Abstract: A portable defogging device for defogging multi-paned windows comprising an open loop source of low moisture gas and a flexible conduit for introducing the gas into the enclosed space between the window panes. A regulator is used to introduce the fixed rate of flow of gas through the flexible conduit and into the enclosed space so as to remove the pre-existing or previous condensation in the enclosed space. In a double-paned aircraft window, the low moisture gas is introduced through a pressure equalization hole in the window. A method of defogging a multi-paned window comprising passing a low moisture gas through a flexible conduit and into an enclosed space between at least two window panes. The discharge of gas is regulated to a constant flow so as to remove moisture from the enclosed space, wherein the defogging device is deactivated and removed from the window to complete the defogging cycle.

Abstract: An improvement to an aircraft flight control system is provided for reducing the likelihood of an aircraft tailstrike. The flight control system includes a pitch command provided to a pitch control device for altering the aircraft's pitch attitude. The improvement is a system of altering the pitch command to avoid an aircraft tailstrike. The improvement includes determining a current tailskid closure rate and a current tail height; comparing the current tailskid closure rate with a threshold closure rate to determine an excess closure rate amount; and adding an incremental nose-down pitch command with the pitch command to avoid a potential aircraft tailstrike. The threshold closure rate is dependent upon the current tailskid height. The incremental nose-down pitch command is calculated as a function of the excess closure rate amount.

Abstract: A thrust vectoring mechanism to vector thrust and control discharge throat area includes four or more vanes mounted across the outlet of a nozzle in a cascade arrangement. The mechanism further includes a rod to control pivoting of each of the vanes that may be selectively rotated with one or more actuators. The rod includes threading. The vanes each include a drive member that is either toothed to engage the rod threading or defines a camming relationship with a coupling member threaded on the rod. The rod threading, drive members, and coupling members may be arranged to define different pivoting schedules for each of the vanes so that a generally constant throat area may be maintained over a given vector directional range of the vanes. The outlet may be generally rectangular in cross-section and a strut may be mounted across the outlet perpendicular to the pivot axes of the vanes to house the rod, drive members, and/or coupling members.

Abstract: This is a relatively simple load-lifting apparatus, tongs-like in appearance with a larger lower portion for grabbing loads of various sizes. It has two embracing halves, pivoted at a selected distance from the apparatus' top. It is designed to safely and reliably hold a person between its lower portions, without injuring one who may be disabled. Sensors have been added to enable it to sense the distance of the apparatus' lower portions from the object to be scooped up. When in range of the object its lower portions automatically separate, in order not to make contact with it, while being lowered. In its descent the apparatus could sway under the influence of wind gusts, thus not being able to precisely straddle the object to be retrieved. A technique using air bursts from solenoid-operated valves, mounted selectively on the apparatus to reduce the effect of wind-gusts, is provided. Compressed-air tanks are provided to supply the air to the valves.

Abstract: A ramming brake is provided for use with a projectile launched from the barrel of a gun having a tapered portion. The ramming brake includes a braking ring that has a tapered surface configured to wedge into a tapered portion of the gun barrel. In a particular configuration, the braking ring wedges in the tapered breach of the gun barrel. The ramming brake further includes a retaining mechanism that is used to couple the braking ring to the projectile. This retaining mechanism restrains and controls the movement of the projectile after the braking ring wedges into the tapered portion of the barrel.

Abstract: A hybrid deicing system for deicing ice or snow covered surfaces comprises a source of pressurized air and a source of pressurized deicing fluid. A nozzle assembly receives the pressurized air and the pressurized deicing fluid at a forward position, a middle position or a rearward position of the nozzle assembly. The nozzle assembly discharges the pressurized deicing fluid and pressurized air as a first independent stream within a second independent stream.

Abstract: A door assembly for a landing gear of an aircraft. The door assembly comprises a door section that in turn has two panels, moveable between closed and open positions by a positioning section. In one embodiment, the positioning section comprises mounting arms fixed to the panels which are connected by parallel linkages and which move the panels in a rotational path from a closed position aligned with the door opening through a path of rotation to a location spaced laterally of the door opening, with the panels being in proximity with another and these partially overlapping. In another arrangement, the inside surfaces of the panels face one another in the open position, and the panels are hinge mounted to one another.

Abstract: The invention provides camouflage in both the visual spectrum and the infrared spectrum by emulating the infrared radiation of an object's background and the visible radiation of an object's background, effectively cloaking the object from detection. Initially, the temperature and color of the background against which an object appears is determined. The external surface of the object, or alternatively a shield around the object, is then heated or cooled using thermoelectric modules that convert electrical energy into a temperature gradient. The ability of the modules to be either cooled or heated permits the output of the modules to be altered to match the temperature of an object's background. In combination with these thermocouples, the invention utilizes choleric liquid crystals to alter the visible color of an object.

Abstract: A basket for supporting equipment between a pair of laterally spaced-apart parallel overhead cables. The basket is provided in the form of a top open container insertable between the overhead cables. A carrying member engageable with a helicopter arm is provided for allowing the basket to be selectively transported between and away from the overhead cables. A pair of wing-like members extend laterally outwardly from opposed side walls of the container for resting on the overhead cables once the basket has been lowered to a suspended position between the overhead cables.

Abstract: A trim actuator for actuating mechanical controls in an aircraft flight control system in response to signals from a pilot having a stepper motor, a gear train member coupled to the stepper motor, an output member coupled to the gear train member. The trim actuator has a locked mode in which the mechanical controls are held in a fixed position relative to the aircraft, and a non-interference mode in which the mechanical controls are free to be moved by the pilot without interference from the aircraft flight control system. The non-interference mode and the locked mode are both achieved by the stepper motor.

Abstract: A method of injecting a missile, having a solid fuel motor, into a satellite orbit. The method includes determining an along-track displacement and cross-track displacement with respect to the satellite orbit. The method also includes determining a velocity-to-be-gained for the satellite orbit, with respect to the current missile velocity. Along-track and cross-track wasting of the solid fuel motor are used to reach the satellite orbit, at the proper velocity for the satellite orbit, when the solid fuel motor burns out.

Abstract: A cascade thrust reverser for use with a mixer/ejector noise suppressor has a set of internal blocker doors controllably moveable between a stowed position, where engine exhaust passes through and out the tailpipe, and a deployed position, where engine exhaust is blocked and redirected out a pair of cascades or louvers. External cascade doors cover the cascades from the outside during flight, but are moved aft, exposing the cascades, when the blocker doors are deployed subsequent landing. In a preferred embodiment, the cascade doors and the blocker doors are interconnected through a pair of actuation mechanisms, whereby movement of the cascade doors is sequenced to the motion of the blocker doors. The blocker doors and the cascade doors are shaped to provide a clean aerodynamic profile when stowed, so that the noise suppressor functions optimally. The actuation mechanisms also preferably include lock mechanisms for only allowing the thrust reversers to be deployed just subsequent landing.

Abstract: A continuous three axes satellite pointing system for a solar powered satellite, the system comprising a body control module for producing three orthogonal axes body control torques, a momentum integration module, a momentum control module, and a program torque decoupling module. The program torque decoupling module de-couples the programmed motion parameters represented by the equation: IB&ohgr;′+B&ohgr;X(IB&ohgr;+BH).

Abstract: The subject of the invention is a translational braking device for a projectile during its trajectory comprising at least two airbrakes that are radially deployable so as to increase the projectile's aerodynamic drag. Each airbrake is a flap pivoting around a pivot integral with the projectile and parallel to its axis. The device incorporates at least one pyrotechnic piston locking at least one of the flaps in its folded position and at least two flaps are stacked one on top of the other when they are in their folded position, at least a first of the two flaps incorporates a mechanism to retain the second of the two flaps in its folded position.

Abstract: A method is disclosed for controlling the attitude of a satellite by controlling the speed of the gimbals of CMGs in a cluster of CMGs, the CMG having respective wheels mounted on gimbals that are mounted on a satellite platform to rotate about different orientation axes. From starting conditions and end conditions relating to attitude and angular speed and time, a cluster configuration is determined that is remote from any singular configuration such that exchanging angular momentum between the cluster of CMGs and the satellite during a given length of time will give rise to the desired attitude maneuver. The orientation of each gimbal is changed in simultaneous and independent manner into its reference orientation by using an angular position reference, applied in an open loop in the local servo-control of the angular positions of the gimbals.

Abstract: A method, apparatus, article of manufacture, and a memory structure for controlling the eccentricity of an orbit. One embodiment of the present invention is described by a method comprising the step of performing a program of eccentricity control maneuvers wherein the control maneuvers are executed at times and in directions selected to apply substantially all eccentricity control along a line of antinodes. In one embodiment, the control maneuvers arc tangential maneuvers, and each control maneuver is applied near the line of antinodes. Provision is made for performing additional maneuvers, including node retargcting maneuvers during specified intervals. Another embodiment of the invention is described by a satellite in a substantially geosynchronous orbit having a satellite control system with a processor implementing instructions to perform control maneuvers as described above.

Abstract: Apparatus for generating vortices to control the flow of air across a airfoil of an aircraft includes a series of pressure active regions arranged along the leading edge of the airfoil. The pressure active regions include spaced apart valves connected to a source of vacuum, a controller for activating the valves, and sensors for sensing air pressure. The controller is configured to activate the valves in response to the pressure sensed by the sensors, wherein the spaced apart valves are connected to a source of pressurized air as well as to the source of vacuum.

Abstract: An aircraft flap drive system utilized a variable displacement motor (15) having a fluid pressure actuated device (23) to vary the displacement of the motor. The system includes a displacement control valve (41), and an electrohydraulic control means (55,67,85) operable in response to an electrical input signal (91) to communicate pressurized fluid from a source (11) to the motor. The displacement control valve (41) includes a load sensing arrangement (13,53,49) responsive to an increasing load on the motor to bias the displacement control valve toward a position whereby the motor moves toward its maximum displacement (minimum flow). One result is that the conventional fixed displacement motor, of a particular size and weight, may be replaced by a variable motor which is smaller and lighter.

Abstract: An aircraft weapons bay acoustic suppression apparatus is disclosed. The apparatus reduces or eliminates acoustic resonance within an open cavity of an aircraft such as a weapons bay of an aircraft in flight. The apparatus includes an oscillatable spoiler plate which is extended into the airstream. At least one shaker is placed in operative engagement with the spoiler plate in order to oscillate the spoiler plate at high frequencies and high amplitudes to seed the shear layer with frequencies which directly complete with the natural frequency of the shear layer vortices. In this way, the damage arising from natural shear layer vortices can reduced or canceled within the weapons bay.

Abstract: A spacecraft comprised of a plurality of functionally organized, fully independent modules. Selected ones of the modules are moveable foldably in a “clamshell”-like manner between assembled positions, wherein various components of the spacecraft are generally not readily accessible, to a service position in which virtually all of the components of the spacecraft are substantially readily accessible for service or testing. Logically organized and routed harnesses comprised of numerous electrical and mechanical elements enable the clamshell-like folding movement of selected modules. Conventional electrical and mechanical connectors associated with the harnesses permit quick detachment and complete removal of selected modules from the spacecraft.