Abstract: A load glider has, between the parachute surface and the load, a device in which a reversible transfer of mechanical energy from the main lines to the steering lines takes place, so that essentially only frictional forces are to be overcome during the operation of the steering lines. The device includes two differential gears, which are arranged in parallel and are accommodated in housings in which a steering line is wound up on a roller with a larger diameter and a main line is wound up on the other roller with a small diameter. Gears, which can be driven by pinions driven by electric motors, are flanged onto the larger rollers.

Abstract: A stabilizing in-flight parachute system for an airplane comprising a retractable canopy built into a top portion of a fuselage of the airplane. A parachute is under the canopy, while a framework is attached to the parachute. A device is for winding and unwinding the parachute on the framework. A facility is for retracting the canopy and exposing the parachute. A mechanism is for accelerating deployment of the parachute out from the fuselage of the airplane, when the canopy is retracted.

Abstract: An aircraft having variable airframe geometry includes an elongate fuselage having top and bottom sides, a swept back, high-speed wing mounted to the top of the fuselage, and a high aspect ratio, low-speed wing pivotally mounted adjacent to the bottom of the fuselage. The low-speed wing is adapted to pivot between a slow speed flight position in which a longitudinal axis of the low-speed wing is generally perpendicular to a longitudinal axis of the fuselage, and a high-speed flight position in which the longitudinal axis of the low-speed wing is generally parallel to the longitudinal axis of the fuselage. A fairing extends from the fuselage for receiving at least a portion of the low-speed wing when pivoted into the high-speed flight position. The low-speed wing further includes landing gear.

Abstract: A special set of elliptical satellite orbits are described which allow preferential coverage of one parameter over another. According to a first modification, the orbits are retrograde, and preferentially cover one geographical location or time of day as compared with another. A second modification uses prograde orbits and allows the apogee of the orbit to be offset a constant amount with respect to the sun, to thereby cover a different time of day relative to the others. According to a special preferred mode of the invention, the apogee is always pointing towards the sun.

Abstract: A method and apparatus for reducing the unwanted sideways motion of an airplane by reducing the lateral side loads and upsets caused by atmospheric turbulence and gusts is disclosed. A rudder modification command that causes the rudder command of the airplane to be changed in a manner that relieves the net force across the vertical stabilizer of the airplane caused by atmospheric turbulence and gusts is produced. More specifically, the pressure differential across opposite sides of the vertical stabilizer is measured and used to produce a rudder deflection value that is roll rate and yaw rate compensated. The compensated deflection value is high-pass filtered with a corner frequency that is twenty-five percent (25%) of the Dutch roll frequency of the airplane. The result is a first rudder deflection value that is subtractively combined with a second rudder deflection value.

Abstract: A liquid coolant heat exchange system for use in semimonocoque aircraft includes an arcuate planar heat sink fixed along a radius of curvature R.sub.1 by forming members, a flexible arcuate planar spreader plate having a radius R.sub.2, such that R.sub.1 >R.sub.2, a heat exchange tube for transferring heat from the liquid coolant to the heat sink and means for attaching the spreader plate to the forming members to hold the spreader plate in contact with the heat sink.

Abstract: A reusable single-stage-to-orbit spacecraft and a reusable launch assist platform provide a new system for space transportation. The platform has a frame with a cradle for supporting the spacecraft. Rocket engines attached to the launch assist platform propel the launch assist platform and the spacecraft substantially vertically through the atmosphere for release of the spacecraft. The launch assist platform returns to a predetermined landing site in a power-controlled, vertical descent.The spacecraft is in the shape of a cone having a large, rounded base with a primary load-bearing structure substantially perpendicular to the base. The spacecraft reenters the atmosphere in a base-first reentry, and is slowed and guided to a landing site by using a rocket engine in the base. The spacecraft lands base first on a resilient landing device.

Abstract: A refueling system mounted to an aircraft fuselage for transferring fuel from a tanker aircraft to a receiver aircraft. The refueling system including a pylon extending from the fuselage at a position aft of the main wing and having a refueling pod mounted thereto at an outboard location. A refueling hose is disposed within and extendable from the refueling pod and functions to transfer fuel from the refueling pod to the receiver aircraft. A means for transferring fuel from a fuel source, located within the aircraft, to the refueling hose is also provided. The pylon and refueling pod are configured so as to channel the refueling hose in a preferred direction to maximize safety during refueling. The channeling of the refueling hose is accomplished by mounting the refueling pod at an angle to the pylon, mounting the refueling pod at an angle to a horizontal plane, mounting the pylon at angle to the fuselage, or a combination of these mounting arrangements.

Abstract: An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.

Abstract: A pliant, controllable contour control surface comprising a first flexible facesheet formed to a first initial contour of the control surface, and a second flexible facesheet formed to a second initial contour of the control surface. The first and second facesheets each have a set of prestrained shape memory alloy tendons embedded therein, extending from a leading edge to a trailing edge of the control surface. Each set of the shape memory alloy tendons is separately connected to a controlled source of electrical current such that tendons of the first and second flexible facesheets can be selectively heated in an antagonistic, slack-free relationship, to bring about a desired modification of the configuration of the control surface. A computer based control system is utilized for maintaining a constant temperature of the antagonists to establish conditions conducive to the stress induced transformation from austenite to martensite, accomplished by causing constant current to flow through the antagonists.

Abstract: A de-icing system is provided including a de-icer attached to an aircraft structural member subjected to an impinging airstream during flight, the airstream passing over the structural member in a fore to aft direction. The deicer has a primary heater element disposed beneath a primary shedding zone upon which ice accumulates during flight, the primary heater element being configured to heat the primary shedding zone upon application of an electrical potential across the primary heater element, and a secondary heater element disposed beneath a secondary shedding zone upon which ice accumulates during flight, the secondary heater element being configured to heat the secondary shedding zone upon application of an electrical potential across the secondary heater element, the secondary heater element being disposed immediately aft of the primary heater element.

Abstract: A split rudder control system for an aircraft which reduces the net opening hinge moments opposing return of the split rudders to the fully closed position from small deflection angles. The split rudder control system provides a smoothly faired aerodynamic protuberance on the upper surfaces of the split rudder control members adjacent to the trailing edge of the wing when the control members are in the closed position and at small deflection angles relative to the closed position. The aerodynamic protuberance smoothly deflects the airstream flow over the upper surface of the wing as it approaches the trailing edge, increasing the local velocity of the airstream at a point forward of the trailing edge. The aerodynamic feature is contoured such that a maximum local airstream velocity occurs generally at the interfacing edges of the control members.

Abstract: An airplane galley is moved through an airplane door and into final position on an airplane over honeycomb floor panels without damaging the panels or straining the workers by the use of a jacking dolly that is inserted into a meal cart slot under the galley. The dolly has a vertically extendable framework attached between an upper structure and a lower structure on casters. The upper structure is dimensioned to fit into at least one of the meal cart slots in the galley and can be jacked up to lift the galley off the floor. The casters supporting the lower structure of the dolly each include a low pressure pneumatic wheel that partially flattens and distribute the weight of the galley over a wide wheel footprint. The footprint of the partially flattened wheels has an area wide enough area to prevent damage to the honeycomb floor panels.

Abstract: An aircraft of disc-shaped configuration provides the capability of vertical take-off and landing; straight horizontal flight; and three-dimensional maneuverability in the air by means of a plurality of counter-rotating lifting rotors assembled of fixed pitch or of self-adjusting pitch aerofoil blade elements; and, submersibility of the aircraft in water is achieved by means of a marine propulsion module using two counter-rotating hydrofoil rotors for up or down thrust, and a tunneled conventional marine propeller for horizontal travel. The marine propulsion module is detachable for emergency and for use with the main frame aircraft of a variety of other detachable modules for different tasks and missions. Exceptionally adaptable for any existing power plant, including nuclear, it is best suited for the environment-friendly types, like integrated steam motor on hydrogen and oxygen burning.

Abstract: A recline safety lock assembly to be secured to an aircraft passenger seat of the type including a reclining seat back portion, a seat foundation and at least one recline cylinder structured to permit reclining of the seat back portion. The recline safety lock assembly includes at least one lock plate having an upper mount portion to be secured to a side rail of the seat back portion, and an engagement end having a downwardly depending lip formed therein. Additionally, the assembly includes at least one lock pin having a main shaft with a transverse notch formed therein. The lock pin is rotatably and axially mounted adjacent the engagement end of the lock plate and is rotatable between a disengaged orientation and an engaged orientation. In the engaged orientation the transverse notch is in a generally upwardly angled orientation such that the lock pin engages the downwardly depending lip of the lock plate and rear reclining of the seat back portion relative to the seat foundation portion is prevented.

Abstract: An apparatus and method of stabilizing unstable shock waves on the surface of a body induce shock waves to form prematurely at a particular location on a surface of the body and fix that location such that shock waves will form consistently and persistently at that location on the surface of the body. Boundary layer flow separates from the surface of the body at that location and can be prevented from reattaching to the surface. Shock wave oscillations due to interactions with the separated boundary layer flow are prevented, thereby minimizing vibrations induced in the body. The apparatus has a flow accelerating surface and a discontinuity in the accelerating surface. The accelerating surface causes local fluid flow over the surface of the body to accelerate and prematurely and consistently form a shock wave at the point where the discontinuity is located.

Abstract: The present invention relates to a protective cover for an airplane nose-wheel fairing. The protective cover prevents a nose-wheel fairing from becoming cracked or scratched as an airplane tow bar is attached or removed from the nose-wheel strut.

Abstract: Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

Abstract: An aerodynamic lifting and control surface comprising an external box structure that encloses an internal grid whose members are parallel to the box structure. The external box structure comprises four panels connected at their comers by spring hinges. When the hinges are unconstrained, the external box structure is compressed into a flat, thin parallelogram shape. The internal grid comprises a plurality of plates connected to each other and to the external box structure by flexible hinges. Control apparatus for use with an aerodynamic vehicle is also disclosed. The control apparatus comprises at least one aerodynamic lifting and control surface that is coupled to an actuator disposed within the vehicle and connected to the aerodynamic lifting and control surface for rotating it.

Abstract: A series of spacecraft designs (10, 42 and 52) for a Satellite Communication System is disclosed. One of the preferred embodiments of the invention called "Gearsat.TM." (10) comprises a hollow torus which inflates when it reaches orbit. When viewed from the side along its circumference, Gearsat (10) looks like two flattened pyramids sharing a common base. Phased array antenna panels (14) are deployed across the top of the pyramid along an exterior cylindrical surface (12), while twin arrays of solar cells (16) cover the slanted surfaces. The satellite (10) rotates about its center, and individual antenna panels (14) are spatially synchronized to transmit and receive signals from particular regions on the ground. An alternative embodiment, called "Batsat.TM." (42, 52), includes a central cylindrical body (B) and a plurality of substantially circular linked antenna and solar/thermal panels (A1-A9 and S1 and S2) which carry individual antennas (X) and solar/thermal surfaces (Y).