Abstract: A VTOL aircraft having a fuselage, a first wing extending from one side of the fuselage, a second wing extending from an opposite side of the fuselage, a first thruster supported on the first wing, a second thruster supported on the second wing and a propulsion system connected to the fuselage. The first thruster serves to direct a thrust of air at an angle toward an area directly below the fuselage. The second thruster is angularly directed so as to direct the thrust of air at an angle toward the area directly below the fuselage. The propulsion system serves to propel the fuselage through the air. Each of the thrusters is a jet engine. Each of the thrusters can be angularly moveable between a vertical position and an acute angle with respect to a plane of the wings.

Abstract: A projectile and a method of launching a projectile from a barrel. The projectile of the present invention may be matched to a pre-selected barrel rifling to produce a controlled spin rate. Controlled spin rate is characterized by substantially balanced forward and axial deceleration. Substantially balanced forward and axial deceleration is characterized by an axial speed that decreases in relationship to the decrease in forward speed. Substantially balanced forward and axial deceleration produces a trajectory that is characterized by a gyroscopic stability factor that remains highly stable over a given distance of a trajectory. Gyroscopic stability is controlled during the projectile's flight by controlling the spin damping moment as a design element. Control of the spin damping moment may be achieved by incorporating physical features in the projectile's design and manufacture and/or may result from the incorporation of physical features imparted upon the projectile during launch.

Abstract: A parachute system operable with a drogue parachute includes a bridle and kill line connected to a deployment bag at one end and to the drogue parachute at another. The bridle includes a stop carried within the parachute container for suspension of the parachute container by the drogue parachute during free fall. A plate is carried within the parachute container for securing the stop when the flaps are in a locked and closed position by a closing member and ripcord. The ripcord includes a ripcord pin and a ripcord line passing through an eyelet of the ripcord pin and attached at a fixed end to the parachute container for providing a pulley effect and thus a mechanical advantage when the free end of the ripcord is pulled. The ripcord further includes left and right lines carried within a housing and an elastic cord between their free ends for biasing ripcord handles against the ripcord housing.

Abstract: The present invention provides an unmanned airborne reconnaissance vehicle having a fuselage, a forward wing pair and a rearward wing pair vertically separated by a gap and staggered fore and aft therebetween such that a general biplane configuration is formed. The present invention provides a pair of wing tip plates for joining the wing tips of the forward and rearward wings. The unmanned airborne reconnaissance vehicle of the present invention includes a power plant to propel the vehicle through the air and a generally T-shaped tail having a vertical stabilizer including a rudder and a full span elevator.

Abstract: The present invention provides a maneuver device for an artificial satellite, which causes small attitude error during maneuver and which requires a shorter period of setting time for obtaining a target attitude. The maneuver device is provided with: a feed forward torque instruction signal generator 8 which outputs a feed forward torque instruction signal 11 based on a maneuver plan; a thruster 10 which outputs control torque based on the feed forward torque instruction signal 11; and an attitude control signal calculator 6 to which an attitude angle and an angular velocity of the artificial satellite as well as a target attitude angle and a target angular velocity are input and which outputs an attitude control signal 13. The maneuver device is further provided with a disturbance compensating signal calculator to which the feed forward torque instruction signal 11 and a detected angular velocity signal 16 are input, and which generates and outputs a disturbance compensating signal 12.

Abstract: Movable surface planes include opposed independently movable endless surfaces over the majority of opposite sides of the planes. By moving one surface in the same direction as the fluid flow about the plane, and the opposite surface in a direction opposite the fluid flow, the flow is accelerated across the surface moving in the same direction to produce a lesser pressure, and retarded across the surface moving in the opposite direction to produce a greater pressure. The net result is a force urging the plane toward the surface moving in the direction of ambient fluid flow. The two surfaces of the present invention may be operated independently of one another, to move in the same or opposite directions and to have the same or different velocities. The movable surfaces are porous and communicate with ductwork within the structure, to provide fluid flow through the surfaces for boundary layer control.

Abstract: A novel drive for a lifting platform utilizing a simple propeller, impeller, or gas turbine is disclosed. The axial air rotation from the drive is eliminated in order to permit the development of a partial toroidal vortex which efficiently maintains a raised air pressure zone beneath the lifting platform. The axial components are eliminated by means such as flow straightening vanes, which may also serve to control lateral motion of the lifting platform. The system can also be easily modified to function as an attractor device. Overall, the present invention explores the effect of vortices, both cylindrical and toroidal, and seeks to optimize their effects.

Abstract: A failsafe arrangement comprising a first mounting member and a second mounting member which is angularly moveable relative to the first mounting member. The first and second mounting members define first and second surfaces respectively which define therebetween a channel, the first and second surfaces being shaped such that the channel is of non-uniform width. At least one wedge member is disposed within the channel, the or each wedge member being carried by a drive member and being arranged such that, in use, when the drive member and the second mounting member move at substantially the same angular speed, the wedge member does not impair movement of the second mounting member relative to the first mounting member, relative angular movement of the drive member and the second mounting member causing the wedge member to cooperate with the first and second surfaces to apply a braking force so as to impede relative angular movement of the first and second mounting members.

Abstract: A flyback booster (200) comprising an aircraft (203) housing a launch vehicle stage as a removable rocket propulsion module (502) and several space launch vehicles using variations of the flyback booster (200) are disclosed. This flyback booster (200) functions as the first stage of a multistage space launch vehicle. The stage used in the flyback booster (200) and the upper stages of the multistage space launch vehicle (213) are selected to optimize the launch cost for a specific payload.

Abstract: A vibration isolator is provided that includes a plurality of elastomeric members. The vibration isolator includes a first support, a second support and at least one third support. The second support is spaced from the first support such that the first and second supports define at least one recess. The at least one third support is spaced from the first support such that the third support and the first support define at least one recess. The recesses between the first and second supports and the first and third supports are structured to at least partially receive at least one of the elastomeric members. The vibration isolator includes at least one fastener that is structured to mount the corresponding elastomeric members between the first and third supports and between the first and second supports such that elastomeric members damp vibration transmitted between the first and second supports.

Abstract: An unmanned air vehicle (UAV) having a ducted fan configuration with a propeller mounted inside of an opening that extends longitudinally through a fuselage. A gyroscopic stabilization device is attached to the propeller shaft such that rotation of the propeller shaft also results in rotation of the gyroscopic stabilization device. The gyroscopic stabilization device has sufficient mass and rotates at a sufficient angular velocity such that the aircraft is gyroscopically stabilized during flight. In one embodiment, the gyroscopic stabilization device comprises a ring mounted to the outer tips of the propeller and in another embodiment is comprised of a disc.

Abstract: A method and means are provided for extending the life of carbon brakes on aircraft. The method comprises measuring the speed of the aircraft and the intensity of braking and comparing these to predetermined maximum values for each. If the values are both lower than the maximum values, one or more of the brakes are selectively disabled.

Abstract: The present invention relates to a device suspended from a carrier craft for the recovery of persons or items of equipment, of the type comprising a connection (21) joining the craft to a foldable and deployable pod (20) formed by a framework associated with a flexible support (23). The framework includes, fixed to the connection (21), a central mast (2, 3) connected to mobile means (4, 6) bearing the flexible support (23), to ensure the folding and deployment of the mobile means and of the flexible support around the central mast. Application to the rescue of persons in danger from a helicopter.

Abstract: Attitude determination and control systems are provided that combine attitude measurements from all spacecraft payloads to determine a master attitude estimate for a master payload and relative slave attitude estimates for the remaining slave payloads. These estimates are then used to control the attitudes of spacecraft elements that correct the absolute and relative attitude errors. These systems significantly enhance attitude accuracy when compared to systems that realize independent payload estimates, determine payload attitudes. These systems also provide significant processing advantages (e.g., simpler algorithms, reduced data throughput and slower processing rate).

Abstract: Boarding device for aircraft and flying wings equipped with such a device. The boarding device consists of at least one tunnel (20) connected to the outside of the aerodynamic shell (12) of the aircraft. More precisely, the tunnel is attached to the trailing edge of the fairing (12) and it extends aft approximately parallel to the longitudinal axis of the aircraft. A door (22) closes off the opening between the passenger cabin (10) and the tunnel (20). The rear part (26) of the tunnel (20) is articulated and/or detachable. In order to evacuate the passengers in an emergency, the front, fixed part of the tunnel (24) can be fitted with an inflatable escape slide or an articulated floor.

Abstract: A flight control system includes a lift control algorithm which selectively communicates with the pitch command of the flight system control algorithm. The lift control algorithm selects the proper control commands to coordinate an effective transition between hover and forward flight. The most efficient vehicle pitch during transition is thereby automatically generated so that sufficient lift and control throughout the transition between rotor borne and wing borne flight.

Abstract: The present invention is directed to spacecraft that have, for any reason, lost the spacecraft's service attitude that permits it to carry out the service operations for which it was designed. The invention provides methods and structures for acquiring and determining a power-safe attitude (i.e., one in which wing current is sufficient to support the spacecraft's housekeeping operations) from which the spacecraft can be subsequently returned to a service attitude. The methods are particularly useful because they a) require only a single star tracker for sensing attitude, comprise simple maneuvers, and typically acquire a power-safe attitude that does not significantly differ from the spacecraft's service attitude to thereby reduce the spacecraft's return-to-service time.

Abstract: A security screen device for protecting persons and property is provided. The security screen device comprises an enclosed screen housing defining a screen receiving area. A screen material made of high strength fibers is receivable within the screen housing in an undeployed condition with the screen material having a first edge and a second edge. The first edge is secured within the screen receiving area and a weighted bar is secured to the second edge of the screen material. An activation mechanism opens one side of the screen housing releasing the screen material from the housing into a deployed condition such that the second edge of the screen material travels in a direction generally away from the enclosed screen housing thereby pulling the screen material from the enclosed screen housing.

Abstract: An air inlet cowl for a jet engine, particularly an aeroengine, includes a leading edge deicer, a hollow leading edge defining an internal peripheral chamber, closed by a first internal partition, and an exhaust orifice, in the leading edge, connecting the internal chamber with the outside. The cowl further includes a pressurized hot air feedpipe for being connected, at its rear end away from the leading edge and passing through a second internal partition, to a pressurized hot air circuit and, at its front end toward the leading edge, to an injector of pressurized hot air into the internal chamber, a protective internal casing functioning with the first and second internal partitions to define an isolation volume enclosing the feedpipe, and an air extraction opening, in the first partition, to place the isolation volume in communication with the internal peripheral chamber.

Abstract: In a method and apparatus for reducing pressure and temperature on the front of a missile at ultrasonic speed a spike with a spherical, ellipsoidal, or drop-shaped mounted is used on the front end. In contrast to conventional shapes, the sensitive nose of the missile is protected from damaging pressure and temperature, even at high angles of incidence.