Abstract: A standard telemetry system is utilized in conjunction with a variable configuration missile irrespective of the missile configuration test fired. The system includes a common energy source, power supply, transmitter, commutator and signal conditioner. A portion of the telemetry signals produced by each missile configuration is, to an extent, unique to that particular configuration. The system utilizes a different programming connector cable for each missile configuration. The connector cable interfaces telemetry signal producing missile components with the common signal conditioner. The signal conditioner includes all of the circuitry and signal processing components necessary to process all of the telemetry produced by all of the missile configurations.

Abstract: An electronic circuit for use in an anti-radiation missile system of the type which uses the electromagnetic transmissions of a target radar for guidance information, detects when the missile has flown into a target null and is no longer receiving energy from one of the main lobes or side lobes of the target radar transmitter. When this condition is detected, the circuit causes an attenuation in the epsilon error guidance signal to momentarily prevent guidance commands based upon the now suspect epsilon error signals from being implemented.

Abstract: A method for manufacturing a multichip module deposited substrate board utilizing alternating layers of high density thin-film metal and either preimidized or non-preimidized organic polymer insulating material wherein the insulating material is cured during manufacture using either ultraviolet radiation, ion beam radiation or electron beam radiation. This method eliminates subjecting the in-process substrate board to temperatures in excess of the recrystalization temperature of the thin-film metal, thereby eliminating the source of warpage and metal interdiffusion and corrosion at the metal to insulating material interface. This process enables successful manufacture of large format multichip module deposited substrate boards in sizes up to approximately 24 inches square.

Abstract: An aircraft fuel tank construction for providing enhanced fuel tank survivability and aircraft structural integrity when the fuel tank is penetrated by an exploding projectile, utilizes selective placement of low density, fluid-displacing material to create a low shock impedance region which decouples protected fuel tank structure from the destructive effects of a shock wave. The low shock impedance region may be formed using closed cell foam, or using isolators comprising bladders inflated with a compressible, inert gas. Such bladders should have a wedge shape and a wedge angle of at least 15 degrees. Precise shape is less important with closed cell foam. Polymethylacrilimide has been shown to be particularly effective for this purpose. Finite element analysis is useful in tuning the design of actual low shock impedance regions for actual aircraft designs.

Abstract: An aircraft for vertical or short take off and landing operations having two main lift nozzles, both positioned at or near the aircraft center of gravity utilizes one or more jet screen nozzles, arranged in a variety of shapes and combinations, discharging bypass air from a position forward of the center of gravity, and a variable pitch nozzle discharging engine exhaust gas mixed with bypass air from a position aft of the center of gravity, to achieve pitch control while airborne in vertical take off or landing mode. The jet screen nozzle also prevents or reduces ingestion of mixed hot exhaust gas and bypass air discharged through the main lift nozzles. The jet screen nozzle further prevents or reduces ingestion of foreign object debris disturbed by the vertical lift discharge flowing from the main lift nozzles.

Abstract: A lightweight, two piece adjustable attachment device provides simple installation into a part, develops robust strength, and enables alignment of a retaining screw or bolt axis with the longitudinal axis of a threaded mounting hole, despite part to mount misalignment caused by tolerance build-up in a complex assembly. The adjustable attachment device is designed to provide sufficient overlap on each side of the part of the edges of the circular receiving aperture that the adjustable attachment device is able to withstand great force without pulling out of the part. The adjustable attachment device includes a fastener receiving slot that extends across the adjustable attachment device. The adjustable attachment device is installed into a circular receiving aperture in a part to be assembled onto a larger assembly.

Abstract: A guide rail and support assembly for use in an aircraft cargo compartment for guiding cargo containers being transported by the aircraft cargo container transportation system uses a four bar mechanism to allow the guide rail to be lowered to accommodate wide cargo containers. The assembly lowers or retracts in response to being accidentally struck endwise by a cargo container, thereby avoiding damage to the cargo deck surface. The guide rail and support assembly uses a detent mechanism to prevent nuisance retractions while reliably retracting in response to endwise impact by a cargo container. The guide rail and support assembly is easily lowered manually when necessary to accommodate wider cargo containers, and is easily reset to the extended or upright position manually.

Abstract: A pitch control system for a vertically launchable and recoverable winged aircraft includes a collective and cyclic pitch control system, a drive yoke and a rotor hub. The collective and cyclic pitch control system is operably connected to two proprotor blades to cyclically control the pitch of each proprotor blade, so that the aircraft is capable of controlled helicopter mode flight when the aircraft body is pointed in a generally upward direction. Proprotor blade flapping caused by applying cyclic pitch control results in teetering of the rotor hub with respect to the drive yoke. Torsion bar springs are used with suitable mechanical linkages to resist this teetering motion and generate the hub moment which is transmitted to the airframe and used to maneuver the aircraft.

Abstract: An aircraft autobrake system utilizes a hydraulic fluid pressure sensor to provide a signal proportional to brake hydraulic fluid pressure magnitude to a control system. The control system uses closed loop feedback of this pressure signal to control autobrake application. Such control avoids pressure or deceleration overshoot or undershoot caused by not achieving brake stack closure when deceleration control is applied. Upon landing, if autobrake control command plus the change in autobrake control command necessary to eliminate deceleration error is less than a specified minimum, then brake stack closure needs to be maintained. In that case, the control system determines hydraulic fluid pressure error and adjusts hydraulic fluid pressure to eliminate such pressure error, using closed loop feedback. Upon elimination of pressure error, indicating brake stack closure, deceleration control then applies autobraking to slow the aircraft without pressure or deceleration overshoot or undershoot.

Abstract: A noise suppression processor maintains a carrier tracking loop in a receiver in lock in the presence of high noise levels to permit the receiver to measure range changes from a remote transmitter in noisy environments. The noise suppression processor is connected in the carrier tracking loop between the phase detector which produces the loop error signal and the loop filter. The noise suppression processor has a cubic-limiter transfer function to provide nonlinear amplification of the loop error signal while limiting the amplified error signal to predetermined maximum and minimum values.

Abstract: An automated setup verification system provides a means and method for rapidly and accurately verifying that the component feeder magazines on a surface mount technology placement machine are correctly installed for manufacturing a selected printing wiring assembly. The system prevents manufacture until machine setup is verified correct, thus preventing manufacture of a large number of defective assemblies when there has been erroneous placement of component feeder magazines. The system comprises a local area controller which contains design and machine information, a programmable logic controller, a bar code scanning and proximity detection system, a test station for testing a sample component from a component feeder magazine, and a structural bridging and spanning assembly for adapting the invention to an existing surface mount technology placement machine. An operator associates a component to a component reel and a component feeder magazine in the local area controller using a bar code system.

Abstract: An aircraft structure for the minimization of microwave energy reflection from the aircraft back to a receiver. The provision of structural configurations and materials operate to reduce microwave energy reflection toward its source or another receiver located at a level below the aircraft and laterally or forward thereof.

Abstract: An aircraft structure for the minimization of microwave energy reflection from the aircraft back to a receiver. The provision of structural configurations and materials operate to reduce microwave energy reflection toward its source or another receiver located at a level below the aircraft and laterally or forward thereof.

Abstract: An aircraft structure for the minimization of microwave energy reflection from the aircraft back to a receiver. The provision of structural configurations and materials operate to reduce microwave energy reflection toward its source or another receiver located at a level below the aircraft and laterally or forward thereof.

Abstract: An aircraft structure for the minimization of microwave energy reflection from the aircraft back to a receiver. The provision of structural configurations and materials operate to reduce microwave energy reflection toward its source or another receiver located at a level below the aircraft and laterally or forward thereof.

Abstract: An electronic circuit breaker has a switching transistor for controlling current flow in a circuit. The switching transistor is controlled by a pair of complementary field-effect transistors to achieve very fast switching action. The electronic breaker is capable of sensing an overcurrent condition and interrupting current flow in less than a microsecond. The electronic circuit breaker also has an inductor for limiting the rate at which current can increase during the time delay between sensing an overcurrent and interrupting current flow.

Abstract: A traveling charge projectile utilizes a microprocessor and a plurality of sequentially fired igniting-priming-expelling charges to initiate respective charge segments containing propellant, such as granular propellant, of predetermined grain size, to produce a more nearly constant pressure against the projectile base. Traveling charge propellant segments attached to the projectile move with the projectile as it accelerates in the gun barrel. At appropriate intervals during barrel transit, a firing signal initiates a charge which propels the aft most propellant segment away from the projectile into the hot gases and flame behind the projectile to fully ignite the propellant charge and repressurize the expanding breech volume immediately aft of the accelerating projectile. This design maintains a higher average pressure on the base of the projectile during barrel transit, and results in a higher projectile muzzle velocity.

Abstract: A vortex control device is designed for installation on the exterior surface of an aircraft nacelle in a position which does not compromise the optimum aerodynamic performance of the vortex control device. Existing cowling structure is bridged by this vortex control device which attaches only to movable structure and which is cantilevered over adjacent stationary structure. A resilient seal prevents air from swirling under the cantilevered portion, thus contributing to vortex generating efficiency and reduced aerodynamic drag.

Abstract: A gun barrel and projectile system utilizes a smooth central bore gun barrel fitted with a short rifled insert near the breech end. A projectile fitted with a perforated skirt and driving band about the base of the skirt are loaded into the gun barrel so that the driving band just engages the rifled insert, and the warhead portion of the projectile extends into the smooth bore portion of the barrel. Upon firing of a breech charge, gases from the breech charge are ducted to the space between the thin side walls of the projectile and the smooth central bore, thereby establishing a gas bearing. The gas bearing provides lateral support to the projectile and lubricates the projectile in the smooth central bore. Because of the lateral support the projectile receives from the gun barrel and the gas bearing, much less projectile structural strength is required to resist set-back forces. Mass fraction ratios of ordnance payload mass to structural mass in the projectile are on the order of ninety percent.

Abstract: A sabot fragment diverter deflects selected sabot fragments discarded by ot type ammunition in a directionally controlled manner to prevent direct fragment impact with the firing platform or impact of a deflected fragment with the projectile from which it is discarded. A fragment diverter cone which includes a deflecting surface, a fragment cutter and a barrier dam is connected to the muzzle end of a gun system by an extender cage and a mounting section.