Abstract: An amphibious aircraft, capable of high speed maneuverability on the surface of the water, utilizes a aerodynamic platform to generate lift and to define a tunnel with a pair of central sponsons extending inwardly of the wings of the aircraft longitudinally of the platform which supports the cockpit and propulsion system.

Abstract: A vehicle cabin construction includes a storage Compartment in the space between the ceiling and outer cabin wall extending longitudinally of the vehicle cabin for storing article holders, an elevator for lowering the article holders from the storage compartment to the deck, and for raising the article holders from the deck to the storage compartment, and longitudinal transfer means engageable with the article holders for moving them longitudinally from or to different locations in the storage compartment on a plurality of roller transfer members.

Abstract: The space debris clearing device of the invention, following launch and placement in or near an orbit considered to be highly populated with debris, is intended to clear the debris allowing safe paths and orbits for space assets. The device is made of a castable, energetic material, and shaped to meet specific clearing requirements. Once in position the device is remotely detonated, and an impulse, caused by the expanding detonation products, is imparted to the debris, pushing the debris into a reentry or earth escape trajectory.

Abstract: This invention is directed to stopped rotor Flipped Airfoil X-wing (FAX-WING.sup..TM.) aircraft which comprises:(a) A rotary wing flight mode which operates similar to a helicopter, wherein all main rotor airfoils rotate with leading edges into the oncoming airstream (neglecting forward motion) to provide lift, and utilize an anti-torque rotor to cancel main rotor torque. The fixed wing flight mode, including supersonic flight, utilizes all stationary main rotor airfoils for primary lift, such that all airfoil leading edges are positioned forward, meeting the oncoming airstream generated by forward aircraft motion. Two airfoils are forward swept 45 degrees, and the other two airfoils are aft swept 45 degrees. The transition mode for converting from rotary wing to fixed wing flight, and vise-versa, causes two adjacent airfoils to flip 180 degrees (in approximately 1/16 second) about their pitch axis, such that all airfoils have leading edges in the correct orientation for a particular flight mode.

Abstract: An aircraft structure, such as a glider including a wing having a substantially flat, upper, first surface and a convex, lower, second surface. The wing first and second surfaces converge to a leading edge and a trailing edge. A weighted member is used to determine the center of gravity of the wing as being 15 to 25% of the length of the chord from the leading edge. The weight structure is fixed to the wing and may also serve as a structural member.

Abstract: A spacecraft berthing mechanism for coupling spacecraft is provided which has minimal effect on the maximum size an associated spacecraft hull may have. The berthing mechanism includes a flange member which defines a hatchway and which is adapted for attachment to a spacecraft port. The flange member has a forwardly facing interface surface through which the hatchway passes and an outer peripheral surface extending rearwardly from the interface surface. The peripheral surface has a plurality of beveled portions spaced substantially evenly about the peripheral surface. A plurality of alignment guides are arranged on the flange member such that several of the alignment guides are positioned adjacent one of the beveled portions and the remaining alignment guides are positioned adjacent an opposing beveled portion.

Abstract: An apparatus for the opening of skydiver's parachute by another skydiver, instantaneously and without physical contact between them, is provided. The device provides a skydiver with the means of generating radio frequency signals, and provides a second skydiver with the means to process those signals and trigger a parachute opening mechanism that opens the parachute of the second skydiver. This invention provides the ability for a more experienced skydiver such as an instructor, to open the parachute of a lesser experienced skydiver, such as a student. In addition, this device can also be used in the activation of a parachute opening mechanism that it attached to any entity accompanying a skydiver in freefall.

Abstract: An inlet bleed system for a supersonic aircraft engine having a longitudinally downstream extending inlet bounded by a boundary wall that in part defines a supersonic flowpath through the inlet, a transversely extending boundary layer scoop extends into a boundary layer region of the flowpath and has an upstream facing bleed aperture, and a shock generating means for generating a shockwave in a supersonic flow in the flowpath such that the shockwave passes through the bleed aperture. One embodiment provides a scoop which extends a height above the wall such that it is operable to scoop off no more than a sufficient amount of a boundary layer flow that would exist in the boundary region and be momentum deficient relative to predetermined conditions that would exist downstream of the scoop under supersonic operating conditions. Another embodiment provides for the scoop to be disposed a throat section of the inlet wherein the aperture located is just upstream of the normal shock location.

Abstract: A multi-axial hand-operated helicopter control includes a pivotal arm which may freely pivot in two planes relative to a base member with collective and rudder control rods attached at the base of the pivoting arm member for translating motion along one plane into collective control and motion along another plane into rudder control. A rotatable throttle control mounts at an end of the arm member and a throttle shaft extends through the arm member attaching to a constant velocity joint for translating rotational movement of the throttle control into rotational movement of a base throttle rod. The pivotal arm member is mounted to a base member via a universal joint, with the constant velocity joint placed at the center of the universal joint, achieving high torque rotation.

Abstract: A lifting body concept applicable to reusable space launch vehicles in which the propellant tankage is shaped in the form of a closed "vee" made up of intersecting cylindrical segments, and represents a major part of both the structural and aerodynamic configurations. The lifting body is made up of conical, wedge and swept cylinder elements. Absence of wings and large vertical stabilizing surfaces together with a configuration made up of joined straight line element surfaces makes for a low-cost, efficient, lightweight airframe/propellant tank configuration. The windward afterbody composed of flat and fixed radius cylindrical surfaces makes possible a small number of ceramic and/or metallic heat shield tiles and contributes to their easy installation and replacement.

Abstract: A helicopter flight control system (21) includes a model following control system architecture which automatically provides a coordinating yaw command signal to the helicopter tail rotor to coordinate helicopter flight during a banked turn. The control system processes information from a variety of helicopter sensors (31) in order to provide the coordinating yaw command signal on an output line (72) to the tail rotor (20) of the helicopter.

Abstract: A rotor flap apparatus is attached to the trailing edge of a wing of a craft. The rotor flap apparatus includes a rotatable rotor mounted on an attachment arm, which is pivotally mounted on a trailing edge of the wing. The attachment arm can be raised or lowered to move the plane of the rotor up or down to vary the lift and thrust characteristics of the wing, to prevent stall and also to allow very low speed take off and landing. In one embodiment, propellers are provided at the leading edge of the wing, in conjunction with the rotor flap apparatus, to provide a system which allows vertical take off and landing of the aircraft. Other embodiments include wings with rotor flap apparatus attached to land craft and underwater craft as well.

Abstract: A helicopter flight control system includes a model following control system architecture to control helicopter response about the yaw axis. The control system processes information from a variety of helicopter sensors in order to provide an output command signal to the tail rotor. Yaw control is accomplished by applying a force on a sidearm controller which provides a yaw axis command signal that is used to schedule a desired yaw rate of change. The lateral acceleration and airspeed signals are used to compute a synthesized yaw rate signal which is compared against the desired yaw rate of change, thus allowing the pilot to control lateral acceleration when he applies force on the sidearm controller.

Abstract: A helicopter flight control system includes a model following control system architecture having provisions to compensate for Euler singularities which occur when the pitch attitude of the helicopter starts to approach ninety degrees. The control system processes information from a variety of helicopter sensors in order to provide the control commands to the helicopter main and tail rotors. The present invention synchronizes a sensed attitude signal, and a desired attitude signal as the pitch attitude of the helicopter approaches ninety degrees to compensate for the Euler singularities.

Abstract: A porous airfoil having venting cavities with contoured barrier walls, formed by a core piece, placed beneath a porous upper and lower surface area that stretches over the nominal chord of an airfoil is employed, to provide an airfoil configuration that becomes self-adaptive to very dissimilar flow conditions to thereby improve the lift and drag characteristics of the airfoil at both subcritical and supercritical conditions.

Abstract: A method and apparatus for changing the orbit of an artificial satellite. The apparatus is caused to approach a target satellite and to be coupled thereto in space so as to constitute a dumbbell-like coupled system. The apparatus has a propulsion unit. The unit generates a thrust, whereby the velocity of the center of gravity of the apparatus increases, and the apparatus rotates around the center of gravity. As a result, the coupling system is placed in transition orbit.In the transition orbit, the coupled system is released at a timing when the direction of elongation of the coupled system becomes perpendicular to the orbital velocity vector. Subsequently, the target satellite is placed in a final target orbit, and the separated orbit changing apparatus is placed in an orbit different from the target orbit.

Abstract: An industrial robot system comprises a robot movable on a track formed on a floor; work stations arranged along the track, where the robot deals with workpieces in a predetermined order; reference points provided at the stations, respectively, and a detector installed on the robot for detecting the reference points so that the robot can be properly positioned with respect to each work station.

Abstract: A re-entry vehicle that includes three detachable modular components which anticipate total re-useability. Modularization of the composite re-entry vehicle offers great flexibility in re-arranging the various modules to suit a particular mission. The three module components include a crew module, principally serving as a crew cabin, and attached thereto is a modular heat shield or re-entry module which principally provides for thermal protection of the cabin module during re-entry. Propulsion for the cabin module to achieve a particular re-entry orbit is provided by a versatile service stage which becomes detached from the other two modules upon attainment of a desired re-entry trajectory. When used in conjunction with a Space Station, the versatile service stage may be propelled back to the Space Station for refueling and re-use.

Abstract: Orbital systems (28, 38) are provided which can be sustained with relatively low propellant requirements. The orbital systems (28, 38) comprise a plurality of earth-relative orbits, at least one of which is outside of the plane defined by the moon's earth-relative orbit (36). Transfers between the earth-relative orbits are achieved by using the moon's gravitational field. The orbital systems (28, 38) could be used to reduce the propellant requirements of lunar missions and could provide economic and life protecting advantages.

Abstract: An air launched, air-to-surface missile which has extended range and reduced radar cross section for low observability is disclosed. The design uses a triangular cross section fuselage, for low profile drag and reduced weight, a very high aspect ratio, such as 22.5, folding wing for low induced drag and three folding tail fins for less profile drag. The wing is a composite structure of graphite/epoxy sparcaps and 2024 aluminum alloy core with glass/epoxy skins and full depth Nomex.