Entries |
Document | Title | Date |
20080210809 | ELECTRICAL SYSTEM FOR UNMANNED VEHICLES - An electrical system for unmanned vehicles includes a first spine printed circuit board (PCB) having an electronic buss on or between layers of the first spine PCB for transmitting electronic signals to and between distal ends of the PCB. The spine PCB can be used as a portion of the structure of the unmanned vehicle or can be contained within an elongated structural spine, tube or spar of an unmanned vehicle thereby forming a structural part of the vehicle. | 09-04-2008 |
20080251631 | Umanned Helicopter - The invention relates to an unmanned helicopter comprising an internal combustion engine and an associated fuel tank. The unit ( | 10-16-2008 |
20090008497 | Rotary-wing miniature gyro helicopter - There is provided a gyro helicopter generally comprising a fuselage, a rotor mast extending upwardly from the top of the fuselage, a rotor adapted to autorotate when the gyro helicopter moves forward, and drive means mounted to the fuselage for driving the gyro helicopter in at least a forward direction and for causing the gyro helicopter to perform yawing motions. The rotor of the gyro helicopter includes a hub mounted to the rotor mast, at least two rotor arms extending radially from the hub, and at least two corresponding lifting blades, a leading edge of each of the lifting blades fixedly mounted to a corresponding one of the rotor arms. The rotor arms are adapted to twist in a first direction while an upward force is applied to the blades, raising the trailing edge of the blades above the plane of the rotor, and the rotor arms are adapted to twist in a second direction while a downward force is applied to the blades, the twisting in a second direction lowering the trailing edge of the blades below the plane of the rotor. | 01-08-2009 |
20090050733 | SIMPLE VTOL FLYING MACHINE - A compact and lightweight portable flyer. | 02-26-2009 |
20090159739 | HELICOPTER DRIP PAN - A drip pan apparatus for a “M” model BLACK HAWK® helicopter and the like includes an expanded corner structure for accommodating an access port also positioned further outwardly in the corner than in prior drip pan apparatuses, facilitating filter viewing while retaining peripheral o-ring seal. An expanded corner of the airframe skirt is accommodated by the expanded corresponding corner of a frame, which also defines a small radius internal curve. The removable pan has a small radius curve cooperating with the small radius curve of the frame and is sealed thereto by the peripheral o-ring seal sealing the entire pan to the frame. Physical access to the filter is enhanced. | 06-25-2009 |
20090189011 | Thrust Vectoring Exhaust Nozzle System for Helicopters - A thrust vectoring exhaust nozzle system for helicopters includes a vertical thrust vectoring nozzle positioned on the rear of the tail of the helicopter and a horizontal thrust vectoring nozzle positioned generally adjacent the vertical thrust vectoring nozzle, the vertical and horizontal thrust vectoring nozzles each connected to the exhaust output of the gas-turbine engine of the helicopter such that by adjusting and controlling the vertical and horizontal thrust vectoring nozzles to direct gas outflow in a selected direction, the exhaust outflow from the engine can be used to assist or modify the movement of the helicopter. | 07-30-2009 |
20090218439 | COVERT SENSOR EMPLACEMENT USING AUTOROTATIONAL DELIVERY MECHANISM - A method for emplacing sensors, comprising the steps of modifying an existing sensor to attach an autorotational mechanism and deploying said sensor by autorotational means. | 09-03-2009 |
20090236467 | Rotary Aircraft Download Alleviation Apparatus and Methods - Apparatus and methods for alleviating rotary aircraft downloads are disclosed. In one embodiment, a rotary aircraft includes an airframe assembly having a fuselage, at least one rotor assembly operatively coupled to the airframe assembly and configured to provide a downwash over at least a portion of the airframe assembly during operation of the at least one rotor assembly, and at least one download alleviation strake operatively coupled to the fuselage, each download alleviation strake extending at least partially along a length of the fuselage and being configured to reduce a downwash download during operation of the at least one rotor assembly. In some embodiments, the airframe assembly includes at least one fuel tank, and the at least one download alleviation strake is coupled to the at least one fuel tank. The download alleviation strake may be pivotably coupled to the at least one fuel tank. | 09-24-2009 |
20090250549 | Aircraft - An aircraft includes at least three drive units, each of which has a first rotor and a first, rotary speed-controlled electrical motor, suitable for driving the first rotor during operation of the aircraft. Each of the drive units has at least a second rotor and at least one second, rotary speed-controlled electrical motor, suitable for driving the second rotor during operation of the aircraft in a rotational direction that is opposite to the rotational direction of the first rotor of each drive unit. Autonomous means for controlling the location and position of the aircraft are also provided. | 10-08-2009 |
20100078516 | Faster Gyrodynes: Mach .88, or better - DARPA's Heliplane Program Manager, Don Woodbury indicated that they did not realize how much of a challenge 400 mph (cruise speed) was. The interviewer noted: “In their initial assessment of the hurdles posed by the Heliplane's requirements GBA considered, rotor head drag was believed to be the simplest to deal with. . . . opposite . . . true.” Faster Gyrodynes . . . allows planes to have both Lift/Drag ratios and speeds equal, or approaching, those of fixed wing planes while having the VTOL/hover capability of a gyrodyne. This is achieved by making the rotor and related components retractable which eliminates their drag. If retracted within the fuselage and the presence of door(s) does not add parasitic drag, the L/D ratio should be the same as an otherwise identical fixed wing craft. If an external pod is required its drag will reduce the L/D ratio to some extent, | 04-01-2010 |
20100181415 | ROTOR BLADE FOR A ROTARY WING AIRCRAFT - The invention relates to a rotor blade ( | 07-22-2010 |
20100230529 | CF BEARING WITH STEADY PITCHING MOMENT - A centrifugal force bearing having a means for providing a steady pitching moment is disclosed. The centrifugal force bearing may optionally comprise a coning means. A rotor system having the centrifugal force bearing is disclosed. A rotary-wing aircraft having the centrifugal force bearing is disclosed. | 09-16-2010 |
20100230530 | HELICOPTER - A helicopter having a drive in turn having an air intake conduit; a main rotor connected functionally to the drive; and a transmission interposed functionally between the main rotor and the drive and housed in a housing. The helicopter has at least one air intake in turn having: a first inlet connected fluidically to the intake conduit; at least one second inlet connected fluidically to the housing; and deflecting means interacting, in use, with an airflow to divide the airflow into a first and a second airflow. The air intake also has guide means for guiding the first airflow along a first path extending from the deflecting means to the first inlet, and for guiding the second airflow along a second path separate from the first path and extending from the deflecting means to the second inlet. | 09-16-2010 |
20100252673 | AERIAL DEVICE - The present invention consists of an aerial device, comprising a structure and a rotating element equipped with at least one blade, suitable for effecting a rotation relative to the structure around a rotation axis, wherein the device is equipped with means making it possible to cause the rotating element to rotate relative to the structure and wherein these means include a gas generator and a pipe that makes it possible to guide the gas towards an orifice at a distance from this rotation axis in order to cause the rotating elements to rotate by means of the gas ejected through the orifice, characterised in that the generator outlet and the pipe are part of the rotating elements and are suitable for rotating around the rotation axis relative to the structures. | 10-07-2010 |
20100270421 | LOCKNUT ASSEMBLY FOR A COAXIAL SHAFT - A locknut which defines a multiple of inner apertures about an inner diameter and a multiple of outer apertures about an outer diameter. | 10-28-2010 |
20110024553 | Bottom Blade Type Vehicle - A bottom blade type vehicle includes a fixed screw-pitch leaf horizontally mounted taking a center axis as the center; a power part mounted above the leaf; a controlling part mounted under the leaf; a first and a second fixing plates and a first and a second protecting plates being crossed each other in a cross-shape taking the controlling part as the center, one end of the first and the second fixing plates and the first and the second protecting plates connected to the controlling part and the other end of them connected to a round frame; a bridge plate vertically fixedly mounted under the round frame; and a first and a second adjusting controlled by a controlling device of the controlling part, wherein the first and the second adjusting blades are mounted on the first and the second protecting plates respectively. | 02-03-2011 |
20110031344 | HIGH VOLTAGE FLYING APPARATUS EMPLOYING MULTIPLE MOTORS - A flying apparatus having a frame configured to couple to a high voltage tether system, and at least one motor module mounted to the frame, the module including a holding structure attached to the frame, a rotating structure, including a rotor shaft, configured to rotate relative to the holding structure, a rotor attached to the rotor shaft and a plurality of motors attached to the holding structure, each including a drive shaft configured to engage with the rotor shaft, wherein the motors are configured to receive electrical energy from the tether system and drive the drive shafts to create a torque on the rotor shaft to thereby rotate the rotor and create lift to fly the apparatus from the ground to a desired position aloft while remaining coupled to the tether system. | 02-10-2011 |
20110036940 | MECHANICAL FLIGHT CONTROL AUXILIARY POWER ASSIST SYSTEM - A mechanical flight control system for a rotary-wing aircraft is disclosed. The flight control system comprises an upstream portion, a downstream portion, and an assembly for connecting the upstream portion to the downstream portion. The assembly may comprise dual concentric valve actuators and/or a variety of system load limiting features. | 02-17-2011 |
20110101156 | ROTATIONAL BOTTOM BLADE TYPE FLIGHT VEHICLE - Conventional bottom blade type flight vehicles have a complex structure and complex flying control operations in that several pairs of fixing plates, and forward/backward and left and right rotation adjustment blades are separately mounted and adjusted to remove the anti-torque of the flight vehicle caused by the rotation of the propellers and to fly the flight vehicle, so that the flight vehicles has difficulties in scouting and surveillance of an indoor area due to the heavy weight and the great volume. The flight vehicle of the disclosure continuously rotates in a state in which the anti-torque is not removed by one adjustment blade. The flight vehicle stops, ascends, descends, advances forward, backward, leftward, or rightward, or left or right rotates, performs flight in a narrow space, scouting and surveillance in an indoor area with a simple structure, simple control, light weight, and small size, and increases power efficiency. | 05-05-2011 |
20110155841 | VIBRATION DAMPER MECHANISM, AND A FLYING MACHINE INCLUDING A CARRIER STRUCTURE AND A ROTOR PROVIDED WITH SUCH A MECHANISM - The present invention provides a mechanism ( | 06-30-2011 |
20110272520 | ELECTRICAL DRIVEN FLYING SAUCER BASED ON MAGNETIC SUSPENSION - A magnetic suspension electric rotor flying saucer comprises: a saucer shell ( | 11-10-2011 |
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 |
20120025011 | AUTOGYRO WITH PRE-ROTATION - The disclosed apparatus is an autogyro which utilizes a variable pitch propeller and an electric motor coupled to the lift rotor. At takeoff, the engine may be started with the thrust propeller at zero pitch and the lift rotor-driving electric motor is engaged to spin the lift rotor to the desired take off speed while the autogyro is still stationary on the ground. The pitch of the pusher propeller is switched from zero pitch to the take off power pitch so as to obtain desired forward thrust while the power to the lift rotor is switched off as the autogyro begins to lift off the ground. In this way the takeoff run may be relatively short. Also, if sufficient head wind is present, vertical takeoff would be possible. | 02-02-2012 |
20120068003 | WIRELESS SENSOR FOR AN AIRCRAFT PROPULSION SYSTEM - A method is provided for wirelessly monitoring an aircraft propulsion system having a plurality of rotor blades, at least some of which rotor blades have an internal compartment. The method includes: providing a primary transducer having a primary coil, and one or more secondary transducers, each secondary transducer having a secondary coil connected to a sensor, wherein the secondary transducers are respectively disposed within the internal compartments; wirelessly powering the secondary transducers using a magnetic field generated by the primary transducer; monitoring at least one operational parameter from within each internal compartment using a respective sensor; and transmitting output signals from the secondary transducers to the primary transducer through the magnetic field, wherein the output signals are indicative of the monitored parameters. | 03-22-2012 |
20120091258 | SYSTEM, FLOATING UNIT AND METHOD FOR ELEVATING PAYLOADS - A method, system and a floating unit. The floating unit includes a propeller, a frame, a propeller motor that is configured to rotate the propeller about a first axis; wherein the propeller motor is coupled to the frame, a movable steering element; a controller, for controlling at least one of the propeller motor and the movable steering unit to affect at least one of a location and an orientation of the floating unit; and an interfacing module for coupling a payload to the floating unit and for receiving power from a connecting element that couples the floating unit to a ground unit; wherein the power received by the power interface is utilized to power the propeller motor and the controller. | 04-19-2012 |
20120104152 | AIRCRAFT PROVIDED WITH HOIST MEANS, AND AN ASSOCIATED METHOD - An aircraft ( | 05-03-2012 |
20120104153 | GYROPLANE PREROTATION BY COMPRESSED AIR - A rotorcraft is disclosed. The rotorcraft may include a rotor having at least one tip nozzle, a compressor having an outlet for compressed air, and a network of conduits connecting the outlet of the compressor with the tip nozzle. In operation, the compressor may deliver a flow of compressed air to the tip nozzle. As the flow of compressed air exits the at least one tip nozzle, it may cause rotation of the rotor. This rotation may prerotate the rotor and shorten the take off distance required by the rotorcraft. Take off of the rotorcraft may be accomplished without ever adding fuel to the flow of compressed air to the tip nozzle. | 05-03-2012 |
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 |
20120181378 | GYROPLANE - The invention relates to a gyroplane comprising a motor ( | 07-19-2012 |
20120298790 | Special Personal Electric Helicopter device with integral wind turbine recharging capability - Disclosed is a Personal Electric Helicopter device with an integral wind turbine recharging capability. The device is a relatively small, lighter weight powered aircraft capable of vertical take-offs and propulsion across various terrain at low altitudes. The device is uniquely capable of re-charging its power source by connection to an electrical grid or by using its uplift components as a wind turbine for re-charging. The preferred embodiment is comprised of a rechargeable uplift and propulsion power system with components and features; a frame structure to carry an operator and/or payload; a means to connect the structure to the power system; and a means to control the uplift and propulsion system wherein the vehicle may be used to elevate and propel a payload at low altitudes across various terrains and may be positioned to reverse power the wind turbine to recharge the batteries. | 11-29-2012 |
20120305698 | Method and Apparatus for Actively Manipulating Aerodynamic Surfaces - A method and apparatus is provided, including an actuator system that may be connected to a wing frame for controlling an active element. The actuator system may include sliding elements movable along an axis parallel to the span-wise axis of the wing. The sliding elements may be connected to fixed elements and a crank element, the crank element generally comprising a beam element and a cross-axis flexure pivot element. The beam element may be offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements. | 12-06-2012 |
20120312914 | HELICOPTER DRIP PAN APPARATUS AND METHOD OF MAKING AND USING SUCH AN APPARATUS - A drip pan apparatus for a helicopter includes a frame and a drip pan. The frame is secured to a skirt on the airframe of the helicopter. The apparatus includes a drip pan for cooperation with a frame to cover an access opening to a transmission. The drip pan includes a substantially planar member of a fiber-reinforced composite and has a seal surface that is configured to cooperate with a seal surface of the frame. A seal member may be disposed between the substantially planar member and the frame to form a fluid-tight seal. The fiber-reinforced composite may be a carbon fiber-reinforced composite. A method of making the drip pan apparatus includes placing a plurality of sheets of an uncured fiber-reinforced composite material on one another to form an uncured stack. The uncured stack is then cured. A frame and a drip pan may be cut from the cured stack. | 12-13-2012 |
20130032660 | LOADS INTERFACE, PARTICULARLY LOADS INTERFACE OF AN AIRCRAFT STRUCTURE AND APPLICATION OF SAID LOADS INTERFACE - A loads interface ( | 02-07-2013 |
20130032661 | LOADS INTERFACE, PARTICULARLY A LOADS INTERFACE FOR A PLUG TYPE AIRCRAFT DOOR - A loads interface ( | 02-07-2013 |
20130037652 | ROTORCRAFT, DYNAMIC, CG MANAGEMENT APPARATUS AND METHOD - An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. A bulkhead is positioned rearward from the cockpit and oriented perpendicular to a longitudinal axis of the airframe. A tailboom and engine are mounted to the airframe by means of the bulkhead having the engine mounted between the tailboom and a lower edge of the bulkhead. Landing gear may mount to the bulkhead proximate a lower edge thereof. Systems and methods redistribute fuel among laterally, vertically, and longitudinally opposed fuel tanks to maintain a center of gravity in a dynamically stable position. | 02-14-2013 |
20130062456 | Reconfigurable Rotor Blade - A reconfigurable rotor blade system includes an internal mass that is configured to translate in order to produce a spanwise torsional twist of the rotor blade. An actuator is configured to selectively translate the mass so as to relocate a center of mass of the rotor blade. The torsional twist is selectively produced during operation of the rotorcraft. | 03-14-2013 |
20130082136 | METHOD AND APPARATUS FOR ACTIVELY MANIPULATING AERODYNAMIC SURFACES - A method and apparatus is provided, including an actuator system that may be connected to a wing frame for controlling an active element. The actuator system may include sliding elements movable along an axis parallel to the span-wise axis of the wing. The sliding elements may be connected to fixed elements and a crank element, the crank element generally comprising a beam element and a pivot element. The beam element may be offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements. | 04-04-2013 |
20130105619 | CAMERA STABILIZATION MECHANISM | 05-02-2013 |
20130134253 | Power Rotor Drive for Slowed Rotor Winged Aircraft - A rotor aircraft has an engine having an output shaft. At least one propeller is driven by the engine to provide forward thrust to the aircraft. Wings provide lift while in forward flight. A rotor is driven by rotor drive mechanism, which selectively provides torque to the rotor drive shaft from the engine while in a first mode. The rotor drive mechanism selectively provides torque to the rotor drive shaft to rotate at a speed independent of a speed of the output shaft of the engine while in a second mode. In one embodiment, the rotor drive mechanism is a variable speed transmission powered by the engine. In another embodiment, the rotor drive mechanism is an electric motor. | 05-30-2013 |
20130134254 | UAV Fire-fighting System - An unmanned aerial vehicle (UAV) designed to extinguish fires from the air while remaining tethered to the ground via a tether system fashioned to provide the UAV with power and extinguishant. The UAV is preferably electrically powered and is stabilized in the air via a system of gyroscopes fashioned to work in concert with a series of electric motors capable of moving to counteract the opposing recoil force exhibited as water escapes the nozzle of the tether. A command and control unit on the ground supplies the UAV with electricity and water via the tether. The UAV is preferably stored within and launched from the command and control unit. Controls and sensor readings are communicated to a controller—be it autonomous or human—on the ground, preferably within or proximal to the command and control unit. | 05-30-2013 |
20130161444 | HIGH EFFICIENCY HUB FOR PRESSURE JET HELICOPTERS - The various implementations of the present invention provide a high efficiency “wye” rotor hub that is introduced into the airflow of the compressed air as the compressed air is delivered to the blades of the helicopter. The hub assembly has a plurality of hollow tubes that more efficiently guide the compressed air into the hollow blades, thereby improving the efficiency and performance of the engine. The hollow rotor tube hub insert looks much like a “ram's horn” where the flow area of the compressed air entering the hollow mast from the air compressor is diverted equally into a plurality of generally circular tubes, with each tube having a substantially equal cross-sectional diameter and area and where the number of circular tubes is equal to the number of rotor blades. | 06-27-2013 |
20130175384 | Bearing Restraint for Rotor Systems - According to one embodiment, a rotor system comprises a yoke, a grip, an elastomeric bearing, and a bearing restraint. The grip is positioned around a portion of the yoke and has both a closed end and an open end. The elastomeric bearing is coupled to the closed end of the grip and located between the closed end and the yoke. The bearing restraint is coupled to the grip between the yoke and the open end at a distance from the closed end such that the yoke contacts the bearing restraint when the rotor system is subject to a first centrifugal force but does not contact the bearing restraint when the rotor system is subject to a second centrifugal force greater than the first centrifugal force | 07-11-2013 |
20130206898 | Pilot Control System with Pendent Grip - According to one embodiment, a control assembly includes a post, a grip, and a shaft. The post has a top, a bottom, and a body joining the top to the bottom. The shaft havs a first end coupled proximate to the body below the top and a second end opposite the first end coupled to the grip. The shaft positions at least part of the grip directly over the top of the post. | 08-15-2013 |
20130334360 | CLUTCH WITH PRESSURE SUSTAINING SYSTEM - An assembly includes an output shaft, an input shaft with an internal reservoir, and a clutch. The clutch is adapted to selectively engage and couple the input shaft to the output shaft. The clutch has a pressure chamber that communicates with the reservoir of the input shaft. The reservoir has a sufficient volume to provide the pressure chamber with a fluid pressure adequate to maintain engagement of the clutch during an interruption of a fluid supply to the input shaft and clutch. | 12-19-2013 |
20140001307 | Aircraft Gearbox Lubrication System | 01-02-2014 |
20140021290 | Elastomeric Bearing Housing and Mating Grip for Helicopter Rotor System - According to one embodiment, a helicopter rotor system has a bearing disposed between the drive train and the rotor blade. The bearing comprises an elastomeric material, a housing member coupled to the elastomeric material, and an anti-rotation member coupled to the housing member opposite the elastomeric material. A bearing mount is coupled to the grip and comprises a first opening configured to receive the anti-rotation member of the bearing. The first opening is defined at least in part by a first surface that receives the anti-rotation member and prevents the anti-rotation member from completing a rotation within the first opening. | 01-23-2014 |
20140070047 | Multifunctional Structural Power and Lighting System - According to one embodiment, a structural electrical system includes an electrical power source operable to provide electrical current, a structural composite, and a plurality of output devices. The structural composite includes alternating layers of conductive layers and insulative layers. Each conductive layer is less than or equal to 500 nanometers thick and each conductive layer is in electrical communication with the electrical power source. The plurality of output devices are in electrical communication with each conductive layer and are operable to receive electrical current from the electrical power source through the conductive layers. | 03-13-2014 |
20140124614 | RADIO-CONTROLLED HELICOPTER - Described is a radio-controlled helicopter comprising a main body, a tail beam, connecting means operating between the main body and the tail beam for connecting the tail beam to the main body; the tail beam has a first end close to the main body and a second end away from the main body and it is defined by a tapered tubular member with a cross-section at the first end greater than the cross-section at the second end; the connecting means comprise an engagement member integral with the tail beam in the first end and a seat for the engagement member made in the main body, and fixing means operating between the engagement member and the main body at the seat. | 05-08-2014 |
20140145025 | Rotary Wing Aircraft Blade Tracking - A blade tracking system for a rotary wing aircraft includes a blade sensor mounted on a blade of the rotary wing aircraft, the blade sensor wirelessly transmitting blade data; a reference sensor mounted to the rotary wing aircraft, the blade driven by the rotor hub, the reference sensor transmitting reference data; and a processor receiving the blade data and the reference data, the processor determining at least one of lead-lag, flap and pitch of the blade in response to the blade data and the reference data. | 05-29-2014 |
20140151495 | Purebred and Hybrid Electric VTOL Tilt Rotor Aircraft - Electrically powered Vertical Takeoff and Landing (VTOL) aircraft are presented. Contemplated VTOL aircraft can include one or more electrical energy stores capable of delivering electrical power to one or more electric motors disposed within one or more rotor housings, where the motors can drive the rotors. The VTOL aircraft can also include one or more sustainer energy/power sources (e.g., batteries, engines, generators, fuel-cells, semi-cells, etc.) capable of driving the motors should the energy stores fail or deplete. Various VTOL configurations are presented including an all-battery purebred design, a light hybrid design, and a heavy hybrid design. The contemplated configurations address safety, noise, and outwash concerns to allow such designs to operate in built-up areas while retaining competitive performance relative to existing aircraft. | 06-05-2014 |
20140166804 | AIRCRAFT STABILIZATION SYSTEMS AND METHODS OF MODIFYING AN AIRCRAFT WITH THE SAME - A method of modifying a helicopter includes providing a tail boom of the helicopter and modifying a surface profile of the tail boom on at least a first side of the tail boom to improve flow attachment of air flowing over the first side of the modified tail boom during operation of the helicopter. The first side of the tail boom is located on an opposite side of the tail boom from a second side of the tail boom towards which a main rotor blade of the helicopter approaches during rotation. | 06-19-2014 |
20140231579 | RADIAL FLUID DEVICE WITH MULTI-HARMONIC OUTPUT - According to one embodiment, a radial fluid device comprises a cylinder block, first and second pluralities of pistons, a first cam disposed about the first plurality of radially extending cylinders, and a second cam disposed about the second plurality of radially extending cylinders. The second cam has at least one more lobe than the first cam. | 08-21-2014 |
20140246537 | Single-Gauge Monitoring of Multiple Components - According to one embodiment, a gauge display prioritization system comprises a priority engine and an output engine. The priority engine is operable to receive a measurement from a first sensor associated with a first aircraft component and a measurement from a second sensor associated with a second aircraft component, select a prioritization criterion based on the received measurements, and select one priority measurement from the received measurements based on the prioritization criterion. The output engine is operable to instruct a gauge disposed within a cockpit to display information representative of the one priority measurement to a pilot. | 09-04-2014 |
20140252157 | Aircraft with Protective Nanocoating - An aircraft component has an exterior surface and a protective nanocoating carried by the exterior surface. An aircraft has an engine, a fuselage, and a component having an exterior surface and a protective nano coating carried by the exterior surface. A method of protecting an aircraft component includes selecting at least one harmful environmental component and applying a protective nanocoating to the aircraft component, wherein the protective nanocoating is configured to protect the aircraft component from the selected harmful environmental component. | 09-11-2014 |
20140263819 | HELICOPTER DRIP PAN - A drip pan apparatus for use in a helicopter includes a drip pan and a frame having a plurality of frame sides and a plurality of frame corners that define an inwardly-facing peripheral surface. A first frame angle is formed between a first inwardly-facing surface and a second inwardly-facing surface. The first frame angle is an acute angle. The drip pan has an outwardly-facing peripheral surface. The outwardly-facing peripheral surface defines a plurality of sides, including a first side and a second side, to cooperate with the inwardly-facing peripheral surface of the frame. A first angle is formed between the first side and the second side. The first angle is an acute angle. A method of installing a drip pan includes modifying at least a portion of a skirt on the helicopter and then securing the frame to one or both of the modified skirt and the helicopter structure. | 09-18-2014 |
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 |
20140299707 | Preventing Condensation on Environmental Control System Fluid Lines - According to one embodiment, a condensation control system features a dew point analyzer, a fluid system, and a condensation control engine. The dew point analyzer provides a dew point temperature measurement of environmental conditions outside a fluid line having a refrigerant flowing therein. The fluid system provides a flow of insulating fluid to an insulation chamber at least partially separating the fluid line from environmental conditions outside the fluid line. The condensation control engine instructs the fluid system to provide the flow of insulating fluid to the insulation chamber at a temperature such that the temperature of the insulating fluid exiting the insulation chamber is greater than the dew point temperature measurement. | 10-09-2014 |
20140312166 | HELICOPTER AND AIRCRAFT POWER DEVICE - A helicopter and aircraft power device has a plurality of fluid inlets on a windward side of a blade housing and a plurality of fluid outlets on a leeward side in a manner that the fluid inlets communicate with the fluid outlets. The path where the fluid flows in the lengthwise direction on the windward side of the blade housing is far greater than the path where the fluid flows in the widthwise direction on the leeward side of the blade housing, generating a very large pressure difference between the leeward side and the windward side. The action of the centrifugal force and a suction force from a suction motor significantly increase the flowing speed on the windward side of the blade and in the fluid passage, generating bigger pressure difference on either sides of the propeller and thus forming more powerful lift force and driving force. | 10-23-2014 |
20150014476 | FLEXBEAM ROTOR ATTACHMENT TO ROTOR BLADE - A rotor blade assembly includes a flex-beam member and a torque tube surrounding the flex-beam member and extending partially along a rotor blade assembly length. A rotor blade surrounds the flex beam member and extends from the torque tube to a blade tip. A connecting pin assembly secures the rotor blade and the torque tube at the flex-beam member. The connecting pin assembly includes a first pin member having a first shaft extending at least partially into the rotor blade assembly through the rotor blade from a first rotor blade side and a second pin member located at a second rotor blade side. A clamping load between the first pin member and the second pin member secures the rotor blade and torque tube to the flex-beam member. | 01-15-2015 |
20150014477 | VIBRATION REDUCING APPARATUS - A compact vibration reducing apparatus includes a dynamic mass; elastic member which apply elastic force to the dynamic mass so that the dynamic mass vibrates in a parallel to a vibration damping direction; a control mass; an actuator which move in parallel to a length change direction; and a motion direction converting mechanism which moves the control mass to the dynamic mass so that the control mass moves in a vibration damping direction to the dynamic mass through the operation of the actuator. The actuator is supported by the dynamic mass so that the operation direction of the actuator is not parallel to the vibration damping direction. | 01-15-2015 |
20150041583 | INFLATABLE WING FOR ROTARY-WING AIRCRAFT - Provided is an inflatable wing for a rotary-wing aircraft capable of obtaining auxiliary lift by inflating the inflatable wing equipped on the fuselage when a main rotor is in non-powered rotation state by not providing power for rotating the main rotor due to causes such as an engine failure in a conventional type of rotary-wing aircraft having a single engine, thereby providing a safer emergency landing. | 02-12-2015 |
20150053814 | Rotor System with Torque-Splitter Assembly - According to one embodiment, a rotor head includes a yoke, a torque-splitter assembly, and a joint assembly. The torque-splitter assembly includes a spine assembly, a first trunion, and a second trunion. The spline assembly is configured to receive the drive shaft through a first opening. The spline assembly has a first plurality of outer splines oriented in a first direction and a second plurality of outer splines oriented in a second direction different from the first direction. The first trunion is disposed about the first plurality of outer splines. The second trunion is disposed about the second plurality of outer splines. | 02-26-2015 |
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 |
20150060595 | system and method for reducing the transmission of vibration from a first vibrating body to a second body - A system for reducing the transmission of vibration from a first vibrating body to a second body, the system having a first part connected to the first vibrating body, a second part connected to the second body and an electro-hydrostatic actuator connected to the first and second parts, the electro-hydrostatic actuator being operable to continuously oscillate the first and second parts | 03-05-2015 |
20150069173 | ANTIVIBRATION SUSPENSION DEVICE FOR A MECHANICAL ELEMENT, AND AN AIRCRAFT - A suspension device ( | 03-12-2015 |
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 |
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 |
20150122939 | ROTORCRAFT HAVING FUEL TANKS MOUNTED IN SUSPENSION UNDER A LOAD-BEARING MIDDLE FLOOR OF THE FUSELAGE OF THE ROTORCRAFT - A rotorcraft ( | 05-07-2015 |
20150122940 | ROTORCRAFT FUSELAGE STRUCTURE INCORPORATING A LOAD-BEARING MIDDLE FLOOR INTERPOSED BETWEEN A CABIN SPACE AND AN EQUIPMENT SPACE - A fuselage structure for a rotorcraft ( | 05-07-2015 |
20150307187 | ELASTOMERIC BEARING HAVING TAPERED LAYERS - A rotor hub for an aircraft that includes a yoke, a rotor mast; and a hub spring assembly. The hub spring assembly includes an upper outer member; an upper inner member; and an upper spring member having a plurality of elastomeric layers and shim layers sandwiched between the upper outer member and the upper inner member, the shim layers being tapered such that a thickness of each shim layer is smaller at a side portion as compared to the thickness of the shim at a center portion. | 10-29-2015 |
20150322287 | LIGHT-CURABLE EPOXY COATING - According to one embodiment, a rotorcraft includes a body, a rotor system with a blade, and a component. The rotor system is coupled to the body of the rotorcraft. The component includes a metal portion, a temperature-sensitive portion adjoined to the metal portion, and a light-cured epoxy layer on the surface of the metal portion. | 11-12-2015 |
20150344132 | HELICOPTER - Helicopter with tip-jet rotor drive comprising at least two rotor blades attached to a central shaft, where each rotor blade comprises means for guiding a fluid from a location close to said central shaft towards a tip of the rotor blade. At the area of said tip there is an outlet arranged so that by each of the rotor blades a jet stream is generated. The helicopter comprises a compressor for releasing compressed air. This compressor is co-axially arranged with respect to said central shaft above the rotor blades. The compressor is connected to the rotor blades to feed compressed air into the rotor blades. A piping system is provided for feeding fuel into the rotor blades. Each rotor blade comprises a combustion zone and means for bringing the fuel and compressed air together so that a combustion process is maintained which produces the jet streams. | 12-03-2015 |
20150353191 | SYSTEMS AND METHODS FOR IMPLEMENTING DIRECTIONAL FORCE WEIGHTING WITH CIRCULAR FORCE GENERATORS - Systems, methods, and computer program products for directional force weighting of an active vibration control system involve arranging a plurality of force generators in an array, identifying individual component forces corresponding to force outputs of each of the plurality of force generators, determining a combination of the individual component forces that will produce a desired total force vector, and adjusting the outputs of each of the plurality of force generators such that the combination of the individual component forces are at least substantially similar to the desired force vector. | 12-10-2015 |
20150360777 | Multi-Task Frisbee-Umbrella - The present invention discloses an unmanned aerial vehicle capable of transforming its shape, comprising
| 12-17-2015 |
20150360778 | ROTORCRAFT WITH INTEGRATED LIGHT PIPE SUPPORT MEMBERS - A radio controlled model rotorcraft implemented with features improving ease of flight and flight performance by increasing structural stability, increasing rotorcraft visibility and orientation awareness through the use of multifunctioning, configurable, and aesthetically pleasing components, while also increasing resistance to damage from crashes through use of impact and vibration absorbing components. | 12-17-2015 |
20150367934 | REACTION DRIVE HELICOPTER WITH CIRCULATION CONTROL - A rotor blade for a reaction drive type helicopter is provided. The rotor blade includes a main duct extending from a proximal end, couplable to and for fluid communication with a rotor hub, to a distal end for ducting a first air/gas stream from the rotor hub to the distal end. A nozzle is attached to an outlet of the main duct at the distal end for receiving the first air/gas stream from the main duct and releasing the first air/gas stream to propel the rotor blade. A circulation control is carried at a trailing edge of the blade. A trailing edge duct is carried intermediate the trailing edge and the main duct and is in fluid communication with the main duct by a partition with a plurality of orifices formed therein to bleed air from the main duct and generate a second air/gas stream therein with a pressure less than the pressure of the first air/gas stream. The trailing edge duct supplies the second air/gas stream to the circulation control. | 12-24-2015 |
20160001881 | MISSION-ADAPTIVE ROTOR BLADE WITH CIRCULATION CONTROL - A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a plurality of blades defining ducts along the length thereof and vents in fluid communication with the ducts. Flow from through the vents may be controlled by valves with piezoelectric actuators. The valves may be adjusted to achieve a lift profile suited for an operational mode such as vertical, autorotative, or unloaded flight. The lift profile may vary along the length of the blade and may vary cyclically with rotation of the blade. The lift profile may be chosen to approximate a figure of merit for the rotor suitable for a given operational mode. | 01-07-2016 |
20160052644 | UNMANNED AERIAL VEHICLE HAVING AN ONBOARD CLEANING DEVICE - Described embodiments include an unmanned aerial vehicle and a method. The unmanned aerial vehicle includes an airframe, and a rotary wing system coupled with the airframe and configured to aerodynamically lift the vehicle in the air. The unmanned aerial vehicle includes a flight controller configured to control a movement of the vehicle while airborne. The unmanned aerial vehicle includes a cleansing controller configured to manage removal by an onboard cleaning device of a surface contamination from a selected portion of a surface of an external object. The unmanned aerial vehicle includes the onboard cleaning device. | 02-25-2016 |
20160054350 | ROTORCRAFT FLIGHT PARAMETER ESTIMATION - An aircraft is provided and includes an airframe. The airframe includes first and second rotor apparatuses at upper and tail portions of the aircraft, respectively, to provide for control and navigational drive. The aircraft further includes a stabilizer component disposed at the tail portion in a position displaced from downwash of the first and second rotor apparatuses at airspeed ranges and a control system configured to apply a dither actuation signal to the stabilizer component at the airspeed ranges by which an aircraft response to a stabilizer component input is measurable for airspeed estimation purposes. | 02-25-2016 |
20160059960 | SEMI-AUTOMATIC COLLECTIVE PITCH MECHANISM FOR A ROTORCRAFT - A rotorcraft rotor head has: (i) two or more rotor blades attached to rotate about a rotor axis, and pivot through a flapping and/or teetering hinge, and having a pitch angle; (ii) pitch angle changing means for collectively changing said pitch angle; (iii) centrifugal pitch stop mechanism having an activation point and comprising one or more centrifugal plates; and (iv) control means for providing a control input to said pitch angle changing means; wherein said centrifugal pitch stop mechanism is configured to attain an activated state and to interact with said pitch angle changing means; wherein said activated state is attained when the rotational speed of said rotor blades is greater than said activation point and when a control input is provided by said control means; and wherein said activation point is less than the minimum rotational speed of the rotor blades that is required for flying the rotorcraft. | 03-03-2016 |
20160076629 | VARIABLE SPEED AIRCRAFT TRANSMISSION - A variable state planetary shifting transmission can include an input shaft, an output shaft; and a planetary system having a sun gear associated with the input shaft, a planetary carrier, and a ring gear associated with a ring housing. The transmission can include an overrunning clutch operably coupled to the planetary carrier. The transmission can include a clutch assembly coupled to the planetary carrier. The transmission is capable of changing the speed ratio between the input shaft and the output shaft by selective engagement of the clutch assembly against the ring gear which can cause either the freeing or locking of the planetary carrier by the overrunning clutch. | 03-17-2016 |
20160090174 | REACTION DRIVE BLADE TIP WITH TURNING VANES - A rotor blade for a reaction drive type helicopter includes a proximal end couplable to a rotor hub and a distal end terminating in a blade tip. A hollow passage extends from the proximal end to the distal end for ducting air/gasses from the rotor hub to the blade tip. The hollow passage terminates at the blade tip in a duct having an inlet and an outlet. The duct has a horizontal 90-degree bend intermediate the inlet and the outlet, and a plurality of vanes positioned in a spaced apart row within the duct intermediate the inlet and the outlet at the 90 degree bend. Each vane of the plurality of vanes has an inner curved surface and an outer curved surface parallel to the inner curved surface. | 03-31-2016 |
20160101854 | Gyroplane - The present invention relates to a gyroplane comprising rotating wings with hydraulically-operated fan propellers. The rotating wing ( | 04-14-2016 |
20160152335 | INVERTIBLE AIRCRAFT | 06-02-2016 |
20160152342 | TORQUE SPLIT GEARBOX FOR ROTARY WING AIRCRAFT | 06-02-2016 |
20160159991 | Nanolevel Dispersion of Nanoparticles in Hydrophobic Materials - According to one embodiment, a method of dispersing nanoparticles into a destination material includes providing a plurality of nanoparticles suspended in a carrier, adding a solvent to the plurality of nanoparticles suspended in a carrier, removing at least some of the carrier to yield the plurality of nanoparticles suspended in the solvent, mixing the nanoparticles suspended in the solvent with a destination material, and removing at least some of the solvent from the mixture of nanoparticles suspended in the solvent and the destination material. | 06-09-2016 |
20160176521 | FLEXBEAM ROTOR ATTACHMENT TO ROTOR BLADE | 06-23-2016 |
20160185436 | Skin Impact Snubber - In some embodiments, an aircraft includes a structural assembly, a skin, and a snubber. The structural assembly comprises a first rigid element and a second rigid element. The first and second rigid elements are separated from each over by a void. The skin is disposed proximate to the structural assembly and adjacent to the void such that the skin would deflect into the void in response to an impact force received by the skin. The snubber is disposed in the void between the first and second rigid elements and positioned such that, when the skin deflects in response to the impact force, the skin contacts the snubber and the snubber reduces further deflection of the skin into the void. | 06-30-2016 |
20160252051 | BUBBLE COLLECTOR FOR SUCTION FUEL SYSTEM | 09-01-2016 |