Abstract: A system and a method for generating a signal to control a steering mechanism and an aircraft using the system are disclosed. A tiller module includes a moveable tiller base configured to moveably respond to a steering signal. The tiller module also includes a tiller coupling configured to couple the tiller with the moveable tiller base and further configured to generate a tiller differential signal indicative of a steering force applied to the tiller relative to a position of the moveable tiller base. A tiller controller is configured to receive the tiller differential signal and a steering mechanism position signal. The tiller controller is further configured to generate the steering signal to direct a steering mechanism to conform with the steering force and to direct the moveable tiller base of each tiller module to a feedback position representative of a current position of the steering mechanism.

Abstract: An articulation device for articulating a flap to an aircraft aerodynamic surface, the flap having its front edge facing a rear edge of the aerodynamic surface and the articulation device including two fittings bearing the flap. The articulation device pivots about a common axle borne by the aerodynamic surface and arranged at the interior side thereof, in order to cause the flap to adopt either a retracted position or a deployed position. The portion of each fitting facing a corresponding cutout, when the flap is in the retracted position, is set back toward the inside with respect to the outer faces of the aerodynamic surface and the flap. A flat blanking piece, the shape of which corresponds to that of the cutout, is associated with each cutout. Each blanking piece is borne by a linkage articulated to the aerodynamic surface and to the flap.

Abstract: Boeing achieves satellite diversity by having a large discrimination angle for a MEO constellation of communications satellites to limit interference in the Ku-band with GSO communications systems. Each satellite entering an exclusion zone over a GSO ground station terminates all transmissions to provide EPFD within acceptable limits. The Boeing MEO constellation preferably comprises 20 satellites, 5 in each orbit. The four orbits are inclined at about 57° with respect to the equator. Services include an Integrated Digital Service (IDS) and Backhaul Data Service (BDS) to accommodate the needs of different users.

Abstract: The invention is, in its various embodiments and implementations, a method and apparatus for planar actuation of a flared surface to control a vehicle. In one aspect, the invention comprises an apparatus for controlling a vehicle capable of moving through a fluid medium. The apparatus includes a flare; a planar yoke operably associated with the flare; a plurality of actuators capable of moving the planar yoke to manipulate the flare through the operable association between the planar yoke and the flare; and a load bearing structure through which the translating means imparts a moment from the flare to the vehicle. In a second aspect, the invention comprises a method for controlling the maneuvering of a vehicle capable of moving through a fluid medium. The method includes moving a planar yoke to deflect at least a portion of a flare.

Abstract: An aircraft body structure is disclosed and has a skeleton frame including a plurality of interconnected frame elements. A skin layer is affixed to at least a portion of the frame elements. The skin layer has an exterior surface and an opposite interior surface. A composite reinforcing layer is affixed to at least a substantial portion of the interior surface of the skin layer. The composite reinforcing layer has a reinforcing material combined with a non-flammable polymer foam material in a variety of different manners.

Abstract: A device for accelerating the destruction of contra-rotating vortices formed at the rear of wings of a moving body by the merging of at least two co-rotating eddies includes, on each of the wings, at least one perturbator which is positioned in the vicinity of the area of creation of one of the co-rotating eddies associated with the wing. Each of the perturbators generates a periodic perturbation of the flow, which has a wavelength capable of exciting at least one of the instability modes of the corresponding eddy in such a way as to increase the core of the contra-rotating vortex which is created from this eddy, in such a way that the diameter of the core becomes greater than a predetermined proportion of the inter-vortex distance.

Abstract: An impact resistant insulation tile is provided that is capable of withstanding the impact of Micrometeriods and Other Debris (MMOD). The tiles are secured to an exterior surface of a Reusable Launch Vehicle (RLV). A durable coating is applied to the exterior surface of a thermally insulative layer to fragment and slow down MMOD that collide with the tile. In addition, a shock layer may be embedded within the thermal insulator to further reduce the size and speed of MMOD particles. A ballistic strain isolator pad may also be located between the thermal insulator and the RLV structure to capture fragmented particles.

Abstract: A reconnaissance system and method utilizes an unmanned surface vehicle (USV) and at least one micro-aerial vehicle (MAV). The MAV, equipped for unmanned flight after a launch thereof, is mounted on the USV. Each MAV has onboard wireless communications coupled to an onboard video surveillance system. Each MAV launched into the air collects video data using its video surveillance and transmits the video data using its wireless communications.

Abstract: A snap-on sidewall assembly is provided for attachment to an airframe of an aircraft. The snap-on sidewall assembly includes an outer rail member that has a mounting portion for attachment to the airframe. The outer rail member has at least one recess integrally formed therein and at least one outer support flange extending from the recess. Each recess is adapted for engaging at least one protrusion integrally formed within an inner rail member. The integral inner rail member further includes at least one inner support flange extending from the protrusion. Finally, the snap-on sidewall assembly includes at least one sidewall panel. Each sidewall panel has an end portion that is, intended to be sandwiched between one of the outer support flanges and one of the inner support flanges.

Abstract: A composite flapping flexure is disclosed in which load carrying belts are located on the upper and lower surfaces of the flexure, and minor load carrying off-axis layers are located at the mid-plane of the flexure.

Abstract: The invention relates to a device and method for milking animals, in which the milk is removed is conveyed though a filter element. Any material which is deposited on the filter element is detected and, if appropriate, identified. After detection is complete, the direction of flow through the filter element is reversed, so that filter material is rinsed clean. The invention also comprises a contamination meter for user in die device and method mentioned above.

Abstract: An embodiment of the present invention provides a loading system for loading a stores item onto a release unit attachable to an aircraft structure, the release unit having a release actuation assembly including an actuator arm. The loading system comprises at least one hook pivotably mountable to the release actuation assembly. The hook has a pivot pin passage formed therethrough, a stores engagement portion and an actuation portion. The stores engagement portion is configured for engaging a lifting structure of the stores item. The actuation portion is configured for engagement by the actuator arm of the release actuation assembly to pivot the at least one hook and disengage the stores engagement portion from the lifting structure of the stores item. The loading system further comprises a pivot pin configured for insertion into the pivot pin passage. The pivot pin is removably mountable to the release actuation assembly for pivotably mounting the at least one hook thereto.

Abstract: The present invention 10 discloses an emergency low altitude parachute having a parachute canopy 28 that inflates by the introduction of compressed gas. A compressed gas canister 30 is located within the housing of the inflatable portion of the device and is activated by an activation ring 24. The device is stored within a carrying case 16 prior to use. When the low altitude emergency parachute 14 is removed from its storage case, the user 12 attaches the attachment harness 32 to their body. A helmet 22 with breathing apparatus is supplied. Once the user 12 is harnessed in, the device is held in the front of the body and an activation ring 24 is provided as means of activating the compressed gas canister 30. Once activated the parachute pontoons fill with the gas rapidly, expanding them and unfolding the parachute canopy 28. The device 10 is then released through the threshold 26 of the escape route.

Abstract: A fault tolerant attitude control system for a zero momentum spacecraft. A zero momentum attitude control system is operable to control spacecraft attitude utilizing data received from an earth sensor, a sun sensor, and the inertial measurement unit. A gyroless attitude control system is operable to control spacecraft attitude without receiving data from the inertial measurement unit. A redundancy management system is operable to monitor an inertial measurement unit to detect faults and to reconfigure the inertial measurement unit if a fault is detected and operable to determine when an inertial measurement unit fault is resolved. A controller is operable to automatically switch the spacecraft from the zero momentum attitude control to the gyroless attitude control when a fault in the inertial measurement unit is detected and is operable to automatically switch the spacecraft from the gyroless attitude control to the zero momentum control upon resolution of the fault.

Abstract: A multi-section aircraft door includes a sliding joint permitting a lower door section displacement into the flight deck area. The door includes an upper door section having a lower edge. The lower edge is connectably joined to an upper member of a two-member sliding joint. The upper member slidably joins to a sliding joint lower member. The sliding joint lower member is connectably joined to a lower door section upper edge. The upper member and the lower member of the two-member sliding joint include paired apertured embossments. A frangible pin slidably mates in each apertured embossment pair. A lever and cam form a frangible pin removal assembly. The lever is held in a normally upright position by either a spring device or a clevis and pin assembly. A rotating clasp or a ball détente system can also replace the frangible pin/apertured embossment and cam/lever.

Abstract: Flight information is displayed using visual indications that resemble real world visual cues. For example, left and right side attitude displays extend vertically along each side of the windshield and a yaw display extends along a lower edge of the windshield. The attitude displays employ reference indications and outermost indications which track the position of the actual horizon. The yaw display employs outermost indications spaced from a reference indication a distance proportional to the rate of turn. Indexing of indications between the references and the outermost indications provides the appearance of movement representing climb, descent and turns. The rate and direction of indexing may be proportional to the rate and direction of change.

Abstract: A heat exchanger system and method for heating selected areas of the wings of an aircraft. The heat exchanger apparatus involves the use of a heat exchanger and thermal contact with the fluid of a gear box associated with a geared fan powerplant used on an aircraft. The heat exchanger is in fluid communication with at least one, and more preferably a plurality, of conduits which circulate fluid heated by the fluid of the gearbox throughout the selected areas of the wings of the aircraft. This serves to selectively heat various areas of the wings to help prevent icing of the leading edge of each of the wings, as well as to increase the region of laminar flow over the wings, and thus decrease those areas where turbulent flow occurs.

Abstract: The invention relates to a process for de-icing an air intake cowling of a reaction motor, comprising a lip (6a), a de-icing system (10) for the lip and acoustic attenuation means (11) characterized in that it consists in constituting said acoustic attenuation means by separate islands (12) each formed of a sandwich comprising an acoustically resistive porous layer forming a portion (13) of the external envelope of the fan channel limited by said lip, a cellular core and a deflector (15), in constituting or covering the reflector of each island with the help of a common element (15) extending over all the islands (12), emplacing in communication the space or spaces between islands, on the one hand, with the interior of the lip (6a) and, on the other hand, with the exterior of the cowling so as to create a forced circulation of de-icing fluid from the interior of the lip to the outside of said cowling.

Abstract: A method for rapid earth reacquisition of a spacecraft. A three-axis inertial attitude of the spacecraft is determined by rotating the spacecraft about its pitch axis while measuring star patterns. A pitch axis of the spacecraft is aligned with earth's pole axis. The spacecraft is reoriented with respect to an earth-pointing reference frame.

Abstract: The present invention provides an anti-hijacking system. In one embodiment, the anti-hijacking system is used in an airplane cockpit to provide forceful contact to disarm, disable, immobilize or otherwise incapacitate a hostile intruder who has entered the cockpit. The anti-hijacking system includes one or more inflation devices, such as deployable air bags.