embodiments are directed to obtaining an impact energy signal associated with each of a plurality of teeth of a gear over a revolution of a shaft associated with the gear, generating, by a computing device comprising a processor, a profile of the impact energy signal, and declaring a fault associated with an identified tooth included in the plurality of teeth based on an analysis of the profile. | 03-26-2015 |
20150086083 | STRUCTURAL HOT SPOT AND CRITICAL LOCATION MONITORING SYSTEM AND METHOD - A method for detecting a crack in a structural component includes receiving, with a processor, signals indicative of at least one image for a critical location in the structural component; determining, with the processor, at least one shape in the at least one image, the at least one shape being representative of a structure of the critical location; representing, with the processor, at least one region around the structure into a matrix; and applying, with the processor, image processing on the matrix to detect cracks in the at least one region of the structural component. | 03-26-2015 |
20150082634 | METHOD AND APPARATUS FOR ROTOR BLADE BALANCE - A method of assembling a rotor blade assembly includes determining a first spanwise moment of a first component of the rotor blade assembly and comparing the first spanwise moment to a target first spanwise moment. The first spanwise moment of the first component is adjusted based on a result of the comparison. A second spanwise moment of a second component of the rotor blade assembly is determined and compared to a target second spanwise moment. The second spanwise moment of the second component is adjusted based on a result of the comparison. The first component is assembled to the second component, resulting in a rotor blade assembly meeting a target spanwise moment of the rotor blade assembly. | 03-26-2015 |
20150078808 | ROD END WEAR PREVENTION - A rod and bracket assembly includes a bracket with a rod connected to the bracket via a fastener extending through a bracket hole. A bushing assembly is positioned at the bracket hole and includes a bushing having a bushing flange and a wear pad positioned between the bushing flange and an inner face of the bracket to prevent wear of the bracket and/or the rod in the event that the rod rolls about its own axis. A clevis assembly for a clevis and rod assembly includes a clevis having one or more clevis legs extending from a clevis base and a bushing assembly located at a clevis hole. The bushing assembly includes a bushing having a bushing flange and a wear pad disposed between the bushing flange and an inner face of the clevis leg to prevent wear of the clevis leg and/or the rod assembly. | 03-19-2015 |
20150078136 | Conformable Transducer With Self Position Sensing - Embodiments are directed to a diaphragm-based flexible array comprising a plurality of piezoelectric elements, wherein the array is configured to conform to a surface of a structure under evaluation and emit acoustic waves in two directions in sequence, a source configured to apply a voltage pulse to each element of the array, and a sensor configured to receive an acoustic pulse from each element of the array in response to application of the voltage pulse to each element of the array. | 03-19-2015 |
20150073627 | ROTOR TRACK AND BALANCE WITH IMPROVED LINEAR OPTIMIZATION - A method for reducing vibrations in an airframe of an aircraft includes determining, with a processor, information indicative of an initial error value between a desired vibration level and a measured vibration level in the airframe; determining, with the processor, an initial adjustment solution for the aircraft in response to the determining of the information for the initial error value; receiving, with the processor, information indicative of a flight response to the initial adjustment solution; combining, with the processor, disturbance signals indicative of vibration noise with the information for the flight response; determining, with the processor, a subsequent error value between the desired vibration level and a subsequent measured vibration level; and determining, with the processor, a predicted adjustment solution in response to the determining of the subsequent error value. | 03-12-2015 |
20150073626 | AIRCRAFT WEIGHT IDENTIFICATION USING FILTERED TRIM ESTIMATION - Embodiments are directed to receiving, by a computing device comprising a processor, at least one control input associated with an aircraft, obtaining, by the computing device, a predicted response to the at least one control input by filtering on a trim position, wherein the predicted response is based on a model of the aircraft, obtaining, by the computing device, an actual response of the aircraft to the at least one control input, comparing, by the computing device, the predicted response and the actual response, and determining, by the computing device, at least one attribute based on the comparison | 03-12-2015 |
20150060596 | TORQUE SPLIT GEARBOX FOR ROTARY WING AIRCRAFT - A gearbox system for a dual coaxial counter rotating rotor assembly includes an input shaft to input a first torque into the gearbox system and a transfer shaft operably connected to the input shaft to transfer the first torque therethrough. Two gear sets are operably connected to the transfer shaft. Each gear set includes a first output gear to transfer a second torque acting in a first direction to a first rotor of a rotor assembly and a second output gear to transfer the second torque acting in a second direction opposite the first direction to a second rotor of the rotor assembly. The second torque transferred by each gear set of the two gear sets is substantially equal. | 03-05-2015 |
20150060594 | HIGH SPEED COMPOSITE DRIVE SHAFT - A shaft assembly includes one or more axially-arranged plies having a plurality of bundles of strands. Each strand is formed of a ultra-high modulus carbon fiber material. One or more strands of glass fiber are wrapped around each bundle of the plurality of bundles. A volume of resin injected into the one or more axially-arranged plies and the assembly is cured via a resin transfer molding process. A method of forming a shaft assembly includes arranging a plurality of strands of ultra-high modulus carbon fiber material into a plurality of bundles. Each bundle of the plurality of bundles is wrapped with one or more strands of glass fiber material. The plurality of bundles are arranged into one or more axially-extending plies at a mandrel. A volume of resin is injected into the plurality of bundles and is cured to form the shaft assembly. | 03-05-2015 |
20150056427 | REMOVABLE MASK FOR COATING A SUBSTRATE - A system and a method for selectively coating a substrate includes a removable mask including a magnetic member having a first surface contour shaped to conform to the outside surface of the substrate and a magnetizable member having a second surface contour shaped to conform to the inside surface of the substrate. The method for coating the substrate includes magnetically coupling a removable mask to at least one surface of the substrate; forming a coating of a coating material on the at least one surface of the substrate with the magnetically coupled removable mask using a bath containing the coating material; and selectively decoupling the removable mask from the at least one coated surface to reveal a portion of the coated surface without the coating. | 02-26-2015 |
20150053815 | AUTOMATED ROTATING TAIL ROTOR CONTROL - Embodiments are directed to causing, by a computing device comprising a processor, a rotating tail rotor to operate in a tail rotor mode when an aircraft is operating at a speed less than a rudder control power threshold, receiving, by the computing device, a command that indicates a request to transition the aircraft, determining, by the computing device, that a rudder of the aircraft has control power in an amount greater than a second threshold based on receiving the command, and causing, by the computing device, the rotating tail rotor to operate in a pusher propeller mode based on determining that the rudder has control power in the amount greater than the second threshold. | 02-26-2015 |
20150050142 | CONTROLLING ROTOR BLADES OF A SWASHPLATELESS ROTOR - Controlling rotor blades of a rotor assembly includes determining an azimuthal position of a rotor assembly and identifying a lateral control command value, a longitudinal control command value and a collective control command value of a rotor assembly control system. A sine value and a cosine value of the azimuthal position are calculated and separate blade commands signals are generated for each separate blade of the rotor assembly to control a position of each blade independent of each other blade. The blade command signals are generated based on combining the sine and cosine values of the azimuthal position with the lateral control command value, the longitudinal control command value and the collective control command value. | 02-19-2015 |
20150039159 | HARD LANDING DETECTION AND ORIENTATION CONTROL - Embodiments of the disclosure are directed to obtaining, by a device, data associated with an aircraft, processing, by the device, the data, determining, by the device, that the aircraft is likely to impact an object with a probability greater than a threshold within a second threshold amount of time based on the processed data, and causing, by the device, a change in an orientation of the aircraft based on the determination. | 02-05-2015 |
20150034760 | AIRCRAFT TAIL ROTOR SYSTEM - An aircraft tail rotor system is provided and includes a rotating element, a translating element and a structure including a first bearing in series with a second bearing, the first bearing including a component rotatable with and movable within the rotating element in accordance with translational movement of the translating element. The structure is configured to selectively use the second bearing to prevent transmission of rotational energy from the rotating element to the translating element in an event of a seizing of the first bearing. | 02-05-2015 |
20150028597 | SWASHPLATELESS COAXIAL ROTARY WING AIRCRAFT - A main rotor system of an aircraft is provided including a first rotor coupled to a transmission and configured to rotate about an axis in a first direction. A second rotor is similarly coupled to the transmission and is configured to rotate about the axis in a second direction. At least the first rotor includes an individual blade control system (IBCS) configured to adjust a pitch of each of a plurality of blade of the first rotor independently. At least one slip ring is configured to transmit electrical power and/or a control signal to the at least one IBCS. | 01-29-2015 |
20150028152 | HELICOPTER ROTOR LOAD REDUCTION AND TIP CLEARANCE CONTROL - A method of controlling a helicopter having a rotor with blades is provided. The method includes receiving, by a computing device comprising a processor, at least one input associated with the helicopter; generating, by the computing device, control signals configured to counteract blade bending associated with the rotors based on the received at least one input; measuring, by the computing device, blade signals using sensors for the blades; extracting, by the computing device, harmonic loads from the measured blade signals; adapting, by the computing device, the control signals based on the harmonic loads; and controlling, by the computing device, servos connected to the blades to adjust the blades according to the adapted control signals to reduce vibratory loads on the blades. | 01-29-2015 |
20150021436 | WING MOUNT ADJUSTMENT - A mounting apparatus includes a fixed mounting structure that is fixed relative to a vehicle wing, the fixed mounting structure including a first fixed fitting and a second fixed fitting. The mounting apparatus further includes a rotatable mounting structure having a swivel fitting configured to engage the first fixed fitting and to swivel with respect to the first fixed fitting, the rotatable mounting structure also having a slide fitting configured to slide with respect to the second fixed fitting based on the swivel fitting being engaged with the first fixed fitting. | 01-22-2015 |
20140373521 | TORQUE CONVERTER FOR ROTORCRAFT - A torque converter for converting torque between an input shaft and an output shaft includes an impeller operably connected to the input shaft and rotatable therewith. The torque converter further includes a turbine operably connected to the output shaft and rotatable therewith. A fluid flow system directs a flow of motive fluid through the impeller and through the turbine to drive rotation of the output shaft relative to the input shaft. A lockup mechanism is engageable to urge rotation of the output shaft at an output shaft rotational speed identical to an input shaft rotational speed. A switching module controls an actuation system to urge engagement of the lockup mechanism. | 12-25-2014 |
20140341746 | MAIN ROTOR BLADE WITH COMPOSITE INTEGRAL SKIN AND CUFF - A main rotor blade assembly is provided including a spar which comprises a main section. A main core is positioned adjacent a trailing side of the main section of the spar. A tip assembly includes a main tip core and a tip end pocket core. The tip assembly is positioned adjacent an outboard end of the main core and the spar such that the main tip core is substantially aligned with a longitudinal axis of the main core and the tip end pocket core is substantially aligned with a longitudinal axis of the spar. At least a portion of both the main tip core and the tip end pocket core comprises a high density core. An upper composite skin and a lower composite skin extend over the spar, the main core, the main tip core, and the tip end pocket core. A portion of the upper composite skin and the lower composite skin has a thickness sufficient to be load bearing. | 11-20-2014 |
20140339366 | On-Blade Deice Heater Mat - A heater mat for a rotor blade includes a plurality of electrically conductive heater wires extending in a path along a span of the rotor blade and a plurality of yarn thread knitted to the plurality of heater wires, each of the yarn threads looping around at least one of the plurality of heater wires. A warp thread is positioned between adjacent heater wires and knitted to adjacent pairs of the yarn threads without looping around the plurality of heater wires, to maintain spacing between adjacent heater wires of the plurality of heater wires. An electrical current flowed through the plurality of heater wires inhibits ice accumulation on the rotor blade assembly. | 11-20-2014 |
20140318057 | STRUCTURE REPAIR WITH POLYMER MATRIX COMPOSITES - An assembly is provided including a structural component having a flange-like member. A partially cured polymer matrix composite patch is wrapped around a perimeter of the flange-like member. The patch includes a plurality of layers, each layer having a plurality of fibers arranged therein. The layers of the polymer matrix composite patch are cured after being wrapped around the flange-like member of the structural component. | 10-30-2014 |
20140316608 | SUSTAINED OVER-THE-HORIZON VERTICAL TAKEOFF AND LANDING SENSING SYSTEM - An electrically powered of the vertical takeoff and landing aircraft configured for use with a tether station having a continuous power source is provided including at least one rotor system. The vertical takeoff and landing aircraft additionally has an autonomous flight control system coupled to the continuous power source. The autonomous flight control system is configured to operate an electrical motor coupled to the at least one rotor system such that the vertical takeoff and landing aircraft continuously hovers above the tether station in a relative position. The vertical takeoff and landing aircraft also includes a detection system for detecting objects at a distance from the vertical takeoff and landing aircraft. | 10-23-2014 |
20140315040 | INTEGRALLY FORMED STIFFENER - A method of integrally forming at least one stiffener onto a sheet metal component configured to carry a load is provided including generating a stereolithography file. The stereolithography file includes a surface geometry of the at least one stiffener extending from a surface of the sheet-metal component. The surface geometry of the stereolithography file is sliced into a plurality of thin strips. The plurality of thin strips is substantially parallel to the surface of the sheet metal component. Energy from an energy source is applied to a powdered material such that the powdered material fuses to form the plurality of thin strips. One of the plurality of thin strips is integrally formed with the surface of the sheet-metal component. Each of the plurality of thin strips is integrally formed with an adjacent thin strip to create at least one stiffener. | 10-23-2014 |
20140314573 | INTEGRATION OF ROTARY ELECTRICAL ACTUATOR FOR SWASHPLATELESS INDIVIDUAL BLADE CONTROL - An individual blade control system (IBCS) for a rotor system having a rotor hub is provided including a plurality of blade cuffs mounted to the rotor hub. Each blade cuff is configured to receive a rotor blade and rotate about a blade axis. A plurality of electrical actuators is mounted to the rotor hub adjacent at least one of the plurality of blade cuffs. Each electrical actuator is configured to rotate about an actuator axis. The plurality of blade axes and the plurality of actuator axes are arranged in a plane. Each electrical actuator is coupled to an adjacent blade cuff such that rotation of one of the plurality of electrical actuators causes a proportional rotation of one of the blade cuffs. | 10-23-2014 |
20140314563 | VIBRATION CONTROL OF A SWASHPLATELESS COAXIAL ROTOR - A rotary wing aircraft is provided including a dual counter-rotating, coaxial rotor system having an upper rotor system and a lower rotor system rotatable about a common axis. A plurality of blade assemblies is mounted to a portion of either the upper rotor system or the lower rotor system. A plurality of individually controllable actuators is coupled to each of the plurality of blade assemblies. Each of the plurality of actuators is configured to control movement of the coupled blade assembly about a pitch axis. The rotary-wing aircraft additionally includes a sensor system within an airframe. A higher harmonic control (HHC) controller is arranged in communication with the sensor system and the plurality of actuators to individually control the upper rotor system and the lower rotor system to reduce vibration. | 10-23-2014 |
20140308123 | BEARING FOR ROTOR BLADE - A rotor blade assembly includes one or more flex-beam members and a torque tube surrounding the one or more flex-beam members and extending at least partially along a rotor blade assembly length. A pitch bearing assembly is supportive of the torque tube relative to the one or more flex-beam members and includes at least two outer bearing members secured to the torque tube and an inner bearing member positioned at least partially within the at least two inner bearing members and secured to the one or more flex beam members. A change in a stiffness of the inner bearing member changes one or more dynamic characteristics of the rotor blade assembly. | 10-16-2014 |
20140299709 | LOW DRAG ROTOR SYSTEM - A rotor assembly includes a rotor hub rotatable about a central axis including a plurality of rotor hub arms and blade yokes, each blade yoke including yoke arms located at opposing lateral sides of a corresponding one of the rotor hub arms to which the rotor hub arm is operably connected. The rotor assembly further includes blade retention bearings, each blade retention bearing being a single-element bearing disposed at a corresponding one of the rotor hub arms and which is supportive of a corresponding one of the blade yokes. Rotor blades are secured to corresponding ones of the blade yokes. | 10-09-2014 |
20140286774 | Flexbeam to Rotor Blade Interface - A spar for a rotor blade assembly is provided including a generally hollow tubular body. A spacer protrudes from at least one surface of the body along a length of the body. A hole extends through the body and the spacer. The hole is configured to align with a through hole in an adjacent flexbeam assembly. The spacer is configured to contact a surface of the adjacent flexbeam assembly to create a match fit between the body and the flexbeam assembly. | 09-25-2014 |
20140284420 | HELICOPTER EXTERNAL LIFE RAFT POD - An emergency pod configured for use with a rotary wing aircraft is provided including a rigid, generally hollow shell. The shell includes a movable portion configured to move between a closed position and an open position. An inflatable raft is arranged within an interior portion of the hollow shell. The life raft is coupled to an inflation mechanism. A first activation device and a second activation device are operably coupled to the inflation mechanism. The first activation device and the second activation device are configured to operate the inflation mechanism to initiation inflation of the life raft when a force is applied thereto. | 09-25-2014 |
20140278149 | RELIABILITY MAINTAINING SERIAL NUMBER CREDIT PROCESS - Embodiments are directed to receiving, by a computing device comprising a processor, an anticipated usage input, a load input and a strength input associated with a unit, calculating, by the computing device, a baseline reliability value based at least in part on the anticipated usage input, the load input and the strength input, receiving, by the computing device, usage data associated with use of the unit, generating, by the computing device, an updated reliability value based on at least some of the inputs used to calculate the baseline reliability value and the usage data, and determining, by the computing device, a lifetime for the unit based on the updated reliability value. | 09-18-2014 |
20140277855 | COMPENSATING FOR LEAD-LAG IN ROTOR SYSTEM - A control system for a rotor assembly includes a plurality of sensors configured to detect a lead-lag rate of each rotor blade of a plurality of rotor blades rotatable around a shaft and a flight control computer configured to generate lead-lag compensation signals based on the detected lead rate and lag rate of each rotor blade to control each rotor blade. | 09-18-2014 |
20140277669 | ADDITIVE TOPOLOGY OPTIMIZED MANUFACTURING FOR MULTI-FUNCTIONAL COMPONENTS - A computing device includes a processor, is operative on a plurality of constraints associated with a component, and integrates the constraints with a design optimization methodology across multiple variables including additive manufacturing constraints to generate a specification for the component. The component may be fabricated in accordance with the specification. | 09-18-2014 |
20140244075 | DAMAGE ADAPTIVE CONTROL - Embodiments of the disclosure are directed to measuring, via at least one sensor, at least one of a damage and a compromise associated with a vehicle, determining at least one of a region and a location of the at least one of a damage and a compromise and a level of the at least one of a damage and a compromise, and adapting an operational envelope for the vehicle based on the determined at least one of a region and a location of the at least one of a damage and a compromise and the level of the at least one of a damage and a compromise. | 08-28-2014 |
20140241884 | ROTARY WING AIRCRAFT PITCH BEAM ATTACHMENT WITH ANTI-ROTATION PLATE DESIGN - A retaining assembly for a tail rotor system is provided including a washer having a plurality of splines. The washer is configured to couple to an adjacent pitch change shaft. A retaining nut includes a self-locking feature and a flange arranged at a first end. The retaining nut is configured to threadably couple to the pitch change shaft such that the flange is in contact with the washer. The flange includes a plurality of first holes configured to at least partially align between the splines of the washer. A lock plate includes a body and a plurality of tabs extending generally perpendicularly from the body. The lock plate is slidably positioned about the pitch change shaft adjacent the flange. The lock plate is operably coupled to the retaining nut and the washer to limit rotational movement thereof relative to the pitch change shaft. | 08-28-2014 |
20140238224 | BALLISTIC PROTECTION MATERIAL - According to an embodiment, a ballistic protection material includes a strike face layer having a first thickness. The strike face layer is configured to distort an outer surface on a projectile that contacts the strike face layer. A ballistic layer is configured to hinder continued movement of a projectile that has passed through the strike face layer. A spacer layer is situated between the strike face layer and the ballistic layer. The spacer layer has a second thickness that is greater than the first thickness. The second thickness of the spacer layer provides a selected distance between the strike face layer and the ballistic layer. | 08-28-2014 |
20140217231 | ROTARY WING AIRCRAFT HAVING COLLOCATED EXHAUST DUCT AND PROPELLER SHAFT - An exhaust system for reducing infrared emissions of a rotary wing aircraft includes an exhaust duct having a fore end for connection with an aft turbine section of an engine of the rotary wing aircraft, the exhaust duct having an aft end having an exhaust opening to expel engine exhaust proximate to a tail fairing of the rotary wing aircraft; and a drive shaft collocated with the exhaust duct, the drive shaft configured to provide rotational force to an aft propeller of the rotary wing aircraft. | 08-07-2014 |
20140208573 | RIVETING TOOL - A riveting tool configured to install a plurality of fasteners simultaneously is provided including a body having a generally central cavity. A strike surface is arranged at a first end of the body and a plurality of contactors extends generally outwards from a second, opposite end of the body. Each contactor includes an engagement surface configured to contact a surface of an adjacent fastener when a force is applied to the strike surface. A biasing mechanism is arranged within the cavity adjacent an upper cavity surface. A dowel is positioned within the cavity adjacent the biasing mechanism. The dowel is configured to engage a portion of an adjacent nut plate and translate within the cavity. | 07-31-2014 |
20140203630 | OIL LEVEL INDICATOR FOR ROTARY WING AIRCRAFT TRANSMISSION - A fluid level sensor for determining an amount of first fluid in a system is provided including a first substantially transparent sight glass mounted outside and fluidly coupled to a portion of the system. A level of first fluid in the first sight glass is indicative of the amount of first fluid in the system. A second substantially transparent sight glass has an independent closed loop containing a second fluid. The second sight glass is positioned adjacent outside the system. A plane of the second sight glass is arranged adjacent to a pivot point of the first fluid within the system. A level of second fluid in the second sight glass is indicative of the amount of first fluid corresponding to normal operation of the system. A comparison of the level of first fluid in the first sight glass and the level of second fluid in the second sight glass indicates if the amount of first fluid in the system requires adjustment. | 07-24-2014 |
20140202650 | QUASI SELF-DESTRUCTIVE CORE FOR INVESTMENT CASTING - A composite core for forming a passage in an investment casting mold is provided including a generally hollow structural element. The structural element is configured to deform when a force is applied to an end thereof. A rigid shell element is formed about the structural element. The shell element extends beyond both an interior surface and an exterior surface of the structural element. The shell element is configured to shatter when the structural element deforms. | 07-24-2014 |
20140137724 | STRUCTURAL BALLISTIC PROTECTION PANEL - According an embodiment, a structural panel includes, among other things, a stiff composite material that establishes a base layer of the panel. A high molecular weight polyethylene fiber composite material establishes a ballistic protection layer of the panel that is secured to the base layer. A second composite material layer received against the ballistic protection layer such that the ballistic protection layer is situated between the second composite material layer and the base layer for providing a depth for recessed features. | 05-22-2014 |
20140124618 | COUNTER ROTATING FACEGEAR GEARBOX - A gearbox assembly includes a first face gear driveable about a face gear axis in a first direction by at least one first pinion gear and a second face gear driveable about the face gear axis in a second direction opposite the first direction by at least one second pinion gear. A thrust bearing is located between the first face gear and the second face gear. The first face gear is configured to drive rotation of a first shaft in the first direction and the second face gear is configured to drive rotation of a second shaft in the second direction. Further disclosed is a power train for a rotary wing aircraft having a gearbox including a first face gear rotatable in a first direction and a second face gear rotatable in a second direction opposite the first direction. | 05-08-2014 |
20140097044 | SECONDARY LUBRICATION SYSTEM WITH INJECTABLE ADDITIVE - A lubrication system includes an additive and a delivery system. During normal operational conditions, the lubricating oil circulating in the transmission system is collected and contained in a secondary oil reservoir to retain a quantity of the lubricating oil for use in an oil-out condition. When an oil-out condition is detected, the additive is injected and mixed with the collected lubricating oil in the secondary oil reservoir or dispersed directly into a power transmission gearbox housing to enhance the characteristics of the lubricating oil and increases the operational time period of the power transmission gearbox during an oil-out condition. | 04-10-2014 |
20140096501 | UPTURNED EXHAUST SYSTEM FOR ROTARY WING AIRCRAFT - An exhaust system for reducing infrared emissions of a rotary wing aircraft includes a manifold; an opening in the manifold, the opening configured to face upwards and away from the rotary wing aircraft; and a chimney including a wall positioned about the opening, the chimney configured to eject an emission of intermixed secondary air and engine exhaust upwards and away from the rotary wing aircraft. | 04-10-2014 |
20140095001 | ALTITUDE AND ACCELERATION COMMAND ALTITUDE HOLD ALGORITHM FOR ROTORCRAFT WITH LARGE CENTER OF GRAVITY RANGE - A flight control system includes an Acceleration and Attitude Command/Velocity Hold mode (AACVH) algorithm which blends attitude commands with acceleration commands This blending determines a trim attitude for a given rotorcraft flight condition. | 04-03-2014 |
20140079234 | NOISE SUPPRESSION DEVICE, SYSTEM, AND METHOD - A noise-suppression assembly of a mechanical drive system having a rotational frequency includes an audio filter unit configured to receive a first audio signal and a timing signal of the mechanical drive system. The audio filter unit generates a noise-cancellation signal based on a frequency of the timing signal to suppress a noise generated by the mechanical drive system and to apply the noise-cancellation signal to the first audio signal to produce a filtered first audio signal. The frequency of the timing signal is based on the rotational frequency of the mechanical drive system. | 03-20-2014 |
20140076882 | DUAL-CHANNEL DEICING SYSTEM FOR A ROTARY WING AIRCRAFT - A dual primary deicing system for a rotary-wing aircraft, according to an exemplary aspect of the present disclosure includes, among other things, an electrothermal heating element system; and a controller in communication with said electrothermal heating element, said controller communicating a heating cycle to said electrothermal heating element system, said heating cycle defining a first electric pulse train associated with a main rotor blade assembly. | 03-20-2014 |
20140067166 | METHOD OF CONTROLLING AN ELECTRIC PROPULSION SYSTEM - An apparatus is described comprising: at least one processor; and memory storing instructions that, when executed by the at least one processor, cause the apparatus to: regulate an operation of a motor based at least in part on a control imposed on an output torque of the motor and a rate of change of a speed of the motor. | 03-06-2014 |
20140008486 | ASYMMETRICAL SINGLE MAIN ROTOR UNMANNED AERIAL VEHICLE - A single engine rotary wing aircraft is provided including a fuselage having a longitudinal first axis. A main rotor assembly is mounted to the fuselage for rotation about a second axis, perpendicular to the first axis. A tailboom is connected to an empennage. The tailboom is mounted to an end of the fuselage such that the tailboom is laterally offset from the first axis in a first direction. The rotary wing aircraft also includes a propulsion system. The single engine of the propulsion system is laterally offset from the first axis in a second direction opposite the first direction. | 01-09-2014 |
20130344295 | LATTICE GRID CAUL FOR HONEYCOMB COMPOSITE STRUCTURE - A caul system for a composite structure having one or more core elements includes a lattice grid hard caul selectively locatable at a portion of the composite structure without core elements. The caul system further includes a soft caul selectively locatable at a portion of the composite structure having a core element. A method of forming a composite structure with one or more core elements includes locating a first laminate in a tool and locating one or more core elements over the first laminate. A second laminate is located over the one or more core elements. A lattice grid hard caul is placed over the second laminate, avoiding locations having core elements of the one or more core elements disposed thereat. A soft caul is located over the one or more core elements, thereby preventing deformation of the one or more core elements. | 12-26-2013 |
20130338858 | METHOD FOR THREE DIMENSIONAL PERCEPTION PROCESSING AND CLASSIFICATION - An apparatus is described comprising at least one processor; and memory storing instructions that, when executed by the at least one processor, cause the apparatus to: organize items of raw data received from at least one sensor of a vehicle as a first data structure, organize classified data objects as a second data structure, and link at least one item of the first data structure to at least one object of the second data structure. | 12-19-2013 |
20130334362 | PLANETARY DE-ROTATION SYSTEM FOR A SHAFT FAIRING SYSTEM - A fairing system according to an exemplary aspect of the present disclosure includes, among other things, a shaft fairing mounted for rotation about an axis of rotation and a planetary gear set configured to control a position of the shaft fairing about the axis of rotation. | 12-19-2013 |
20130327879 | HIGH SPEED COMPOUND ROTARY WING AIRCRAFT - A rotary wing aircraft includes an airfame and an extending tail extending from the airframe. A main rotor assembly is operably connected to the airframe and includes a plurality of rotor blades operably connected to a rotor shaft, and one or more active adaptive devices located at one or more rotor blades of the plurality of rotor blades. The one or more active adaptive devices are operably connected to an aircraft flight control system such that, when activated, the one or more active adaptive devices change one or more operational characteristics of the rotor assembly. A tail rotor is operably connected to the extending tail. The tail rotor is rotatable about a tail rotor axis and the tail rotor axis movable from laterally-extending to rearward-extending. | 12-12-2013 |
20130325218 | SYNTHETIC ESTIMATION OF ROTORCRAFT AIRSPEED - A method for estimating airspeed of an aircraft includes receiving values indicative of operating conditions of the aircraft along an axis; estimating a tip path plane (TPP) angle along the axis from at least one of the operating conditions to create an estimated TPP angle; and determining an estimated airspeed as a function of the estimated TPP angle, the determining including referencing a look-up table that indexes the estimated TPP angle with the airspeed. | 12-05-2013 |
20130313371 | ENGINE INLET - An inlet duct for an engine or multiple engines includes two or more joining duct legs and a pressure relief pathway located at each duct leg to condition inlet airflow from the duct legs. A method of operating an aircraft includes urging an inlet airflow into two or more duct openings disposed at a fuselage of the aircraft. The inlet airflow is urged through two or more converging inlet duct legs extending from the two or more duct openings toward an engine inlet. A portion of the inlet airflow is flowed from at least one inlet duct leg of the two or more inlet duct legs into a pressure relief pathway. An inlet duct for an engine or multiple engines includes one or more inlet duct legs and a bypass leg extending from an inlet duct leg of the one or more inlet duct legs through a bypass opening. | 11-28-2013 |
20130304400 | SYSTEM AND METHOD OF DETERMINING ROTOR LOADS AND MOTION - A system for reconstructing sensor data in a rotor system that comprises a rotating component of the rotor system, a plurality of sensors in the rotating component to sense at least one of loads and motion characteristics in the rotating component and to generate sensor data, and an analysis unit to generate reconstructed sensor data from the sensor data using numerical analysis for low-rank matrices. | 11-14-2013 |
20130299640 | AUTOMATIC CARGO HOOK RELEASE ASSEMBLY - A method of releasing cargo suspended from at least one cargo hook release pendant in a suspension system coupled to a cargo hook release system includes receiving a voltage release signal at a cargo hook control interface and a cargo release harness assembly; receiving an energizing voltage signal at the cargo release harness assembly; energizing a relay in response to receiving the energizing voltage signal, the relay being electrically coupled to the cargo release harness assembly; automatically transmitting the voltage release signal from the cargo release harness assembly to at least one cargo hook release pendant in response to energizing the relay; and automatically releasing the cargo from at least one cargo hook release pendant in response to automatically transmitting the voltage release signal. Also, the cargo hook release system includes the cargo hook control interface, the cargo release harness assembly, and at least one cargo hook release pendant. | 11-14-2013 |
20130294914 | MULTI-ELEMENT ROTOR BLADE - A main rotor assembly for a rotary wing aircraft includes a blade assembly secured to a rotor hub. The blade assembly includes a rotor blade and a slat positioned to define a slat gap between the rotor blade and the slat. One or more struts extend from the rotor blade to the slat to position the slat and control motion of the slat. The rotor blade and the slat are secured to a common rotor cuff such that the rotor cuff acts as a centrifugal force support. | 11-07-2013 |
20130275059 | HYBRID VIRTUAL LOAD MONITORING SYSTEM AND METHOD - Virtual sensors can be used to monitor the loads on the system in determining damage accumulation, remaining useful life or retirement time of the components. A virtual sensor is a mathematical construct to infer a desired system measurement (e.g. a structural load) from readily available system state parameters (e.g. speed, weight, load factors, control settings, etc.). The accuracy of the virtual sensor depends upon the mapping between the desired measurement and the state parameters. A hybrid load monitoring system and method includes one or more direct or physical sensor measurements in addition to the plurality of virtual sensors. Signals from the physical sensors are included as an input (as opposed to an output) to the mapping between system state parameters and the various target sensor feature amplitudes. | 10-17-2013 |
20130248648 | Portable Control System For Rotary-Wing Aircraft Load Management - A control system for portable control of a rotary-wing aircraft includes a portable, hand-held, control device executing a control application, the control device operating in a loaded mode when a load is attached to the rotary-wing aircraft and an unloaded mode when no load is attached to the rotary-wing aircraft, the control device presenting command icons in response to being in loaded mode and unloaded mode; a vehicle management system in the rotary-wing aircraft; a sensor package on the rotary-wing aircraft; and a communication system providing communications between the control device and the rotary-wing aircraft, vehicle management system and sensor package; wherein the control device communicates commands to the vehicle management system to implement loading and unloading of the rotary-wing aircraft. | 09-26-2013 |
20130233977 | Engine Starting System For Rotorcraft In Flight - A rotorcraft engine starting system includes a starting system controller in communication with a flight control computer; an electric engine starter; an electronic engine controller in communication with the electric engine starter; an electrical power distributor; and a plurality of power sources coupled to the electrical power distributor; the starting system controller selecting at least one of the plurality of power sources and instructing the electrical power distributor to use the at least one of the plurality of power sources to power the electric engine starter. | 09-12-2013 |
20130228647 | Rotary Wing Aircraft Propulsion System - A rotary wing aircraft propulsion system includes an engine, a heat exchanger cooling a fluid from the engine and a thermoelectric generator in thermal communication with the fluid to generate electrical power. The thermoelectric generator provides electrical power to at least one aircraft component. | 09-05-2013 |
20130228646 | RETRACTING TAILWHEEL ASSEMBLY AND FIN - A tailwheel assembly for an aircraft includes a ventral fin including a fixed airframe portion of the ventral fin and a moveable tailwheel portion of the ventral fin. A tailwheel strut extends through the ventral fin and includes a fixed first strut portion and an extendable second strut portion having the moveable tailwheel portion of the ventral fin secured thereto. A tailwheel is secured to the extendable second strut portion. A method of operating a tailwheel assembly for an aircraft includes extending an extendable portion of a tailwheel strut from an airframe of the aircraft. The tailwheel strut has a tailwheel secured thereto and is located at least partially in a ventral fin of the aircraft. A tailwheel portion of the ventral fin is moved away from a fixed airframe portion of the ventral fin via extension of the extendable portion of the tailwheel strut. | 09-05-2013 |
20130224507 | VIBRATION ABSORBING DEVICE FOR FLEXBEAMS - A replacement vibration absorbing device for replacing a wear wrap on a flexbeam includes a sleeve having a plurality of layers of vibration absorbing material, wherein an edge of the sleeve is cut so that the sleeve may be installed around a generally central portion of a flexbeam. | 08-29-2013 |
20130224022 | HELICOPTER BLADE RETENTION COMPOSITE YOKE - A rotary wing aircraft yoke is provided including an arcuate medial portion. A pair of arms extends from the medial portion and each terminates in a distal end. The yoke is made from multiple plies of glass and graphite fibers of varying orientations. The number of graphite plies increases along each arm from adjacent the medial portion to the distal end. | 08-29-2013 |
20130224017 | MISSION ADAPTIVE ROTOR BLADE - A rotor assembly for a rotary wing aircraft includes a plurality of rotor blades operably connected to a rotor shaft. Two or more active adaptive devices are located at one or more rotor blades of the plurality of rotor blades. The one or more active adaptive devices are operably connected to an aircraft flight control system such that, when activated, the one or more active adaptive devices change one or more operational characteristics of the rotor assembly. A method of operating a rotor assembly of a rotary wing aircraft includes rotating a plurality of rotor blades about a rotor shaft. Two or more active adaptive devices located at one or more rotor blades of the plurality of rotor blades are activated and change one or more operational characteristics of the rotor assembly. | 08-29-2013 |
20130218372 | Weapons Stores Processor Panel For Aircraft - An aircraft weapons control system including a weapons stores processor panel for receiving input signals from a weapons input; a weapons interface for receiving fire signals from the weapons stores processor panel to control firing of aircraft weapons; and a flight management system in communication with the weapons stores processor panel and the weapons interface, the flight management system providing control signals to the weapons interface; wherein the weapons stores processor panel implements safety interlocks to prevent or enable firing of the aircraft weapons | 08-22-2013 |
20130215536 | FAULT CLEARING WITHOUT A DC BACKUP POWER SOURCE - An electrical power protection system, includes a generator configured for supplying Direct Current (DC) power to a load bus, the load bus in electrical communication with a bus circuit; a generator control unit being configured for regulating the output voltage supplied by the generator; a bus contactor in serial communication with the bus circuit, the bus contactor including logic circuits configured for detecting an overcurrent in the bus circuit, the overcurrent representative of a ground fault in the bus circuit; and a capacitor bank coupled to the generator for selectively supplying an excitation voltage through a diode switch to the generator during the ground fault in the bus circuit. | 08-22-2013 |
20130214597 | ELECTRICAL POWER DISTRIBUTION SYSTEM - A distributed electrical power system includes a first AC generator configured for supplying an AC voltage; a second AC generator configured for supplying the AC electrical voltage; an AC power distribution network connected to the first AC generator and the second AC generator for receiving the AC voltage, the AC power distribution network including a two or four-wire AC power distribution circuit; at least one (solid state circuit breaker (SSCB) module remotely located for receiving the AC voltage from the power distribution network; a system controller connected to a data bus for controlling operation of the at least one power distribution module; and at least one contactor for selectively switching supply of the AC voltage to the at least one power distribution module from either the first AC generator or the second AC generator upon failure of either of the first AC generator or the second AC generator. | 08-22-2013 |
20130214095 | SLEEVE AND ROD SUPPORT FOR FUEL BLADDER - A flexible fuel bladder structure for an aircraft includes one or more sleeves extending along an exterior of the fuel bladder. The one or more sleeves are receptive of one or more rods to at least partially suspend the fuel bladder in the aircraft. An aircraft includes a fuselage and a flexible fuel bladder disposed in the fuselage. One or more rods are installed through a portion of the fuel bladder and into a fuselage member. The flexible fuel bladder is at least partially suspended from the one or more rods. A method of installing a fuel bladder in an aircraft includes inserting a flexible bladder into a fuselage space of the aircraft. One or more rods are installed through one or more fuselage members and one or more sleeves of the fuel bladder. The one or more rods at least partially suspend the fuel bladder in the fuselage. | 08-22-2013 |
20130211634 | METHOD AND SYSTEM FOR PROVIDING SIDESLIP ENVELOPE PROTECTION - A system for providing sideslip envelope protection includes a processor for obtaining values of a sideslip envelope indicative of operating conditions of the aircraft along an axis and for estimating a sideslip angle along the axis from at least one operating condition; and a comparer for comparing the sideslip angle with the sideslip envelope to generate an output value, where the processor determines a maximum yaw rate from the output value and scales the maximum yaw rate to generate a scaled yaw rate. | 08-15-2013 |
20130206899 | Control System For Reconfigurable Rotary Wing Aircraft - A control system for a rotary wing aircraft having a reconfigurable element. The control system includes a model predictive control module receiving operator commands, objectives and constraints; and a dynamic inversion module receiving an output of the model predictive control module, the dynamic inversion module providing control commands to reconfigure the reconfigurable element of the rotary wing aircraft. | 08-15-2013 |
20130192374 | RETROREFLECTOR FOR ULTRASONIC INSPECTION - A system for ultrasonic inspection of a structure includes a transducer located at a first surface of the structure to transmit an ultrasonic signal from the transducer through the first surface to a second surface of the structure located substantially opposite the first surface. A plurality of retroreflector elements are located at the second surface to reflect the ultrasonic signal back toward the transducer. A method of ultrasonic inspection of a structure includes transmitting an ultrasonic signal from a transducer located at a first surface of the structure toward a second surface of the structure located substantially opposite the first surface. The ultrasonic signal is reflected back toward the transducer via a plurality of retroreflector elements disposed at the second surface. | 08-01-2013 |
20130164132 | DUAL FREQUENCY HUB MOUNTED VIBRATION SUPPRESSOR SYSTEM - A vibration suppressor system includes an annular electric motor system which independently controls rotation of at least two masses about the axis of rotation to reduce in-plane vibration of the rotating system. A method of reducing vibrations in a rotary-wing aircraft includes independently controlling a relative angular position of a multiple of independently rotatable masses to reduce vibrations of a main rotor system. | 06-27-2013 |
20130162035 | MULTI-DIRECTIONAL ELECTRICAL POWER PROTECTION SYSTEM - A multidirectional electrical power protection system, includes a first power supply and at least a second power supply with each supply being configured for supplying power to a main bus circuit; a first load bus electrically connected to the first power supply and at least the second power supply, at least a second load bus electrically coupled with each of the first power supply and at least the second power supply, the first load bus and the second load bus configured for energizing devices connected to the respective first and second load bus; and at least one smart contactor in coupled with the main bus circuit, the at least one smart contactor being configured for sensing a first current flowing in a first direction through the main bus circuit and for sensing a second current flowing in a second direction through the main bus circuit. | 06-27-2013 |
20130160605 | SPLIT-TORQUE GEAR BOX - A split torque gearbox system provides a multiple path, three stage power gear train that transmits torque from a high-speed engine to a low speed output shaft, while providing equal gear load distribution with a floating pinion in the second stage of reduction. The number of the split modules in the gearbox depends on gearbox configuration, number of high speed input shafts, and transmitted power. The split modules are located around a last stage output gear that combines power from each module and transmits the power to an output such as a main rotor system. | 06-27-2013 |
20130152389 | ROTOR BLADE REPAIR STRUCTURE AND METHOD - A method of repairing a damaged portion of a rotor blade includes filling the damaged portion with a filler material. A pre-cured patch assembly is applied over the damaged portion, the patch assembly including one or more laminate packs positionable at least one of an upper rotor blade surface and a lower rotor blade surface and one or more overwrap plies positionable over the upper rotor blade surface and the lower blade surface. A repair structure for a damaged portion of a rotor blade includes a volume of fill material disposed at the damaged portion. | 06-20-2013 |
20130149475 | Composite Core Densification - A reinforcement tube for composite core densification and a composite article therewith. | 06-13-2013 |
20130149160 | AIRFOIL FOR ROTOR BLADE WITH REDUCED PITCHING MOMENT - A rotor blade for a rotary wing aircraft includes a root region extending from a rotor head to about 15% to 20% of a blade radius, a main region extending from a radial extent of the root region to about 80% to 95% of the blade radius, and a tip region extending from a radial extent of the main region to a blade tip. At least a portion of one of the root region, the main region and the tip region includes an airfoil profile section defined by a scaled set of coordinates in which a set of y/c coordinates listed in Table I are scaled by a selected factor. | 06-13-2013 |
20130103182 | CUTTING TOOL DATA VERIFICATION SYSTEM AND METHOD - A method of operating a machining system includes comparing one or more features of a cutting tool to information stored on a data chip secured to a tool holder of the cutting tool. The cutting tool is loaded into the machining system, and the information stored on the data chip is compared to cutting tool requirements of a machining program for instructing operation of the machine. When a result of one or more of the comparisons is outside of a predetermined threshold, operation of the machining system is stopped. | 04-25-2013 |
20130099064 | Methods And Systems For Providing Constant-Feel, Multi-Axis Tactile Cues - A system for adjusting tactile cues includes a controller having an axis and a cross-axis; an axis tactile cue generated in response to the position of the controller along the axis; a position scaling unit scaling a cross-axis controller position to generate a scaled cross-axis controller position; a force scaling unit scaling a cross-axis controller force to generate a scaled cross-axis controller force; a combiner combining the scaled cross-axis controller position and the scaled cross-axis controller force to generate an adjustment factor; and an adjuster adjusting the axis tactile cue in response to the adjustment factor to generate an adjusted axis tactile cue. | 04-25-2013 |
20130095284 | COMPOSITE STRUCTURE AND CORE POSITIONING PLY - A composite structure includes a first laminate, a second laminate, and at least one core component located between the first laminate and the second laminate. The at least one core component includes a honeycomb core and at least one locking ply extending from the honeycomb core between the first laminate and the second laminate. The at least one locking ply is configured such that a pressure applied during a cure cycle of the composite structure retains the at least one locking ply between the first laminate and the second laminate thereby preventing movement of core component. | 04-18-2013 |
20130094959 | ROTOR BLADE COMPONENT COOLING - A rotor blade for a rotary wing aircraft includes a component bay located substantially enclosed in the rotor blade and one or more components positioned in the component bay. An airflow is located at the component bay and an airflow outlet is located at the component bay radially outboard of the airflow inlet. The airflow inlet and airflow outlet allow a continuous airflow through the component bay via centrifugal forces of rotation of the rotor blade, the continuous airflow cooling the one or more components disposed at the component bay. | 04-18-2013 |
20130078100 | LOW OFFSET HINGELESS ROTOR WITH PITCH CHANGE BEARINGS - A hub assembly for a tilt rotor includes a yoke having a plurality of yoke arms located substantially orthogonal to a central axis of the hub assembly. An inboard pitch change bearing assembly substantially surrounds a yoke arm of the plurality of yoke arms. An outboard pitch change bearing assembly is located at the yoke arm. The inboard pitch change bearing assembly and the outboard pitch change bearing assembly are operably connectable with a rotor blade to allow pitch change of the rotor blade relative to the yoke about a pitch change axis. | 03-28-2013 |
20130075271 | PROTECTION OF MAGNESIUM ALLOYS BY ALUMINUM PLATING FROM IONIC LIQUIDS - A method for electroplating aluminum metal on a magnesium alloy includes providing an Lewis acidic ionic liquid having dissolved species of an aluminum metal salt; pre-treating a surface of the magnesium alloy including subjecting the surface of the magnesium alloy to a reverse current etching in the ionic liquid; electroplating the aluminum metal on the surface using the ionic liquid as the electrolyte; and subjecting the surface of the magnesium alloy to a post-treatment including neutralization rinsing in a rinsing solvent solution. | 03-28-2013 |
20130064674 | ROTOR WITH BLADES INCLUDING OUTER BLADE SHELL AND INNER STRUCTURAL MEMBER - A rotor for use in an aircraft includes an inner hub; and a plurality of blades arranged around the inner hub, each of the plurality of blades comprising an inner structural member; an outer blade shell surrounding the inner structural member; and a centering block located at a base of the inner structural member proximal to the inner hub, wherein the centering block is located between a first lateral portion of the inner structural member and a second lateral portion of the inner structural member, wherein the centering block is further connected to the outer blade shell, and wherein the centering block allows the outer blade shell to rotate about an axis approximately corresponding to the inner structural member. | 03-14-2013 |
20130062808 | CONFORMAL DELTOID NOODLE FOR A COMPOSITE STRUCTURE - A method of fabricating a conformal deltoid noodle includes providing a composite prepreg material having a predetermined length and a width, the predetermined length being aligned along a longitudinal axis; subjecting the composite prepreg material to a cutting process to form a notched section coextensive along the predetermined length; and rolling the composite prepreg material along its width to create the conformal deltoid noodle. | 03-14-2013 |
20130056586 | AUTOMATIC JETTISON SYSTEM FOR A ROTORCRAFT - A method of automatically jettisoning cargo suspended from a suspension system coupled to an auto jettison system, includes receiving an initial load value from at least one attachment point of the suspension system, the receiving of the initial load value in response to attaching the cargo to the suspension system; receiving an instantaneous load value of the cargo suspended on an attachment point, the attachment point being coupled to the cargo; predicting a rate of change of the instantaneous load value at a predetermined future time period; combining the predicted rate of change of the instantaneous load value with the initial load value to create a predicted load value; comparing the predicted load value to a threshold value for the attachment point; and jettisoning the cargo from the attachment point if the predicted value is greater than the threshold value. | 03-07-2013 |
20130054053 | TORQUE BASED POWER LIMIT CUEING SYSTEM AND METHOD - A torque based power limit cueing system is provided and includes an engine computer to compile data relating to torque and additional information of each of one or more engines, an active stick by which tactile cueing are provided to a pilot and by which the pilot inputs control commands, a multi-function display (MFD) by which visible cues are provided to the pilot and a flight control computer (FCC) operably coupled to the engine computer, the active stick and the multi-function display, the FCC being configured to receive the data from the engine computer and to output tactile cue commands and visible commands in accordance with the torque and the additional information of each of the one or more engines to the active stick and the MFD, respectively. | 02-28-2013 |
20130052034 | NON-ROTATING STATIONARY GROUND TUBE FOR A WIND FAIRING - A stationary ground tube for use in an aircraft rotor fairing includes a first cylindrical portion including a first bore aligned along a longitudinal axis, the cylindrical body portion having a tubular body from a first end to a second end; and a second cylindrical portion coupled to the first cylindrical portion, the second cylindrical portion including a second bore aligned along the longitudinal axis. The second cylindrical portion is coupled to the aircraft rotor fairing via at least one attachment device. | 02-28-2013 |
20120320159 | Apparatus And Method To Automatically Distinguish Between Contamination And Degradation Of An Article - An inspection apparatus includes an imaging unit producing image signals; a processing unit for receiving the image signal; the imaging unit producing a stack of images of an article at different focal lengths in response to the processing unit; the processing unit generating a depth map from the stack of images; the processing unit analyzing the depth map to derive a depth profile of an object of interest; the processing unit determining a surface mean for the article from the stack of images; and the processing unit characterizing the article as degraded or contaminated in response to the depth profile and the surface mean. | 12-20-2012 |
20120310448 | AIRCRAFT ENVIRONMENTAL THREAT DETECTION AND MITIGATION - A method of aircraft engine thermal threat mitigation includes detecting an airflow thermal profile at a location on the aircraft forward of an aircraft engine inlet and transmitting the thermal profile to an aircraft control system. The thermal profile is compared to a catalog of thermal threat profiles at the aircraft control system and a determination is made if a thermal threat is present based on the comparison. A thermal threat mitigation measure is initiated to reduce an effect of the thermal threat on aircraft engine performance. | 12-06-2012 |
20120292434 | Six Degrees Of Freedom Vibration Suppression - A vibration suppression system for a rotorcraft having an airframe, a main gear box, a rotor, a hub, and a rotor head, said system comprising a hub mounted vibration suppressor (HMVS) mounted on the rotor head to reduce in-plane loads that the rotor exerts on the hub; and a plurality of active vibration control (AVC) actuators grouped in an overhead of the airframe beneath and proximate to the main gear box, to reduce residual loads. | 11-22-2012 |
20120276362 | FAY SURFACE SEALANT APPLICATION - A method of sealing between two components includes applying and curing a layer of fay surface sealant to a first component. A layer of liquid shim is applied to one or more of the first component and a second component. The first component is assembled to the second component with the layer of fay surface sealant and the layer of liquid shim therebetween. An assembly of two components includes a first component and a layer of fay surface sealant applied and cured to a first facing surface of the first component. A second component includes a second facing surface, such that the second facing surface and the layer of fay surface sealant define a gap therebetween. A layer of liquid shim is located between the second component and the layer of fay surface sealant thereby substantially filling the gap. | 11-01-2012 |
20120255676 | EXTERNAL TO BAGGING MECHANICAL CLAMP - A tool for forming a panel including a core area, at which plies sandwich a core, and a trim area surrounding the core, at which the plies are bonded together, is provided and includes a body having a surface on which the panel is formable, an assembly to apply bonding pressure to the plies at least at the core and trim areas and a clamping device external to the assembly to apply a clamping force to the vacuum bag and the plies. | 10-11-2012 |
20120253652 | Method and System for Detecting Forces on Aircraft - A system for sensing a force applied to an aircraft includes a first sensor, a second sensor, and a processor operative to define a first velocity vector as a function of a first velocity due to a rotation motion of the aircraft, define a second velocity vector as a function of a second velocity due to the rotation motion of the aircraft, define an instant axis of rotation of the aircraft as a function of the first velocity vector and the second velocity vector, determine whether a force has been exerted on a first portion of the aircraft, and output an indication that a force has been exerted on the first portion of the aircraft responsive to determining that the force has been exerted on the first portion of the aircraft. | 10-04-2012 |
20120207602 | MODULAR INTEGRATED DEVICE FOR ROTOR BLADE CONTROL - A rotor blade assembly includes a rotor blade including one or more pockets and a housing located on the rotor blade within one or more pockets. The housing is secured to the rotor blade via one or more dovetail joints. A drive mechanism for a control surface of a rotor blade includes an actuator and a rocker operably connected to the actuator. At least one hinge rod is operably connected to the rocker and operably connected to a control surface at a control surface pivot. The drive mechanism translates substantially linear motion of the actuator into rotational motion of the control surface about the control surface pivot. | 08-16-2012 |
20120204741 | CO-CURING REUSABLE ELASTOMERIC CAUL PLATE - A caul plate system for a laminate structure includes a plurality of layers of curable caul plies disposed over a laminate structure and substantially conforming to a surface of the laminate structure. A resin is applied to the plurality of layers of caul plies. Co-curing of the plurality of layers of caul plies with the laminate structure hardens the plurality of layers of caul plies such that a normal pressure is applied to the laminate structure during cure of the laminate structure. | 08-16-2012 |
20120201678 | FLEXBEAM ROTOR - A rotor hub assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extend through the rotor hub, with each end of each flex beam operably connectible to a rotor blade. One or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A rotor assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extending through the rotor hub and one or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A plurality of rotor blades are operably connected to the ends of the one or more flex beams. | 08-09-2012 |
20120199292 | PLY LOCKING FOR HONEYCOMB PANELS - A tool for forming a panel including a core area, at which plies sandwich a core, and a trim area surrounding the core, at which the plies are bonded together, is provided and includes a body having a surface on which the panel is formable, the surface including core and trim portions for respective correspondence with locations of the core and trim areas of the panel, a border between the core and trim portions defining a surface feature displaced from a plane of the core portion, a lock disposable proximate to the surface feature to increase a pre-bonding friction between the plies at the surface feature and an assembly to apply bonding pressure to the plies and the lock at least at the core and trim areas. | 08-09-2012 |
20120181389 | PASSIVE CONTROL OF ICE SHEDDING - A plate including a body with an aft face at an aft portion of the body, which is attachable to a leading edge of an ice accretion surface such that the body protrudes substantially in a forward direction from the leading edge, and a forward face opposite the aft face, which extends between opposing surfaces of the body and which is oriented substantially perpendicularly with respect to the forward direction and a predominant flow direction of air flowing past the leading edge. | 07-19-2012 |
20120181379 | MOMENT LIMITING CONTROL LAWS FOR DUAL RIGID ROTOR HELICOPTERS - A method of counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes sensing angular velocity and angular acceleration of a helicopter during a flight maneuver. The angular velocity and angular acceleration are compared to a set of control parameters and one or more control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment. A control system for counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes one or more sensors configured to sense angular velocity and angular acceleration of a helicopter during a flight maneuver. A computer is operably connected to the one or more sensors and configured to compare sensor data to a set of control parameters. A plurality of control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment. | 07-19-2012 |
20120181377 | VIBRATION CONTROL SYSTEM - A vibration control system includes four mass discs located at a central axis and rotatable thereabout. Each mass disc includes a mass secured thereto wherein rotation of the four mass discs creates a vibratory force output. A power transfer assembly is located between adjacent mass discs of the four mass discs and is configured to transfer rotational energy between the adjacent mass discs. The power transfer assembly includes a power transfer shaft rotatable about a power transfer shaft axis and a power transfer disc connected to the power transfer shaft and in frictional contact with each of the adjacent mass discs at a contact point. When the power transfer shaft is rotated, a radial location of the contact point at each of the adjacent mass discs relative to the central axis is changed, altering the vibratory force. | 07-19-2012 |
20120156033 | HELICOPTER ROTOR CONTROL SYSTEM - A rotor control system operatively linked to a plurality of rotor blades includes a swashplate assembly having a stationary member and a rotating member. A blade attachment member is operatively connected to the plurality of rotor blades and a control horn is operatively connected to the blade attachment member and one of the plurality of rotor blades. At least one hydraulic actuator member is operatively coupled to the control horn and at least one hydraulic actuator element is operatively coupled to the swashplate assembly and the at least one hydraulic actuator member. The at least one hydraulic actuator member transmits control signals from the swashplate assembly to the one of the plurality of rotor blades through the at least one hydraulic actuator member. | 06-21-2012 |
20120136512 | External Load Inverse Plant - A method of controlling the flight of a rotorcraft in a feed-forward/feedback architecture includes utilizing an aircraft plant model to control the rotorcraft performance; determining when an external load is coupled to the rotorcraft; and modifying an inverse plant when the external load is present. | 05-31-2012 |
20120121412 | BLADE FOLD SYSTEM MONITORING - A rotor blade fold system for an aircraft includes one or more actuators operably connected to one or more blade components of one or more rotor blades of the aircraft. One or more sensors are located at the one or more rotor blades and are configured to sense operation of the one or more blade components. A fold control system is configured to monitor output from the one or more sensors and is capable of stopping operation of the blade fold system, via communication with the one or more actuators, if the one or more blade components are not operating within predetermined limits. | 05-17-2012 |
20120116612 | IMPLEMENTATION OF KALMAN FILTER LINEAR STATE ESTIMATOR FOR ACTUATOR EQUALIZATION - A rotorcraft control system is provided and includes a rotor blade having a moving surface operatively connected for movement among various positions, an actuator receptive of a modified control signal and operatively connected to move the surface among the various positions, a sensor operably coupled to the actuator to generate a sensor response signal reflective of a response of the actuator to the modified control signal and a controller to output the modified control signal to the actuator, the controller including a control loop to generate the modified control signal from an initial control signal that is modified by relating the initial control signal and the sensor response signal and by accounting for actuator inaccuracies, sensor sensitivities and noise. | 05-10-2012 |
20120045344 | HELICOPTER COMPOSITE BLADE SPAR AND METHOD - A composite spar for a helicopter blade includes two or more layers of unidirectional laminate material. One or more upper plies of bi-directional laminate extend from an upper airfoil portion of the spar disposed between adjacent layers of the two or more layers of unidirectional laminate material. One or more lower plies of bi-directional laminate material extend from a lower airfoil portion of the spar disposed between adjacent layers of the two or more layers of unidirectional material. The upper plies and the lower plies overlap defining a crackstopper layer configured to prevent propagation of defects in the spar. | 02-23-2012 |
20120018569 | EXTERNAL CARGO HOOK SYSTEM FOR ROTARY-WING AIRCRAFT - An external hook system for a rotary-wing aircraft includes a lower frame interface which accommodates longitudinal and lateral loads and an upper frame interface. A tension member is mountable between the lower frame interface and the upper frame interface to transfer tension loads between the lower frame interface and the upper frame interface. | 01-26-2012 |
20120004844 | FORMATION FLYING METHOD AND SYSTEM - A method for directing formation flying of an aircraft includes sensing a relative position of a leader to a follower aircraft by one or more sensors disposed at the follower aircraft. The relative position is compared to a selected relative position, and a follower velocity of the follower aircraft necessary to move the follower aircraft to the selective relative position is determined via a flight control computer of the follower aircraft. The follower velocity is transformed into flight control inputs and the follower aircraft is moved to the selected relative position via the flight control inputs. | 01-05-2012 |
20110287239 | Multilayered Coating For Improved Erosion Resistance - An erosion resistant coating for a substrate includes two or more coating layers affixed to the substrate having an increasing modulus of elasticity and hardness from an innermost layer of the coating adjacent to the substrate to an outermost layer of the coating furthest from the substrate. A method of applying a coating system to a substrate includes applying a first layer of a high hardness and high modulus of elasticity material combined with an added metal to the substrate. A second layer of the high hardness and high modulus of elasticity material combined with the added metal is applied to the first layer, resulting in a coating system wherein the second layer has a modulus of elasticity and hardness greater than the modulus of elasticity and hardness of the first layer. | 11-24-2011 |
20110264310 | Method Of Determining A Maneuver Performed By An Aircraft - A method of determining a maneuver performed by an aircraft having sensors for monitoring motion data, the method including periodically sampling the sensors to electronically determine segments of motion data of the aircraft; aggregating sequences of the segments of the motion data; comparing the aggregated segments of motion data to models of particular maneuvers; and determining the maneuver performed by the aircraft. | 10-27-2011 |
20110260581 | Flexible Phased Array Sensor - A sensor includes a film, at least one piezoelectric strip disposed on the film, a first conductive line disposed on the film, the first conductive line electrically connected to a first portion of the at least one piezoelectric strip, a second conductive line disposed on the film, the second conductive line electrically connected to a second portion of the at least one piezoelectric strip, and a dampening member disposed on the at least one piezoelectric strip. | 10-27-2011 |
20110254706 | Methods and Systems Involving Viewing Angles in Aircraft Displays - A method and system for presenting environmental data including receiving environmental data from a sensor, processing the data to generate a graphical representation of the environment, wherein the view point of the graphical representation of the environment is a distance (d) and an angle (θ) relative to a point in an aircraft, and presenting the graphical representation of the environment to a user on a display. | 10-20-2011 |
20110211968 | ROTOR BLADE FOR A ROTARY-WING AIRCRAFT - A rotor blade for a rotary-wing aircraft includes a core member having a first end that extends to a second end, and a spar member positioned about the core member. The spar member includes a first end section that extends to a second end section. A tip core assembly is mounted at the second end section of the spar member. The tip core assembly is formed from a honeycombed material. The rotor blade also includes a rotor blade skin mounted about the spar member and the tip core assembly. | 09-01-2011 |
20110211953 | Concentric Rotor Control System - A rotor control system including a collective control rod positioned internal to a rotor shaft, the rotor shaft for imparting torque to rotor blades; and a cyclic control rod positioned internal to and concentric with the collective control rod. | 09-01-2011 |
20110206513 | Drive Mechanisms For Variable Diameter Rotor Systems - A rotor hub assembly includes a rotor hub for supporting a telescoping rotor blade having an outboard section; and a drive mechanism associated with the telescoping rotor blade, the drive mechanism including: a motor; a spool driven by the motor; and a strap wound on the spool, the strap coupled to the outboard section of the telescoping rotor blade. | 08-25-2011 |
20110195815 | PLANETARY REDUCTION GEARBOX - A gearbox assembly includes a yoke operably connectable to an input shaft and rotatable about a stationary gear located at a central axis. A planetary gear is rotatably located in the yoke and is meshable with the stationary gear such that rotation of the yoke about the stationary gear drives rotation of the planetary gear, via the mesh between the planetary gear and the stationary gear, about a pin axis. An intermediate gear is located substantially coaxially with the planetary gear and is operably connected to the planetary gear such that rotation of the planetary gear about the pin axis drives rotation of the intermediate gear about the pin axis. At least one output gear is located at the central axis and is operably meshed to the intermediate gear. | 08-11-2011 |
20110194935 | COUNTER ROTATING FACEGEAR GEARBOX - A gearbox assembly includes a first face gear driveable about a face gear axis in a first direction by at least one first pinion gear and a second face gear driveable about the face gear axis in a second direction opposite the first direction by at least one second pinion gear. A thrust bearing is located between the first face gear and the second face gear. The first face gear is configured to drive rotation of a first shaft in the first direction and the second face gear is configured to drive rotation of a second shaft in the second direction. Further disclosed is a power train for a rotary wing aircraft having a gearbox including a first face gear rotatable in a first direction and a second face gear rotatable in a second direction opposite the first direction. | 08-11-2011 |
20110164979 | MECHANICAL SYSTEM FOR HIGH ACCELERATION ENVIRONMENTS - A mechanical system for high acceleration loading includes a mechanical element configured for rotational movement in a high acceleration environment. The mechanical element possesses a first density. A lubricant having a second density is disposed about the mechanical element. The first and second densities are substantially identical such that the mechanical element is substantially neutrally buoyant in the lubricant. | 07-07-2011 |
20110164976 | ACTIVE ROTOR BLADE CONTROL EFFECTOR SYSTEM FOR A ROTARY-WING AIRCRAFT - A helicopter includes an airframe, and a rotor system mounted to the airframe. The rotor system includes a plurality of rotor blades. Each of the plurality of rotor blades includes a root portion that extends to a tip portion through an airfoil portion. The airfoil portion includes first and second surfaces. An effector is mounted within the airfoil portion of at least one of the plurality of rotor blades. The effector includes a first end portion that extends to a second end portion through an intermediate portion, and a flap arranged at the second end portion. The effector is selectively actuated to shift from a first, stowed, position wherein the flap is positioned within the at least one rotor blade to a second, deployed, position, wherein flap projects through at least one of the first and second surfaces of the at least one rotor blade. | 07-07-2011 |
20110150646 | CONTROL SYSTEM AND METHOD FOR ROTOR ASSEMBLY - A rotor assembly includes a rotor shaft rotatable about a rotor axis and a plurality of rotor blades operably connected to the rotor shaft. A rotor control assembly has a plurality of substantially concentric control tubes extending through the rotor shaft. Each control tube of the plurality of control tubes is operably connected to a rotor blade of the plurality of rotor blades such that movement of one or more of the control tubes of the plurality of control tubes along the rotor axis effects a pitch change in one or more rotor blades of the plurality of rotor blades. A method of controlling pitch of a plurality of rotor blades of a rotor assembly includes locating a plurality of concentric control tubes inside of a rotor shaft of the rotor assembly capable of changing a pitch of one or more of the rotor blades. | 06-23-2011 |
20110146375 | IMPACT TEST FIXTURE WITH SIMULATED CENTRIFUGAL FORCE - A test apparatus for a rotor blade of a rotor includes at least one guide rail located in proximity to the rotor blade and at least one bearing secured to the rotor blade radially outboard of the at least one guide rail. The at least one bearing is in operable communication with a radially outboard surface of the at least one guide rail to be translatable thereon. At least one force applicator is in operable communication with the at least one guide rail and is configured to exert a force radially outwardly on the at least one guide rail. The force is transferred to the rotor blade via the at least one bearing and simulates a centrifugal force on the rotor blade. Further disclosed is a method for securing a rotor blade of a rotor in a test fixture. | 06-23-2011 |
20110137494 | Systems and Methods for Velocity Profile Based Approach to Point Control - A method for velocity profile based approach to point control for an aircraft includes determining a distance from the aircraft to a target point; determining a velocity command based on the distance to the target point and a desired acceleration; and issuing the velocity command. A velocity profile based approach to point control module for an aircraft and a computer program product comprising a computer readable storage medium containing computer code that, when executed by a computer, implements a method for velocity profile based approach to point control are also provided. | 06-09-2011 |
20110112878 | Virtual Monitoring of Aircraft Fleet Loads - A computer-implemented method, system, and computer program product for virtual monitoring of aircraft fleet loads are provided. The method includes calculating virtual load data associated with an aircraft from a set of orthogonal waveforms. The method also includes calculating a set of coefficients as a function of parametric data and high frequency data associated with an aircraft. The method further includes storing the set of coefficients on the aircraft and transmitting the set of coefficients to a ground-based system configured to reproduce the virtual load data based on a copy of the set of orthogonal waveforms and the received set of coefficients in order to perform aircraft fleet management. | 05-12-2011 |
20110098967 | Method and System for Detecting Forces on Aircraft - A method for sensing a force applied to an aircraft includes receiving a derivative of the acceleration of a motion of a portion of the aircraft, determining whether the derivative of the acceleration of the motion of the portion of the aircraft exceeds a threshold, and outputting an indication that a force has been applied to the portion of the aircraft responsive to determining that the derivative of the acceleration of motion of the portion of the aircraft exceeds the threshold. | 04-28-2011 |
20100161244 | METHOD AND APPARATUS FOR MONITORING STRUCTURAL HEALTH - A method includes performing a first damage prediction with a computational model using at least data from a first multitude of damage sensors on a structure, performing a second damage prediction with the computational model using at least data from a second multitude of load sensors associated with the structure, and selectively performing a damage monitoring action in response to the first damage prediction and the second damage prediction to determine a structural health A system includes a computing device configured to perform a first damage prediction using at least data from a multitude of damage sensors on a structure, a second damage predication using at least data from a multitude of load sensors associated with the structure, so as to selectively perform a damage monitoring action in response to the first damage prediction and the second damage prediction to determine a structural health of the structure. | 06-24-2010 |
20090025362 | INFRARED SUPPRESSION SYSTEM WITH SPIRAL SEPTUM - An InfraRed Suppression System (IRSS) includes a double-walled exhaust duct and double walled septum. The double walled structure provides a flow path for secondary (non-exhaust gas) cooling air flow to slots along the surfaces exposed to exhaust gases. Exhaust gas flow past these slots draws cooling air across the duct and septum surfaces. This flow cools the surfaces close to the slots and mixes with exhaust gasses downstream to cool the exhaust plume. The septum in the shape of a helix rotating fully blocks line-of-sight to the turbine exit from the aft of the aircraft. The exhaust duct is intended to be shrouded by an aerodynamic fairing which provides an aerodynamic contour which minimizes aerodynamic impact on the aircraft. | 01-29-2009 |