Gulfstream Aerospace Corporation Patent applications |
Patent application number | Title | Published |
20160123763 | METHODS AND SYSTEMS FOR DISPLAYING FLIGHT INFORMATION - Avionics systems, controllers, and methods are provided. An avionics system includes a display and a controller. The controller is communicatively coupled with the display. The controller is configured to generate a flight clearance portion of the image including flight clearance information and to generate a flight progress portion of the image including flight progress information. | 05-05-2016 |
20150353204 | DISPLAY SYSTEM FOR USE IN A FLIGHT DECK OF AN AIRCRAFT - A display system for use in a flight deck of an aircraft is disclosed herein. The flight deck has an instrument panel. The display system includes, but is not limited to, a display screen that is adapted for mounting to the instrument panel and that is configured to extend along substantially an entire lateral length of the instrument panel without any discontinuity of display capability. The display system includes, but is not limited to, a plurality of image sources associated with the display screen. The plurality of image sources is configured to cause a plurality of images to appear on the display screen. | 12-10-2015 |
20150311841 | APPARATUS AND SYSTEMS FOR ENGINE AND GENERATOR CONTROL WITHIN AN AIRCRAFT - A system is provided for engine and generator control. The system includes a compound AC generator, a generator control unit (GCU) module and an engine electronic controller (EEC) module. The compound AC generator includes a shaft, and a permanent magnet generator (PMG) configured to be driven by the shaft to generate an AC power signal. The GCU module is configured to control the compound AC generator. The PMG is coupled to the GCU module and the EEC module such that it is configured to simultaneously supply the AC power signal to the GCU module and to the EEC module. | 10-29-2015 |
20150274278 | OVER-FRAME BLANKET ASSEMBLIES AND METHODS OF INSTALLATION IN FUSELAGE ASSEMBLIES - Fuselage assemblies, over-frame blanket assemblies, and methods of installing over-frame blanket assemblies are provided. A fuselage assembly for an aircraft includes a fuselage skin, a cabin liner, and an over-frame blanket assembly. The cabin liner has an outer side facing the fuselage skin. The over-frame blanket assembly is disposed between the fuselage skin and the cabin liner and has a first blanket piece. The first blanket piece includes a first sound barrier layer that defines a first outer surface of the over-frame blanket assembly and a first sound absorbing layer that defines a second outer surface of the over-frame blanket assembly facing the fuselage skin. A method of installing the over-frame blanket assembly includes positioning the first blanket piece in an orientation such that the first sound barrier layer is directly adjacent the cabin liner. | 10-01-2015 |
20150258763 | COMPONENTS MADE FROM PANELS AND METHODS OF PRODUCING THE SAME - Methods for producing panels and components made from panels are provided. A method of producing a panel includes positioning an expandable film between a first and second layer, where the first and second layer include a fiber and a resin. The expandable film is expanded such that a distance between the first and second layers increases as the expandable film expands. Expansion of the expandable film is terminated when a panel thickness is within 1% of a panel thickness specification, and a polymer in the expandable film is crosslinked while the panel thickness is within 1% of the panel thickness specification. | 09-17-2015 |
20150251750 | NOSE LANDING GEAR ARRANGEMENTS AND METHODS FOR MAKING THE SAME - Nose landing gear arrangements including a folding follow-up door for reducing airflow noise for aircrafts, aircrafts including such nose landing gear arrangements, and methods for making such nose landing gear arrangements are provided herein. In one example, a nose landing gear arrangement includes a wheel assembly and a main strut. The main strut is operatively coupled to the wheel assembly and is configured to extend outside of the fuselage substantially along a generally vertical plane. A folding follow-up door is pivotally coupled to the main strut and extends to the fuselage. The folding follow-up door includes a first door section and a second door section that extend outwardly in directions away from each other to define an unfolded position. The folding follow-up door is foldable to move the first and second door sections towards each other about the generally vertical plane to define a folded position | 09-10-2015 |
20150246718 | METHODS FOR MANUFACTURING AN I-STRINGER OF AN AIRCRAFT AND DEVICES FOR USE IN SUCH METHODS - Methods for manufacturing a reinforced composite structure for an aircraft and devices used in such methods are provided. A method includes advancing a composite material layout through a cap-forming device. The advancing results in a preformed cap section, a first length of the layout and a second length of the layout. The layout is removed from the cap-forming device and the preformed cap section of the layout is arranged within a cavity of a flexible mandrel with a foot portion of the first length and a foot portion of the second length remaining outside the cavity of the flexible mandrel. The foot portion of the first length and the foot portion of the second length contact a skin structure. The layout is heated and pressurized using the flexible mandrel to cure the layout and form the reinforced composite structure affixed to the skin structure. | 09-03-2015 |
20150206438 | AIRCRAFT TOW OBSTACLE ALERTING AND INDICATION & METHOD FOR RECORDING AND NOTIFICATION OF PARKED AIRCRAFT DAMAGE - The disclosed embodiments relate to methods and systems for avoiding a collision between an aircraft and an obstacle when the aircraft is being moved on a ground surface via a ground vehicle. When a processor onboard the aircraft determines that the obstacle is located in proximity to the aircraft, the processor generates a warning generator signal, which causes an apparatus to communicate a warning signal that is perceptible to an operator of the ground vehicle to warn the operator of the obstacle. | 07-23-2015 |
20150120090 | METHODS AND SYSTEMS FOR DISPLAYING AIRCRAFT INFORMATION - A method and an instrumentation system for an aircraft are provided. The method of presenting aircraft information includes activating a master indicator in response to a trigger event associated with operation of the aircraft, receiving a user input associated with the master indicator, and displaying information associated with the trigger event in response to receiving the user input associated with the master indicator. The instrumentation system performs the operations of the method. | 04-30-2015 |
20150106005 | METHODS AND SYSTEMS FOR AVOIDING A COLLISION BETWEEN AN AIRCRAFT ON A GROUND SURFACE AND AN OBSTACLE - The disclosed embodiments relate to methods and systems for avoiding a collision between an aircraft on the ground and an obstacle. The method includes receiving a direction signal from a sensor indicating the forward direction of the aircraft and receiving a video image from a camera representing a field of view from a wingtip of the aircraft. Using this information, a processor determines a predicted path through which the wingtip of the aircraft will travel based upon the direction signal. The video image is displayed together with an overlay representing the predicted path within the field of view. In this way, the overlay provides information to assist in preventing the aircraft from colliding with obstacles in the field of view. | 04-16-2015 |
20150037092 | WEB COMPONENT AND METHOD OF MAKING A WEB COMPONENT - A web component suitable for use with a snap-fit assembly is disclosed herein. The web component includes, but is not limited to, a sheet metal member that has a periphery and a first side and a second side. The sheet metal member also includes a plurality of protrusions that extend from a first surface of the first side and from a second surface of the second side. The plurality of protrusions are disposed proximate a portion of the periphery and are configured to engage a female receiver associated with the snap-fit assembly. | 02-05-2015 |
20150029046 | METHODS AND SYSTEMS FOR DISPLAYING BACKUP AIRSPEED OF AN AIRCRAFT - The disclosed embodiments relate to an aircraft that includes system for selecting an airspeed reference that is displayed within a cockpit of an aircraft. The system includes a processor and a display located in the cockpit. The processor is configured to determine whether primary airspeed is valid or invalid, and, to select a backup airspeed as the airspeed reference that is output to the display when it is determined that the primary airspeed is invalid. The display is configured to display the backup airspeed as the airspeed reference. The backup airspeed is generated based on Global Position System (GPS) information that is received by the aircraft. | 01-29-2015 |
20140375478 | TAKEOFF RUNWAY MONITOR - Disclosed is a runway alerting method and system for an aircraft during a take-off maneuver. The method includes determining stopping positions for the aircraft along the runway using aircraft energy state, deceleration and braking information and displaying the stopping positions on a display. | 12-25-2014 |
20140333510 | OMNIDIRECTIONAL HUD - Systems and aircraft are provided. The systems and aircraft include a controller, a projection surface, and at least one pair of active shutter 3-D glasses. The 3-D projector is configured to project a first 3-D HUD layout onto a projection surface. The projection surface is configured for displaying the 3-D HUD layout. The controller is operatively coupled with the 3-D projector and is configured to control the projector to project the 3-D HUD layout onto the projection surface. The first pair of active shutter 3-D glasses is configured to synchronize with the 3-D projector to present the first 3-D HUD layout to a first user. | 11-13-2014 |
20140327190 | VACUUM BAG MOLDING ASSEMBLY AND METHODS - An assembly for vacuum bag molding includes a mold for receiving a workpiece. An edge breather comprising a plurality of braided polymer threads is disposed about a periphery of the workpiece. A vacuum bag film is disposed over the workpiece and the edge breather. A seal seals the vacuum bag film to the mold and a passageway in fluidic communication with the edge breather. | 11-06-2014 |
20140309820 | METHODS AND SYSTEMS FOR REQUESTING AND RETRIEVING AIRCRAFT DATA DURING FLIGHT OF AN AIRCRAFT - The disclosed embodiments relate to methods for requesting and retrieving aircraft data during flight of an aircraft. This aircraft data can be used to perform additional monitoring of aircraft sub-systems to detect an abnormal condition, and/or to identify one or more sources that are causing the abnormal condition. In one embodiment, aircraft data for one or more relevant parameters can be requested from the ground, measured on-board the aircraft, and stored in a data file that is then communicated back to personnel on the ground. The real-time aircraft data for one or more relevant parameters can then be analyzed to identify the one or more sources that are causing the abnormal condition. | 10-16-2014 |
20140306862 | DISPLAY SYSTEM AND METHOD FOR DISPLAYING INFORMATION - A display system is disclosed herein. The display system includes, but is not limited to, a rear projection screen. The display system further includes, but is not limited to, a first projector arranged to project a first image on the rear projection screen. The display system further includes a second projector arranged to project a second image on the rear projection screen. The display system still further includes a processor that is operatively coupled with the first projector and the second projector. The processor is configured to control the first projector to project the first image and to control the second projector to project the second image, and is further configured to align the second image with the first image in an overlaying manner so as to create the appearance of a single image, a portion of the second image being substantially identical to a portion of the first image. | 10-16-2014 |
20140306058 | Supersonic Aircraft with Spike for Controlling and Reducing Sonic Boom - Method and arrangement for reducing the effects of a some boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region there between and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle. | 10-16-2014 |
20140272312 | AIRCRAFT COMPONENT AND METHOD OF MAKING AN AIRCRAFT COMPONENT - An aircraft component includes, but is not limited to, a first panel including a first channel and a second panel including a second channel. The second panel is disposed such that the second channel is aligned with the first channel. The aircraft component further includes, but is not limited to, a web section that disposed adjacent the first and second panels. The web section includes a first engagement portion engaged with the first channel and a second engagement portion engaged with the second channel. The aircraft component further includes, but is not limited to an adhesive that is disposed between the first engagement portion and the first channel and between the second engagement portion and the second channel. The first panel and the second panel are joined together by cooperation of the web section and the adhesive. | 09-18-2014 |
20140257602 | METHODS AND SYSTEMS FOR INSTRUCTING AN AIRCRAFT TO PERFORM A GO-AROUND MANEUVER - Method, and apparatus, and computer readable medium embodying the computer program product are provided for instructing a pilot of an aircraft to go-around and make another approach and landing attempt. During an approach maneuver, it is determined whether an operational parameter of the aircraft exceeds a threshold and whether the aircraft has reached a decision height altitude. A go-around instruction to the pilot when the aircraft has reached the decision height altitude and the operational parameter exceeds the threshold. | 09-11-2014 |
20140257601 | RUNWAY OVERRUN MONITOR - Disclosed is a runway alerting method and system for a landing an aircraft. The method includes determining stopping positions for the aircraft along the runway using aircraft energy state, deceleration and braking information and displaying the stopping positions on a display. A system is provided that includes a first apparatus that is configured to determine an aircraft speed relative to the ground, a second apparatus that is configured to determine the aircraft's position, and a third apparatus that can provide information about the runway of intended landing. A flight system coupled to the first and second apparatus is configured to determine a minimum and corporate stopping position for the aircraft using the aircraft speed and the position relative to the runway. The minimum and corporation stopping positions are presented to the aircraft pilot on a display to as assist the pilot in safely landing the aircraft. | 09-11-2014 |
20140216845 | THERMAL-ACOUSTIC SECTIONS FOR AN AIRCRAFT - Embodiments of thermal-acoustic sections for an aircraft for reducing noise along an acoustic path produced from an acoustic source are provided herein. The thermal-acoustic section comprises a first porous layer having a first characteristic acoustic impedance. A second porous layer is disposed adjacent to the first porous layer and has a second characteristic acoustic impedance that is greater than the first characteristic acoustic impedance. The thermal-acoustic section is configured to be positioned along the acoustic path such that at least a portion of the noise from the acoustic source is directed through the first porous layer to the second porous layer to promote absorption of the noise. | 08-07-2014 |
20140214266 | ADAPTIVE OSCILLATORY FAULT MONITORING - Systems, media, and methods are provided for oscillation monitoring. An aircraft system includes a first oscillation monitoring module and a second oscillation monitoring module. The first oscillation monitoring module is configured to select first oscillating portions of an input signal, generate a frequency signal that indicates a frequency of the first oscillating portions, and generate a first failure signal in response to the frequency of the first oscillating portions exceeding first oscillatory fault detection requirements for the input signal. The second oscillation monitoring module is configured to select second oscillating portions of the input signal based on the frequency signal generated by the first oscillation monitoring module and to generate a second failure signal in response to a frequency of the second oscillating portions exceeding second oscillatory fault detection requirements for the input signal. | 07-31-2014 |
20140209737 | WING FLAPS FOR AIRCRAFT AND METHODS FOR MAKING THE SAME - Flaps for operatively coupling to wing main elements of aircraft, aircraft including such flaps and methods for making such flaps are provided herein. In one example, a flap for operatively coupling to a wing main element of an aircraft comprises an outer flap section that has a side edge portion. The side edge portion at least partially surrounds a flap side-edge cavity. A porous cavity-filler insert is positioned in the flap side-edge cavity. | 07-31-2014 |
20140131514 | NOSE LANDING GEAR ARRANGEMENT FOR AIRCRAFT AND METHOD OF ASSEMBLY - A nose landing gear arrangement for an aircraft and a method of assembling the nose landing gear arrangement are disclosed herein. The nose landing gear arrangement includes, but is not limited to, a wheel assembly, a shock strut extending upwards from the wheel assembly towards a fuselage of the aircraft, and a torque arm assembly coupled to the wheel assembly and to the shock strut. The torque arm assembly is configured to transmit torque to the wheel assembly. The torque arm assembly is disposed forward of the shock strut with respect to a direction of travel of the aircraft. | 05-15-2014 |
20140118349 | SYSTEMS AND METHODS FOR PRESENTING VEHICLE COMPONENT INFORMATION - A system and method for presenting vehicle component information includes storing voxel data in a computerized database. The voxel data represents a plurality of voxels spatially arranged to encompass a shape representing at least part of a vehicle. A plurality of component records is stored in the database, wherein each component record corresponds to a component of the vehicle. Each component record is associated with voxel data representing at least one voxel. A graphical representation of at least one of the components is displayed on a display. | 05-01-2014 |
20140095012 | SYSTEMS AND METHODS FOR PROVIDING A VEHICLE CHECKLIST - A system for providing a checklist to an operator of a vehicle includes, but is not limited to, a processor in communication with a display. Operation of at least one component of the vehicle is sensed and provided to the processor. The processor is configured to generate a checklist based at least in part on the operation of the at least one component of the vehicle. The checklist is then displayed on a display for use by the operator of the vehicles. | 04-03-2014 |
20130234867 | METHOD AND SYSTEM FOR DISPLAYING INFORMATION - A display system for an aircraft includes a controller in communication with a display. The controller receives a category associated with a phase of flight of the aircraft. Information related to operation of the aircraft and associated with the received category is displayed on the display. | 09-12-2013 |
20130209746 | REINFORCED COMPOSITE STRUCTURES FOR AIRCRAFTS AND METHODS FOR MAKING THE SAME - Embodiments of reinforced composite structures for aircrafts and methods for making such reinforced composite structures are provided herein. A reinforced composite structure for an aircraft comprises a fiber reinforced composite stringer. The fiber reinforced composite stringer comprises a beam body portion and a runout portion that extends from the beam body portion in a first direction. The beam body and runout portions are defined by projection of a variable I-shaped cross-section in the first direction along at least a portion of an entire combined length of the beam body and runout portions. The variable I-shaped cross-section has a cap section, a foot section, and a web section that extends between the cap and foot sections. The variable I-shaped cross-section is configured such that a height of the web section tapers in the first direction along at least a portion of an entire length of the runout portion. | 08-15-2013 |
20130206504 | THERMAL-ACOUSTIC SECTIONS FOR AN AIRCRAFT - Embodiments of thermal-acoustic sections for an aircraft for reducing noise along an acoustic path produced from an acoustic source are provided herein. The thermal-acoustic section comprises a first porous layer having a first characteristic acoustic impedance. A second porous layer is disposed adjacent to the first porous layer and has a second characteristic acoustic impedance that is greater than the first characteristic acoustic impedance. The thermal-acoustic section is configured to be positioned along the acoustic path such that at least a portion of the noise from the acoustic source is directed through the first porous layer to the second porous layer to promote absorption of the noise. | 08-15-2013 |
20130205570 | METHOD FOR ATTACHING A COMPONENT TO AN INTERNAL PORTION OF AN AIRCRAFT FUSELAGE - A method for attaching a component to an internal portion of an aircraft fuselage is disclosed herein. The method includes mounting a vibration isolator assembly to the internal portion of the aircraft fuselage. The vibration isolator assembly has a protruding engagement portion having a flange. The method further includes defining an opening in a vibration-deadening body. The method further includes positioning the vibration-deadening body over the vibration isolator such that the protruding engagement portion is received within the opening. The method further includes pressing a retaining member onto the protruding engagement portion such that the retaining member engages the flange. The retaining member will retain a portion of the vibration-deadening body below an end of the protruding engagement portion. The method still further includes attaching the component to the protruding engagement portion. | 08-15-2013 |
20130204544 | METHODS AND SYSTEMS FOR DETERMINING AIRSPEED OF AN AIRCRAFT - The disclosed embodiments relate to methods and systems for determining airspeed of an aircraft. | 08-08-2013 |
20130197739 | METHODS AND SYSTEMS FOR AIRCRAFT HEALTH AND TREND MONITORING - The disclosed embodiments relate to methods and systems for monitoring sub-systems of an aircraft to detect an abnormal condition, and for identifying one or more sources that are causing the abnormal condition. In response to detecting a trigger event during flight of the aircraft, data for a plurality of relevant parameters is measured and stored in a parameter file. The parameter file is transmitted from the aircraft over a wireless communication link, and relayed to a ground support network. At the ground support network, the measured data for the plurality of the relevant parameters is then used to identify the one or more sources that are causing the abnormal condition. | 08-01-2013 |
20130197725 | METHODS AND SYSTEMS FOR REQUESTING AND RETRIEVING AIRCRAFT DATA DURING FLIGHT OF AN AIRCRAFT - The disclosed embodiments relate to methods and systems for requesting and retrieving aircraft data during flight of an aircraft. This aircraft data can be used to perform additional monitoring of aircraft sub-systems to detect an abnormal condition, and/or to identify one or more sources that are causing the abnormal condition. In one embodiment, aircraft data for one or more relevant parameters can be requested from the ground, measured on-board the aircraft, and stored in a data file that is then communicated back to personnel on the ground. The real-time aircraft data for one or more relevant parameters can then be analyzed to identify the one or more sources that are causing the abnormal condition. | 08-01-2013 |
20130185668 | VIRTUAL KEYBOARD ARRANGEMENT - A display assembly includes display having a bottom edge. An input device is integrated with the display for receiving input from a user. A plurality of icons are arranged as a row and displayed on the display. Each of the icons is selectable by the user. The row of icons is displayed non-parallel to the bottom edge of the display. | 07-18-2013 |
20130175395 | MOUNTING ASSEMBLY AND METHOD FOR MOUNTING A SOUND-DEADENING BODY TO A FUSELAGE OF AN AIRCRAFT - A mounting assembly for mounting a sound-deadening body to a fuselage of an aircraft and a method for attaching a sound-deadening body to a fuselage of an aircraft using the mounting assembly is disclosed herein. In a non-limiting embodiment, the mounting assembly includes, but is not limited to, a retaining member that is configured to engage the sound-deadening body. The mounting assembly further includes an isolating member that is engaged with the retaining member. The isolating member is configured for connection to the fuselage and is further configured to diminish transmission of vibration from the fuselage to and through the retaining member, and therefore to reduce the transmission of sound into the cabin. | 07-11-2013 |
20130147493 | SYSTEM AND METHOD FOR DETERMINING A CONCENTRATION OF GAS IN A CONFINED SPACE - A system for determining a concentration of gas in a confined space includes a first frequency generator for generating a first RF signal. A first antenna transmits the first RF signal across the confined space and second antenna receives the first RF signal. First and second RF signal power detectors detect the power of the first RF signal both prior to and after transmission through the confined space. A first comparator circuit determines a concentration of oxygen in the confined space based on the power of the first RF signal prior to transmission through the confined space and the power of the first RF signal received by the second antenna. | 06-13-2013 |
20130118594 | LOW SHOCK STRENGTH INLET - Embodiments of the invention relate to a supersonic inlet having a cowl lip configured to capture the conic shock and exhibit a zero or substantially zero cowl angle. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine. | 05-16-2013 |
20130115868 | VENTILATION SYSTEM AND METHOD OF ASSEMBLY - A ventilation system for ventilating a passenger compartment of an aircraft is disclosed herein. The ventilation system includes, but is not limited to, a nozzle that is adapted to be mounted proximate an interior of the aircraft and that is configured to direct a stream of air into the passenger compartment. The ventilation system further includes a valve that is spaced apart from the nozzle and positioned upstream of the nozzle, the valve configured to control a flow of air to the nozzle. The ventilation system still further includes a conduit that fluidly couples the valve to the nozzle. The conduit is configured to convey the flow of air from the valve to the nozzle. | 05-09-2013 |
20130112776 | NOZZLE ARRANGEMENT AND METHOD OF MAKING THE SAME - A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a nozzle having a trailing edge and a plug body partially positioned within the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface. A protruding portion of the plug body extends downstream of the trailing edge for a length greater than a conventional plug body length. The plug body is configured to shape the exhaust gases to flow substantially parallel to a free stream of air flowing off of the trailing edge of the nozzle and to cause the plume of exhaust gases to isentropically turn the free stream of air to move in a direction parallel to a longitudinal axis of the plug body. | 05-09-2013 |
20130110323 | METHODS AND SYSTEMS FOR AVOIDING A COLLISION BETWEEN AN AIRCRAFT ON A GROUND SURFACE AND AN OBSTACLE | 05-02-2013 |
20130099061 | FLAP ROLLER ARRANGEMENT, FLAP ASSEMBLY, AND METHOD FOR REMOVING A ROLLER ASSEMBLY FROM A FLAP FITTING - A flap roller arrangement for supporting a flap on a wing of an aircraft is disclosed herein. The flap roller arrangement includes, but is not limited to, a roller assembly that is configured for rolling engagement with a flap track of the wing and for engagement with a flap fitting. The flap roller arrangement further includes a retaining member that is removably coupled to the roller assembly. The roller assembly is configured to egress through an opening in the flap fitting in a direction away from the flap track. The retaining member is configured to obstruct egress of the roller assembly through the opening when the retaining member is coupled to the roller assembly. The roller assembly is enabled to egress through the opening when the retaining member is removed from the roller assembly. | 04-25-2013 |
20130098454 | ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT - A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining overall engine performance. | 04-25-2013 |
20130042922 | AIR INLET ARRANGEMENT AND METHOD OF MAKING THE SAME - An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate. | 02-21-2013 |
20120256768 | SYSTEM AND METHOD OF USING A MULTI-VIEW DISPLAY - Embodiments of the invention relate to a vehicle instrumentation systems and display systems employing multi-view displays in various land, water, air, and/or space vehicles. In one embodiment of the invention, an aircraft instrumentation system for a flight deck instrument panel includes at least one multi-view display configured to display at least two views, associating one view with a first crew member and the other view with a second crew member. In another embodiment of the invention, a standby instrument may be displayed on each of two multi-view displays such that a standby instrument is visible to each crew member at all times during aircraft operation. | 10-11-2012 |
20120256048 | Vibration Isolation System - A vibration isolation system for attenuating vibration energy between two aircraft structures, such as between the aircraft's fuselage and interior cabin. The vibration isolation system includes a first isolator attached to the first structure, a second isolator attached to the second structure, and an intermediate mass attached between the first and second isolators. The intermediate mass may be electrical cables, wiring bundles, a cable holder, or other component disposed between the two structures. Cable holder intermediate masses can be fabricated from an electrically conductive material to provide electromagnetic interference shielding for cables disposed therein. Multiple vibration isolation systems can be disposed between the fuselage and interior cabin to provide a less noisy cabin. Additional noise and vibration suppressors, such as skin damping material and acoustic blankets, also can be disposed between the fuselage and interior cabin to further reduce noise in the interior cabin. | 10-11-2012 |
20120199212 | ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT - A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance. | 08-09-2012 |
20120091286 | ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT - A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance. | 04-19-2012 |
20120065817 | LOW VISIBILITY LANDING SYSTEM AND METHOD - A low visibility landing system is provided for guiding aircraft on landing approaches. The low visibility landing system may aid a pilot during landing in low visibility conditions such that an aircraft may descend to lower altitudes without visual contact with the runway than is possible with other landing systems. The system may use various navigational systems to produce a hybrid signal that may be more stable than individual signals of those navigational systems. The hybrid signal is compared to a predetermined landing approach plan to determine the deviation of the aircraft from the landing approach plan and to provide guidance to the pilot to get the aircraft back onto the landing approach plan. The system may also use multiple navigational systems to perform checks on an operation of a primary navigational system to ensure that the primary navigational system is operating accurately. | 03-15-2012 |
20110241901 | Standby Display Aircraft Management System - One embodiment of the present invention includes an aircraft instrumentation system for a cockpit instrument panel having a first device associated with a first pilot of an aircraft and positioned on the instrument panel substantially in front of the first pilot. The first device may include a first display and a first controller, which may have a set of controls for controlling the first display and aircraft systems. The instrumentation system may also include a second device associated with a second pilot of the aircraft and positioned on the instrument panel substantially in front of the second pilot. The second device may include a second display and a second controller, which may have a set of controls for controlling the second display and the aircraft systems. The instrumentation may be configured such that at least one of the first display and the second display presents attitude, altitude and airspeed at all times. | 10-06-2011 |
20110190965 | System and Method for an Integrated Backup Control System - Embodiments of the invention relate to a flight control system for controlling an aircraft in flight having a backup control system integrated into an active control stick. The actuated control stick may include a processing unit that includes independent and separate hardware and/or software dedicated to the primary control system and the backup control system. For the primary control system, the processing unit may receive a sensed primary control stick signal and communicate with a primary processor, which may be configured to generate a primary control signal. For the backup control system, the processing unit may receive a sensed backup control stick signal and generate a backup control signal. The processing unit may also generate tactile signal for use by the actuated control stick to adjust the feel of a pilot's control stick. | 08-04-2011 |
20100043389 | LOW SHOCK STRENGTH PROPULSION SYSTEM - Embodiments of the invention relate to a supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine. By shaping the nacelle, embodiments of the invention may function to reduce sonic boom strength, cowl drag, and/or airframe interference drag. Embodiments of the invention may also function to improve total pressure recovery and/or total thrust of the primary flow path through the engine. | 02-25-2010 |
20090128366 | Multifunction Controller/Standby Instrument - One embodiment of the present invention includes an aircraft instrumentation system for a cockpit instrument panel having a first device associated with a first pilot of an aircraft and positioned on the instrument panel substantially in front of the first pilot. The first device may include a first display and a first controller, which may have a set of controls for controlling the first display and aircraft systems. The instrumentation system may also include a second device associated with a second pilot of the aircraft and positioned on the instrument panel substantially in front of the second pilot. The second device may include a second display and a second controller, which may have a set of controls for controlling the second display and the aircraft systems. The instrumentation may be configured such that at least one of the first display and the second display presents attitude, altitude and airspeed at all times. | 05-21-2009 |