Abstract: The invention is a system and method for verifying the radar signature of a pair of aircraft. The system includes a radar transmitter and receivers located in the leading and trailing edge of the wing at the wing tip of the aircraft such that when flying the aircraft in formation with one aircraft behind the other aircraft, each aircraft can illuminate the other and verify the radar signature of the other.

Abstract: A method and apparatus is provided for managing bandwidth and prioritizing different forms of data to be transmitted from a central hub or node to a plurality of ground stations. All data of all types including image data and text data is processed into frames of TCP formatted data at the central hub or node and passed through a bandwidth flow control system which imposes flow control on the data. Some of the TCP formatted data has inserted therein a conversion flag which denotes a desire to convert the TCP formatted data into UDP formatted data. A computer or controller/converter reads the conversion flags and converts TCP formatted data into UDP formatted data for multi-broadcasting simultaneously to a plurality of ground stations which reduces bandwidth.

Abstract: The invention is a system for supporting a vertical take off and landing aircraft during hover tests about the ground, the aircraft having a longitudinal, vertical, and lateral axis, a nose landing gear and a main landing gear positioned rear therefrom on either side of the longitudinal axis. In detail, the system includes a bearing assembly, preferably and air bearing assembly positionable under the nose and each main landing gear. An air cushion assembly mounted to each of the air bearings with the air cushion assembly detachably coupled to each landing gear. Preferably, the air cushion assemblies are coupled to the landing wheel axles. Thus the bearing assemblies allow horizontal motion above the ground and the air cushion provides for vertical movement of the aircraft above the ground.

Abstract: An anti-submarine warfare system includes an unmanned “sea-sitting” aircraft housing submarine detecting equipment, the aircraft including a body portion having a catamaran configuration adapted for stably supporting the body portion when sitting in water, the body portion including a fuselage and laterally disposed sponsons connected to the fuselage via platforms, and submarine detecting equipment housed within the fuselage and adapted to be electronically linked to sonobuoys disposed in adjacent water locations.

Abstract: An apparatus for continuously producing composite structural beams is disclosed. The invention includes novel apparatus for producing a continuous lightweight composite beam by combining solid pultruded cap sections with composite sandwich panels. The invention further provides novel means by which pultruded composite tubular structural elements can be made of composite materials, wherein the tubular elements include solid pultruded corners.

Abstract: The invention is at least a partially buoyant vehicle. In detail, the vehicle includes a gas-containing structure having an outer contoured surface. At least one solar panel assembly is mounted to the outer surface of gas-containing structure, the solar panel movable over a portion of the surface of gas-containing structure. A drive system is provided for moving the at least one solar panel assembly over the outer surface of the gas-containing structure. A track assembly mounted on the surface of the gas-containing structure for guiding the at least one solar panel assembly over the surface. Preferably the at least one solar panel assembly in the form of a flexible strip having first and second ends movable along the surface about the longitudinal axis of the vehicle.

Abstract: Improved joints for cryogenic liquid-containing tanks are disclosed. The joints include a support plate, a lower arm mounted on the support plate, an upper arm mounted on the support plate spaced from the lower arm, and tank skins extending into the space between the lower and upper arms. Sealing layers are provided between the tank skins and the joint arms. The joints are particularly useful for space launch vehicle cryogenic liquid propellant tanks which must be lightweight, withstand high structural loads and maintain leak-free conditions.

Abstract: A propulsion system for a non-rigid and at least semi-buoyant vehicle, the vehicle including a pressure stabilized gasbag having a gondola mounted on the bottom thereof. The gasbag further includes catenary curtains extending from the top of gasbag to the bottom of the gasbag and attached thereto. In detail, the propulsion system includes a first pair of tubular members attached, preferably pivotally attached, by one of their ends to the gondola and which extend through the air bag and exit out the top thereof and having propulsion units, preferably turbo-prop engines, attached to their opposite ends. A second pair of tubular members is attached by one of their ends to the gondola, preferably pivotally attached, and extends into the gasbag and having their opposite ends terminating therewithin. A horizontal tubular member extends through the gasbag and has its ends extending out of the sides thereof and is attached to the opposite ends of the second pair of tubular members in the middle thereof.

Abstract: A landing gear actuation system for deploying aircraft landing gear and associated doors includes a pressurized gas source, a first hydraulic circuit for actuating landing gear doors, a second hydraulic circuit for actuating landing gear, and valving for regulating flow of gas sequentially from the source to the first hydraulic circuit, and from the first hydraulic circuit to the second hydraulic circuit. The pressurized gas source includes a container, a gas in the container at a pressure of approximately 6500 psi, and a pyrotechnically actuated device for opening the container. Preferably, the gas comprises helium, nitrogen or a combination thereof. The pyrotechnically actuated device comprises a burst disk cutter valve, and the pressurized gas source further comprises a pressure regulator for reducing the pressure of gas flowing from the container to a safer level of pressure of approximately 2000-3000 psi.

Abstract: This invention relates to a pressure stabilized inflated air transport vehicle having means for limiting crack propagation in the hull envelope whereby leakage of the gas in the haul due to the crack will not exceed the gas pressure maintaining means.

Abstract: A non-ridged semi-buoyant vehicle includes a pressure stabilized gasbag having a longitudinal, vertical and horizontal axis, top, bottom and side surfaces and front and rear ends and an aerodynamic shape capable of producing lift. Within the gasbag are first and second vertical catenary curtains attached to the top and bottom surfaces between the sides of the gasbag. These first and second catenary curtains are positioned on either side of the longitudinal axis extending from the front end along a first portion of the gasbag. A pair of first and second Y shaped catenary curtains are coupled to the first and second vertical catenary curtains and extend along a second portion of the gasbag. The arms of each of the Y shaped curtains are attached to the top surface and the legs are attached to the bottom surface of the gasbag. First and second pairs of vertical catenary curtains are coupled to the first and second pairs of Y shaped catenary curtains, respectively, and extend to the rear end of said gasbag.

Abstract: Improved joints for cryogenic liquid-containing tanks are disclosed. The joints include a support plate, a lower arm mounted on the support plate, an upper arm mounted on the support plate spaced from the lower arm, and tank skins extending into the space between the lower and upper arms. Sealing layers are provided between the tank skins and the joint arms. The joints are particularly useful for space launch vehicle cryogenic liquid propellant tanks, which must be lightweight, withstand high structural loads and maintain leak-free conditions.

Abstract: A method and system is disclosed for using inertial sensors in an Inertial Navigation System (INS) to obtain analytic estimates of angle-of-attack (&agr;) and sideslip angle (&agr;). The inertial sensors consist of one or more accelerometers which produce the estimated signals for angle-of-attack (&agr;) and sideslip angle (&bgr;). Three methods are shown for obtaining &agr; and &bgr; estimates from INS information and are programmed into a nonlinear simulation of a relaxed stability aircraft requiring a high level of artificial stability augmentation in its flight control system. Simulation results from the nonlinear simulation for each of the three methods were compared with the results obtained when conventional probes were used to obtain direct measurements of &agr; and &bgr;.

Abstract: An apparatus and process for continuously producing composite structural beams is disclosed. The process includes a first step of forming a tubular element from fibers of composite material, a second step of separating the tubular element into longitudinally extensive, circumferentially separated, corner caps, a third step of securing sandwich panels between adjacent corner caps to form a tubular beam, a fourth step of shaping the tubular beam, and a fifth step of curing the shaped tubular beam. Also disclosed is an exemplary beam constructed in accordance with the process of the present invention.

Abstract: A rugate filter coating for reflecting at least a portion of at least one electromagnetic wavelength band, the filter comprising a transparent coating on a substrate, the coating having an incrementally varying refractive index of refraction depth, with each of the increments having a constant a constant index of refraction. The index of refraction of the increments determined by calculating the index of refraction profile of the coating, dividing the continuous index of refraction coating into increments and setting the constant of refraction for each of the increments equal to the average index of refraction of the continuous index of refraction over the increment.

Abstract: A method for making an improved absorber entails the loading of reticulated foam loaded with radar absorbing material and the forming and curing of the loaded foam in a mold on which vacuum is impressed prior to curing of the foam so that the foam expands and thereby experiences a substantial reduction in density of the resulting absorber structure.

Abstract: A method for making an improved radar absorbing structure which includes forming a stack of layers of elastomeric sheet material, at least one of which supports conductive material, with a layer of dielectric material, shaping the stack, and curing the shaped stack. The stack of layers has a thickness of no more than 0.1″, and may be wrapped about a mandrel or fitted to another forming body to impart a final, complex, shape to the stack, and then cured.

Abstract: The invention is an apparatus for releasably connecting a first structure to a second structure. In detail, the invention includes the first structure having a first cavity extending inward from a surface thereof. An inward facing circumferencial lip is mounted in the first cavity in proximity to the first surface forming a restricted opening having a first diameter. The second structure includes a second cavity extending inward from a surface of the second structure. A hollow tubular member having first and second ends is movably mounted within the second cavity, with the tubular member movable from a retracted position to an extended position. The first end of the tubular member is in the form of a collet movable between a retracted position and an expanded position in contact with the lip in the first cavity when the tubular member is in the extended position.

Abstract: The invention is a non-ridged, semi-buoyant vehicle. In detail, the invention includes a pressure stabilized gasbag having front and rear ends and an aerodynamic shape capable of producing lift, and longitudinal, vertical and horizontal axis, the tail end of the gasbag extending outward along the horizontal axis from each side of the longitudinal axis toward said front end at an acute angle to the horizontal axis. A horizontal tail surface is mounted outboard of the rear end of the gasbag, having a trailing edge extending outward along the horizontal axis from each side of the longitudinal axis toward the front end at the acute angle to the horizontal axis. A horizontal ridged beam is mounted outboard of the rear end of the gasbag that extends outward along the horizontal axis from each side of the longitudinal axis toward the front end at the acute angle to the horizontal axis with the horizontal tail surface mounted to the beam. The preferred acute angle is approximately 20 degrees.