Abstract: A cushion, preferable of a buoyant material, includes a layer of threat-resistant material for precluding penetration by a projectile from a firearm or sharp edged or sharp pointed instrument and serves in the manner of a shield to prevent injury to a person's shielded body parts. The threat-resistant material may envelope the cushion, be disposed on either the front or the back side or be interleaved between the front and back sides. One or more straps may be disposed on a side to facilitate manipulation in positioning of the cushion to render it most effective to ward off an attack.

Abstract: A joint is provided for unfolding systems, e.g. for satellite solar generators that permits sufficiently large unfolding torque, low weight and small dimensions. A drive on one joint half acts on a small pulley to wind a cord on it. The other end of the cord is tautly connected to a large pulley that rotates on the hinge pin and is fixed to the second joint half. The large pulley rotates in the opposite direction of the small pulley when the cord is wound so that the second joint half folds away from the first joint half on the hinge pin into an unfolded state and is held In this state by a stop against the tension of the cord. The joint is used, for example, for unfolding joints for satellite solar generators that consist of two joint halves, a hinge pin and a drive.

Abstract: A satellite energy and attitude control system includes a first energy wheel, a second energy wheel and a third energy wheel. The first energy wheel is mounted in a first double gimbal and the second energy wheel is mounted in a second double gimbal. The third energy wheel is mounted in a third double gimbal and the first, second and third energy wheels, which have at least two degrees of motion orthogonal to their respective spin axes, are located within a single plane and positioned with respect to each other such that the total angular momentum provided by the first, second and third energy wheels sums to zero approximate an operational range center of the gimbals.

Abstract: A kite has a support frame and a waterproof fabric covering the support frame. The support frame has a levelling rod, a center spine passing through the levelling rod, a head rod disposed on a front of the center spine, a hollow joint disposed on the center spine, a first front rod and a second front rod connected to the hollow joint, a first positioning block disposed on the hollow joint, a second positioning block disposed on the hollow joint, a first connector disposed on the first front rod, a second connector disposed on the second front rod, a first extended bar connected to the first connector, a second extended bar connected to the second connector, a first connection rod connected to the second extended bar and the first front rod, and a second connection rod connected to the first extended bar and the second front rod.

Abstract: An aircraft flare control system for semi-automatically controlling the pitch and thrust of an aircraft during landing is disclosed. The system includes a flight director and indication of the pitch angle of an aircraft during a landing maneuver and a flare computer. The flare computer includes a control law defining a predetermined pitch angle of the aircraft as a function of height above ground level. The system also includes a radio altimeter connected to the flare computer for producing a signal indicative of the height of the aircraft, a signal of pitch deviation from the control law is generated to allow a pilot or auto-control to adjust the pitch to comply with the control law. A thrust control for retarding the throttle as a function of altitude above ground level is also provided.

Abstract: A passenger aircraft so arranged that complete partition wall(s) is/are disposed in the manned space (e.g. a flight deck and a passenger cabin) of the aircraft fuselage so as to completely partition the manned space into at least two manned space sections which are completely isolated from each other. Hence, any hijacker is prevented by the partition wall(s) from his or her access to the manned space. Further, doors and lavatory are provided in the aircraft at points corresponding to such at least two isolated manned space sections, so that pilots, crews, flight attendants and passengers may not only find their own ways for egress from the aircraft and ingress thereto, but also have a wash and relieve themselves, for instance.

Abstract: The present invention provides a temperature control system for an aircraft ventilation system that couples with existing aircraft upstream ventilation system architecture and downstream ventilation system architecture. The temperature control system includes an air duct arranged to receive a volume of ventilation air from the upstream ventilation system architecture and transfer the volume of air to the downstream ventilation system architecture. At least one heater is interposed within the duct and is arranged to heat the ventilation air. Additionally, at least one temperature sensor that is in thermodynamic communication with the volume of air within the duct is located downstream from the at least one heater and is arranged to determine an actual temperature of the ventilation air. A controller is in electrical communication with the at least one heater and the at least one temperature sensor. The controller is programmed with a predetermined range of temperatures above the freezing point of water.

Abstract: A one-piece wrap around fin for a projectile which includes a main portion, a first end and a second end. The main portion has at least one flap. The first end and the second end cooperate such that the fin is circumferentially mountable around the projectile.

Abstract: In order to provide that the braking elements (16), which are to be deployed radially under the effect of centrifugal force, of the braking arrangement in the region of the ogival head of a spin-stabilized artillery projectile (12) are secured in the rest position and can then be released in a defined manner when reaching the braking point of the ballistic trajectory, the stowage space (14) for accommodating the braking elements (16) is radially covered by a hood (22) which is fitted on to the projectile fuse (11) in the afflux direction and is axially fixed between a recess (24) in the rear wall (25) of the stowage space and a front-end holding ring (26) connected to the ogival head.

Abstract: The invention provides a deployable radiator for a space vehicle such as a satellite. The radiator of the invention has two radiating faces, one of which is insulating over a portion of its area so that during launch and while the satellite is being moved onto station, with the radiator in the stored position, it naturally serves to keep the highest possible temperature on board the vehicle.

Abstract: A returnable and reusable space vehicle including a main body separate from and releasably mounted to a booster rocket assembly. A crew compartment module is provided that is separate from and releasably mounted to the main body. A propellant system is operably coupled to the crew compartment module so as to propel the crew compartment module from the main body during an emergency procedure. An orientation control system is coupled to the propellant system such that the orientation control system maintains the crew compartment module in a predetermined attitude during the emergency procedure. A pair of aerodynamic lifting wings extend from the main body to provide aerodynamic lift the the main body to permit the main body to return from the orbit and land.

Abstract: A data network includes a plurality of network devices spaced apart from one another and distributed at multiple locations, a plurality of cables each coupled to a respective one of said plurality of network devices by a respective one of a plurality of first connectors, and a network hub including a second connector coupled to each of said plurality of cables. The network hub also includes a removable and replaceable termination element that mates with the second connector to provide signal connectivity between selected ones of said plurality of cables. The removable and replaceable termination element couples each of the plurality of cables to another of the plurality of cables such that any signal transmitted on the plurality of cables by the plurality of network devices both enters and exits said network hub at said second connector.

Abstract: A method and apparatus for actuating an aircraft nose portion. The aircraft can have a longitudinal axis and a pitch axis generally transverse to the longitudinal axis. The fuselage can include a pressure bulkhead and a pressurized payload portion aft of the pressure bulkhead. The nose portion can be positioned forward of the pressure bulkhead and can be changeable from a first configuration to a second configuration while the pressurized payload portion is capable of being pressurized relative to a region external to the aircraft. For example, the nose portion can be inclined upwardly relative to the longitudinal axis when pivoted from a first position to a second position. Accordingly, the length of the aircraft can be reduced, for example, to accommodate the aircraft at a loading gate or other ground support area.

Abstract: A flexible, rotatable, removably detachable tie-out system configured to mount easily for set-up, adjustment, storage, and the like on horse trailers or other structures. The tie-out system includes a base. Coupled to the base is a receiver configured to both receive a connector and allow rotation of the same therein. The connector is coupled to a tie-out that includes a flexible portion, the flexible portion configured to both allow substantially universal motion of the tie-out and dampen the pulls and tugs of an animal, while preventing damage to a trailer or other structure, the tie-out, and the animal. The tie-out may be rotated and stored attached to or removed from a trailer while traveling. Furthermore, by having additional bases and receivers mounted where convenient, a detached tie-out may be moved to multiple sites on the trailer or to a building or other structure as the need arises.

Abstract: The optimal control design for antiskid brake control uses a discrete Kalman filter scheme in combination with a conventional aircraft brake control system, comprising sensors for measuring a speed of a wheel and brake torque, and for providing output signals indicative of the speed and torque values, and an optimal antiskid braking controller. The optimal antiskid brake controller includes a wheel speed filter, a reference velocity module, an optimal controller, and an integrator module. The optimal controller includes a discrete Kalman regulator utilizing a discrete Kalman filter, which compels the wheel velocity to quickly converge to the reference velocity, while the integrator produces appropriate antiskidding control and compensates for low frequency torque disturbances. The discrete Kalman filter estimates brake pressure, and the difference between the wheel velocity and a reference velocity, and these estimated states are regulated by a control feedback gain matrix.

Abstract: A door lock system for an airplane is operative to alternately operate spaced doors to provide controllable entry into a restricted area located between the spaced doors.

Abstract: An aircraft refueling boom load alleviation system uses received light to detect boom displacement and generates a control signal to correct the displacement. Both a set of flight surfaces and a plurality of light imageable targeting sights are disposed on a refueling tube. At least one digital camera converts the light imageable shape of each of the targeting sights to individual pixel images. The pixel images converted by the digital camera are input to a computer system. The computer system recognizes either a displacement of pixel images or a quantity change of pixels between pixel images as a displacement of the refueling tube. The computer system calculates the displacement of any of the pixel images. A signal is generated to control the refueling tube flight surfaces to correct the displacement.

Abstract: A missile 1 with a missile attachment 2 according to this invention. The missile attachment 2 consists of a tube 3 with a protruding section 4. The protruding section 4 has a concave forward facing surface area 5. The concave curvature is such that it is noticeable when the protruding section 4 is at the highest position on the tube 3. The tube is in the form of a cylindrical tube and is fitted to the missile 1 so that it encircles part of the missile and such that it can rotate continuously relative to the missile 1 during flight of the missile.

Abstract: The invention is a new pet blanket that drapes around an animal in an outdoor kennel. The invention is installed in a pet kennel or animal enclosure. It comprises bundles of fabric that are attached to a platform or attached directly to the ceiling of a kennel. The attachment means comprises a Velcro® connection means or a mechanical safety snap connection means. The blanket fabric may be cotton, wool, a synthetic blend, or other suitable material, shaped into strands and gathered into bundles. The bundles of fabric hang down loosely from the ceiling or supporting platform, to within one to three inches from the floor of the kennel or animal stall. The bundles of fabric are spaced to allow the animal to move about freely in the kennel. At the same time, the bundles of fabric automatically provide a blanket that shelters the animal from the outside elements.

Abstract: The Rotational Canted-Joint Missile (RCJM) Control System utilizes a single or multiple body joints that rotate in planes that are not perpendicular to the missile body axis. The result is the deflection of a portion of the missile body for flight control purposes. The canted interface plane between any two adjacent movable sections of the missile body and a joint at the interface plane that allows one of the sections to be rotated by a pre-determined angle with respect to the other section comprise a rotational plane mechanism that offers an inclined bearing plane with a large mechanical advantage over typical “brute force” ball joint methods.