Abstract: A dispensing system for releasing a number of spacecraft from a launch vehicle. The dispensing system includes a base support structure securely fastened to a launch vehicle and a number of stacked frame assemblies. Each frame assembly includes a number of substantially parallel load bearing elongated post elements and a shear load transferring structure. The post elements are so arranged and spaced so as to define a geometry having a centerline. Each post element has a first end portion and a second end portion. Each first end portion is connected to either another frame assembly or the base support structure of the launch vehicle. The post elements support a number of spacecraft. The spacecraft are supported between adjacent post elements. The shear load transferring structure is connected to the post elements for transferring shear loads between the post elements.

Abstract: An aircraft engine apparatus with a reduced inlet vortex is provided which utilizes a vortex disruption system that periodically discharges pulses of engine bleed fluid through at least one outlet port opening through the inlet of the engine nacelle to disrupt the engine inlet vortex. The vortex disruption system thereby prevents ingestion of foreign matter into the engine inlet without sacrificing engine power, efficiency, or aircraft cruise performance.

Abstract: A computer system automatically generates CNC code for a stitching machine. The computer determines the locations of a present stitching point and a next stitching point. If a constraint is not found between the present stitching point and the next stitching point, the computer generates code for making a stitch at the next stitching point. If a constraint is found, the computer generates code for changing a condition (e.g., direction) of the stitching machine's stitching head.

Abstract: The present invention relates to an engine mount assembly for supporting an aircraft engine in aft-cantilevered position beneath the aircraft wing. The assembly includes a pair forward engine mounts positioned on opposite sides of an integrally formed yoke member wrapped about the upper half of the engine casing. Each side of the yoke is preferably configured as an A-shaped frame member with the bottom portions joining each other and the pylon. To prevent "backbone bending" of the engine trunnion assembly, the forward engine mounts supported at opposite ends of the yoke engage the casing along its centerline. The trunnion assembly is preferably constructed of high strength titanium machined and/or forged.

Abstract: The method and associated apparatus of the present invention decodes digital signals by appropriately weighting the respective noise portions of the two phase segments generated by the detector, such as an APD in an optical communications system, such that the digital signal can be reliably decoded despite the presence of multiplicative noise induced by the detector. The detector detects a digitally encoded communications carrier signal having a waveform defining first and second portions. The detector then generates an electrical signal in response to the digitally encoded communications carrier signal. The electrical signal has two phase segments, namely, one phase segment corresponding to the first portion of the digitally encoded communications carrier signal and another phase segment corresponding to the second portion of the digitally encoded communications carrier signal. Each phase segment also includes a respective noise portion.

Abstract: The structural assemblies are selectively reinforced with metal matrix composite in the regions susceptible to mechanical failure. More specifically, a channel is machined in a structural member in an area of relatively high stress. A reinforcing member is inserted into the channel. A metal powder is deposited on and around the reinforcing member. The metal powder is irradiated by a high energy source to thereby encase the reinforcing member in a metal matrix and to consolidate the metal matrix to the interior surface of the channel. The resultant assembly is lightweight and has improved strength and stiffness at room and elevated temperatures.

Abstract: A high responsivity thermochromic infrared detector which has an operating temperature that is established on the steepest part of the phase transition curve and is maintained there while the infrared detector is operated.

Abstract: The stores ejection system and method of the present invention provide automatic pre-load device, such as a pneumatically-operated pre-load piston, to pre-load a store ejection ram into contact with a bomb or other store prior to store ejection. Mechanical shock to the store during ejection is thereby minimized. The ejection system automatically retracts following store ejection to minimize ejection system aerodynamic drag during flight.

Abstract: A store interface for routing different types of store signal formats to multiple wing stations using pre-existing aircraft wing wiring. The store interface provides an interface between an aircraft and an associated store adapted to bidirectionally communicate with the aircraft according to one of a plurality of predetermined store signal formats. The store interface includes a store identifier that determines the type of the associated store, and an interface that bidirectionally communicates between the aircraft and the store, includinga first and second communication links that communicate with the store using either a first set of store control signals configured in accordance with a first store signal format or a second set of store control signals configured in accordance with a second store signal format.

Abstract: A conformable, integrated antenna assembly providing three or more radiating apertures in a single antenna structure is provided. The antenna assembly is adapted to mount flush with the fuselage or other surface of an aircraft or other structure. A range of antenna services, including communications, navigation and IFF (CNI) services, may thus be provided while simultaneously minimizing aerodynamic drag and reducing size, weight and cost.

Abstract: A sighting apparatus is provided for aiming an optical device mounted on a moving platform and having both coarse and fine adjustment. The sighting apparatus includes a fixed base and an outer support ring that is capable of rotation by a drive motor about an azimuthal axis perpendicular to an axis defined by the outer support ring. A support hub is rotatably supported within the outer support ring and is capable of rotation by a drive motor about an elevational axis substantially coincident with the axis defined by the outer support ring. At least one mounting plate is supported by the support hub and the mounting plate is capable of movement about the azimuthal and elevational axes relative to the support hub, and the mounting plate is capable of movement about a roll axis perpendicular to the azimuthal and the elevational axes.

Abstract: An imaging apparatus for aiding landing of aircraft in weather conditions obscuring a pilot's view of a runway. The apparatus comprises a plurality of LED assemblies which are disposed along the runway. Each LED assembly includes a plurality of LEDs, a receiver and a plurality of drivers responsive to the receiver for energizing the LEDs. The LEDs of each LED assembly are pulsed on by signals from a transmitter disposed adjacent an end of the runway. The transmitter also sends synchronization signals to a receiver located on board the approaching aircraft. The receiver on the aircraft is coupled to a processor which uses the synchronization signals to determine when the LEDs are energized and when they are not energized. The processor controls a CCD camera mounted on the aircraft so as to obtain an unobstructed view of the approaching runway. The processor controls the CCD camera such that the camera takes images (i.e., frames) while the LEDs are pulsed on and also while the LEDs are off.

Abstract: A method for recording and reporting fault information pertaining to various components of an aircraft. The method involves recording a diverse plurality of information output from various line replaceable units (LRU's) and other components of the aircraft during takeoff, flight and landing through the use of a bulk storage device, such as an optical quick access recorder (OQAR), on an electronic medium. The electronic medium is then removed from the aircraft after landing and read by an appropriate apparatus. From this information a service technician is able to determine whether or not a fault indication recorded during flight is in fact a legitimate fault requiring the affected LRU to be removed from the aircraft for further diagnostic testing. The method significantly reduces the incidents of no-fault-found diagnostic test results and saves significant man hours which would otherwise be spent testing LRU's and other components which are in fact operating properly.

Abstract: A multilayer circuit board and an associated heating apparatus is provided for heating electrical components. The multilayer circuit board includes a trace layer having at least one electrical trace terminating with a contact pad that is positioned to electrically contact a respective lead of an electrical component mounted upon the multilayer circuit board. The multilayer circuit board also includes a heating layer disposed in thermal contact with the electrical component mounted upon the multilayer circuit board. The heating layer includes a first electrically resistive heating element disposed upon an insulating substrate in general alignment with the electrical component mounted upon the multilayer circuit board. The electrically resistive heating element provides heat to maintain the operating temperature of the electrical component within a desired range.

Abstract: The present invention provides a door operating system for opening and closing a door covering an exit opening of an aircraft. More particularly, the present invention provides a door operating system for opening and closing a plug type door typically located on the lower passenger deck of an aircraft. The door operating system includes a frame that is connected to the door of the aircraft and defines a pivot for the door. Connected to the frame is a torque drum and linkage system. The door operating system also includes a motor and a cable drum attached to the opposite end of the track. A cable is connected to the cable drum, the torque drum, and the frame. When opening the door, the motor turns the cable drum, which thereby pulls the cable. The cable rotates the drive torque drum and causes the door to be rotated about the pivot thereby moving the door upwardly and inwardly away from the exit opening.

Abstract: An apparatus and method for forming an aircraft fuselage having at least one doubly curved portion. A plurality of fuselage panels are extruded with integrally formed stiffening portions extending preferably longitudinally the full length of each fuselage panel. The stiffening portions are further formed so as to be generally parallel to one another. The fuselage panels are then formed into skin panels having a desired curvature and trimmed into gores, and the stiffening portions trimmed at end portions that run out toward longitudinal edges of the panels. When adjacent panels are affixed together, the stiffening portions run out toward longitudinal edges of adjacent panels. The longitudinal edges are secured by splice longerons which are riveted or welded to the longitudinal edges of the skin panels. Independent fastening members are then secured to the stiffening portions and the splice longerons at the points where the stiffening portions run out to positions closely adjacent the splice longerons.

Abstract: A method for measuring strain on a structure having a bore and an untethered fiber-optic strain gauge embedded in the bore, which includes the steps of inserting a coupler portion of a fiber-optic cable into the bore in operative relationship to the fiber-optic strain gauge, and using an optical cavity length measurement device attached to the distal end of the fiber-optic cable to measure the strain on the structure. The coupler portion of the fiber-optic cable is removed from the bore after the strain on the structure has been measured. In an illustrative embodiment, the structure is a fastener, e.g., a rivet, used to join together the aluminum skin and the airframe of an aircraft, the bore being provided coincident with the central, longitudinal axis of the rivet.

Abstract: The present invention provides a fastening assembly system for applying fasteners along the seams of a cylindrical structure. The fastening apparatus includes a base unit which releasably attaches to a cylindrical structure, and a first fastening device coupled the base unit for applying fasteners along a seam of the cylindrical structure. The base unit may be embodied as either two crescent shaped members in parallel alignment for attaching to the upper half of the cylindrical structure. Alternatively, the base unit may include a base plate that is attachable to the floor beams on the interior of the cylindrical structure. In the preferred embodiment, the first fastening device cooperate with a second fastening device located on the opposite side of the cylindrical structure during the fastening process.

Abstract: A preform resin immersion process (PRIP) for impregnating resin into a preform for the fabrication of composite structures. The resin contains a heatactivated catalyst and a thixotropic agent which maintain the viscosity of the resin at selected low level during the resin immersion process. The dry preform is placed in an impregnation vessel, and the resin is held in a resin storage vessel, with both vessels initially held at vacuum of about 5.0 mm Hg torr to draw off any air or volatiles. Pressure is introduced into the resin storage vessel, causing the resin to flow through a line into the impregnation vessel which is still held at vacuum conditions. When enough resin is in the impregnation vessel to completely immerse the preform, the flow of resin to this tank is stopped. Once the resin has completely permeated the preform, the resin is drawn back into the resin storage vessel, and the saturated preform is raised up from the impregnation vessel so that the excess resin drips off into collection means.

Abstract: An interface seal (52) for an aircraft (50) has a first rigid structural beam (60) attached to a first portion of the aircraft (50). A second rigid structural beam (64) is attached to a second portion of the aircraft (50). An elastomer skin (62) is connected to the first rigid structural beam (60) and attached to the second rigid structural beam (64).