Abstract: A reorientation controller for a satellite includes a slew rate command generator that generates a slew rate command signal ({right arrow over (?)}r—cmd) in response to an attitude error signal. The attitude error signal corresponds to the difference between an initial attitude and a target attitude. The slew rate command generator may introduce a phase lead (?L) into the slew rate command signal ({right arrow over (?)}r—cmd). The controller may perform a spin phase synchronization when the target attitude is unsynchronized in spin phase with the initial attitude. The satellite may perform a reorientation maneuver in response to the slew rate command signal ({right arrow over (?)}r—cmd).

Abstract: An electronically controlled pneumatic paintball gun, comprising means for monitoring and/or controlling one or more parameters of the gun's operation and alphanumeric display means for displaying data related to said monitoring or control on a display panel integral with the gun.

Abstract: An aircraft, comprising a fuselage having an elongated, narrow forward portion, a main wing carried by a rear portion of the fuselage, a canard wing carried by said fuselage forward portion and having swept back leading and trailing edges tapering toward a tip or tips, the canard wing having less lifting surface than the main wing.

Abstract: A baggage compartment includes a support structure, a bin, and a guide. The bin defines an at least partially closed volume configured to store baggage. The guide connects the support structure and the bin. The guide is configured to move the bin along a first portion of a path linearly and a second portion of the path rotationally.

Abstract: A cavity is provided on the leading edge of an object that is subject to the flow of liquids or gasses, where said cavity preferably has a wall that follows the curvature of a diminishing sine wave, although other configurations are possible that do not follow a specific sine wave. The cavity accepts the flow of liquids or gasses that enter into the cavity, and where the dimensions of the cavity cause the flow of liquids or gases within it to form a pressure node that extends forward of the cavity. The pressure node provides a wedge means to cause oncoming gasses or liquids to divert around the object body ahead of the object body itself, decreasing turbulence around the periphery of the object. The cavity may be spherical, in the instance of a missile, plane, or underwater transportation means, or may be linear, in the instance of an automobile grill that is subject to wind, or a bridge support, where the bridge support has to maintain position against the flow of current.

Abstract: A system and apparatus for deployment of a decoy from a moving object, such as an aircraft, to protect the aircraft from an enemy missile. The decoy is stored in a housing mounted on the aircraft and is connected by a cable containing fiber optics and high voltage conductors. The cable is stored on a spool which is reciprocally moveable along a rotating shaft provided with a double helix and which is located coaxially within an outer rotatable de-bailer. The cable is drawn through a passage formed in an outer cylindrical side wall and end wall of the de-bailer as the decoy is deployed from the aircraft. The cable causes the de-bailer to rotate about the spool which reciprocates back and forth along the double helix shaft. The spool is connected to the helix of the shaft by a pawl and a brake mechanism controls the rotational speed of the shaft, and thus the payout speed of the cable.

Abstract: Methods and systems for performing landing gear operations. In one embodiment, a method for retracting a landing gear is useable with an aircraft having a gear door that at least partially covers a gear well when the landing gear is extended. The method can include receiving a first signal during movement of the aircraft down a runway for takeoff. The first signal can correspond to at least a first aspect of motion of the aircraft, such as upward rotation of the aircraft for liftoff. The gear door can be opened in response to receiving the first signal. The method can further include receiving a second signal after the aircraft has lifted off of the runway. The second signal can correspond to a second aspect of motion of the aircraft, such as the aircraft achieving a positive rate of climb. In response to receiving the second signal, the landing gear can be retracted into the gear well.

Abstract: An electro-hydraulic thrust reverser lock actuation system includes a hydraulic fluid source and a lock actuator assembly that is configured to selectively pressurize the hydraulic fluid. The lock actuator assembly is adapted to receive a lock control signal and, in response, pressurize the hydraulic fluid in the hydraulic fluid source. One or more lock assemblies are in fluid communication with the hydraulic fluid source and are configured, in response to the hydraulic fluid pressurization, to move to one of a locked or an unlocked position.

Abstract: A stable heli-borne vector platform capable of accepting a range of different sensors or instruments, particularly, but not exclusively, for the mapping and exploration of mountainous regions is described. The platform enables the arrangement of the sensors in three orthogonal directions, thus allowing the restitution of the resultant vector. The geographical referencing is provided by the use of a differential GPS receiver, whose antenna is installed on the main body of the platform. This platform distinguishes itself from its predecessors through the use of a lateral pulling axis, the use of a heavy weight placed underneath the main body, and by a perfectly symmetrical geometry in the direction of pull, thus ensuring perfect in-flight balance and stability.

Abstract: A thrust reverser includes forward and aft louvers pivotally mounted in a compartment defining a flow tunnel through the outer and inner skins of a fan nacelle. An aft flap is integrally joined to the aft louver for rotation therewith. A unison link joins together the forward and aft louvers. And, an actuator is joined to the louvers for rotation thereof between a stowed position in which the louvers and flap are closed in the nacelle skins and a deployed position in which the louvers and flap are pivoted open from the skins.

Abstract: An omni-directional air vehicle having a pod with a connected turbofan system, the pod has a body that contains a power source for generating electrical power and a ducted fan with spherical articulation mechanism having a projecting arm with counter-rotating propellers and a ducted shroud around the periphery of the counter rotating propellers and containing drive motors for electrically driving the propellers.

Abstract: A mobile platform lift increasing system includes at least one wing-shaped structure having a leading edge, a trailing edge and a chord length perpendicularly measurable between the leading and trailing edges. A rotatable control surface is located near a trailing edge undersurface. The control surface length is approximately one to five percent of the chord length. A deployment device is positioned between the wing shaped structure and the control surface. The deployment device operably rotates the control surface through a plurality of positions ranging between an initial position and a fully deployed position. Wing lift is increased at speeds up to approximately transonic speed by continuously rotating the control surface to accommodate variables including mobile platform weight change from fuel usage.

Abstract: The present invention provides a balance load actuator for effecting motion between a first part and a second part. An embodiment of the present invention comprises a main housing; a shaft; a motion transfer assembly; and a load balancing assembly. The balance load actuator receives substantial external loads through a load balance assembly and distributes the loads to the main housing, thus relieving undue stress otherwise exerted on the shaft and enabling lighter and smaller design components and construct.

Abstract: Integrated glass ceramic spacecraft include a plurality of glass ceramic components including molded, tempered, annealed, and patterned glass ceramic components coupled together for forming a support structure or frame or housing through which is communicated optical signals through an optical communications grid and electrical signals through an electrical communications grid, with the optical communications grid and electrical communication grid forming a composite electrooptical communications grid for spacecraft wide intercommunications. The support structure multifunctions as a frame, a housing, a support, a thermal control system, and as part of an electrooptical communications grid while encapsulating a plurality of optical, electronic, electrical, and MEMS devices between which is communicated the electrical and optical signals over the electrooptical communication grid.

Abstract: A system for launching a space for humans into orbit comprises a launch vehicles. There are multiple separate crew modules mounted in relationship to the launch vehicle. The multiple crew modules are nested around the circumference of the launch vehicle. Alternatively or additionally, there are multiple separate crew modules located in a pod relatively directed along the length of the launch vehicle. A single rocket is for launching the multiple space crew modules. The separate crew module return from orbit to Earth separately.

Abstract: In one embodiment the present invention includes a landing gear for an airplane comprising a plurality of connectors coupled to the airplane; a first support member coupled to at least one of the plurality of connectors; a second support member pivotally coupled to the first support member; a third support member pivotally coupled to the second support member; a wheel coupled to the third support member; a bell crank coupled to the third support member; and a link system coupled to the bell crank; wherein the third support member folds back upon the second support member and moves aft upon retraction of the landing gear into the airplane.

Abstract: The drogue 11 comprises a canopy 50 supported by a plurality of adjustable ribs 42 and further ribs 43. A control unit 36 is provided for moving the adjustable ribs 42 into a first position P1, in which an air stream can inflate the canopy 50 whereby drag on the canopy causes the drogue 11 to draw a fuel hose 74 from a tanker aircraft 63 into an extended position, and into a second position P2 in which the canopy 50 takes on a cylindrical form and drag thereon in the extended position will be reduced. Selected adjustable supports are movable relative to the others by a control mechanism 41 to adjust a selected portion of the canopy 50 whereby the drag on that portion will be increased and the drogue 11 will move to a new position.

Abstract: An aircraft adapted for covert deployment and having low vulnerability to hostile detection and aggression is provided. The aircraft includes a fuselage having a pair of sidewalls and a bottom. The sidewalls and bottom form an armored payload bay. The aircraft additionally includes a pair of wings connected to the fuselage. The wings have a fixed wingspan constrained such that the aircraft can be transported within a larger aircraft. This allows for the aircraft to be aerial deployed from the larger aircraft. Each of the sidewalls include at least one pulse ejector thrust augmentor (PETA) bank that is canted outward. Therefore, a thrust exhaust produced by each PETA bank is directed down and away from a centerline of the payload bay. Furthermore, the bottom of the aircraft is adapted to allow ingress and egress of cargo, e.g. military troops, from the payload bay.

Abstract: A compressed gas powered gun provides recoil simulating the recoil of a gun firing gunpowder propelled projectiles. The valve assembly provides both consistent shot to shot pressure, and rearward gas pressure for generating recoil. Preferred embodiments of the compressed gas powered gun may include means for adjusting the amount of recoil provided. A trigger mechanism permitting semi-automatic operation, or full automatic operation at a user selectable cyclic rate, is provided. The air gun provides consistent gas pressure behind the projectile from shot to shot. A magazine and magazine indexing system for loading projectiles into the firing chamber in a manner contributing to the accuracy of the air gun is also provided.

Abstract: The present invention provides an environmental control system for an aircraft attendant or crew rest ventilation system. The system provides primary and secondary sources of air to the crew or attendant rest. A pressure sensor within the supply duct determines whether air from the primary duct is within desired pressure limits and controls operation of the ducts accordingly. Additional features related to temperature control and ventilation are also provided.