Abstract: A hypersonic inlet and a hypersonic engine and flight vehicle having such an inlet. The three-dimensionally-swept inlet has an upper member with a caret-shaped lower surface portion producing a two-dimensional wedge flow below such lower surface portion. The inlet also has a lower member having two inverted and transposed semi-caret-shaped upper surface portions producing a two-dimensional wedge flow above such upper surface portions. An inlet aft portion connects together the upper and lower members and has an orifice defining the engine inlet throat which at least partially receives the two-dimensional flows.
July 25, 1988
Date of Patent:
January 21, 1992
General Electric Company
Paul H. Kutschenreuter, Jr., Jon M. Vishnauski
Abstract: A fastening combination adapted for quickly and efficiently connecting a first structure to a second structure using a single tool (like a screwdriver) and from just one side of the two structures. The fastening combination (which may be called a "blind" fastener) is particularly useful in the aircraft industry for installing a transparency such as a canopy or window to the airframe of some plane. A transparency may be removably connected to the airframe with a plurality of internally threaded members (or sleeves) and mating fastening bolts. The sleeves are loosely mounted in a plurality of fastener housings that can be permanently installed near an edge of the transparency. A means is provided for achieving a mechanical connection between each sleeve and an associated housing in such a way that torque applied by the fastening bolt to the sleeve will be resisted by the housing--and in turn by the transparency (or any other mounting structure to which the housing is anchored).
Abstract: An automatic neutral position locking system for a control surface of an aircraft. A hydraulic prime mover is provided for moving the control surface. A locking device is capable of locking the control surface against movement. A ratchet-and-pawl device is operatively associated with a rotary drive train between the prime mover and the control surface for actuating the locking device in response to the control surface reaching a neutral position. The ratchet-and-pawl device normally is maintained in inactive condition when hydraulic pressure exists in the prime mover. A pneumatic piston-and-cylinder device, when under pressure, maintains the ratchet-and-pawl device in normally inactive condition. With a loss of hydraulic pressure, the ratchet-and-pawl device is effective to actuate the locking device in response to the control surface itself reaching the neutral position as the control surface moves under external loads.
Abstract: An airfoil having two (2) basic components, a sail and spoiler, associated with the leading edge of the sail, is herein disclosed. This unique airfoil design has application in flexible wing aircraft (i.e., ultralites), sport parachutes and sport kites. In the typical sport kite embodiment of this invention, there will generally be at least three (3) aerodynamic flight control surfaces: a sail, a keel, and a flexible resilient spoiler attached to the leading edge of the sail. The sail material is itself resilient, however, sufficiently rigid to maintain a preset configuration without the need for struts, spars or extrinsic physical support. A spoiler, which is located along the entire leading edge of the sail, provides additional structural reinforcement to the sail while undergoing controlled deformation in gusty or high winds. The effect of such deformation of the spoiler causes the sail to stall before any physical damage can occur.
Abstract: A seat insert insertable within the existing seat of a vehicle for maintaining a crew member of the vehicle in a forward posture during high G acceleration. An elongated head support member is provided for supporting the crew member's head during a forward leaning posture. A back plate assembly including at least one back plate is connected to the head support member for supporting the spine in its natural curvature. Means being connected to the back plate assembly are provided for pivoting the back plate assembly forward relative to the seat of the vehicle. Means are provided for transfering any G-induced weight from the spine to the back plate assembly and ultimately to the existing seat of the vehicle. The head support member is restrained in such a manner so as to maintain the crew member's head in an "eyes up" attitude during a forward lean.
September 27, 1988
Date of Patent:
May 8, 1990
Rockwell International Corporation
William J. Adams, Robert E. Zegler, Conrad B. Monson
Abstract: Method and apparatus for controlling the attitude of a satellite in space by thruster reaction forces without loss of thruster fluid into space. A jet of gas, preferably compressed air, comprising reaction mass stored in a reservoir on board, is discharged in a predetermined direction into an endless enclosed evacuated volume. The molecules of discharged gas are scavenged from the volume and recompressed and restored to the reservoir. The discharged gas is scavenged sufficiently rapidly from the volume to prevent appreciable increase in the static pressure encountered by repeated bursts from the jets. The apparatus comprises an endless duct network circumferentially surrounding the two axes of the satellite, with solenoid operated thrusters selectively to discharge the gas jets and a vacuum-pressure pump to scavenge the air molecules, recompress them and pump them back into the reservoir tank.
Abstract: An aerial aircraft carrier is disclosed having a first and a second shuttlecraft that have a cantilever fluselage extending between the first and second shuttlecraft. The cantilever fuselage is disposed at both ends within a fuselage housing that depends from the under-carriage of the first (lead) and second (aft) shuttlecraft, the cantilever fuselage forming a longitudinal member therebetween. A means for elevating a plurality of aerodynamically stable platforms, (wing assemblies), is affixed to the cantilever fuselage. The wing assemblies each have a wing span member attached thereto, with control surfaces, for stabilizing an aircraft (a payload) that is secured in a mount assembly.
Abstract: Atmospheric drag and heating of the forwardmost portions of high speed transatmospheric vehicles and projectiles are reduced by lowering the atmospheric mass density immediately forward of a moving body. A fine high speed stream or jet of a material containing a chemically interactive component is ejected forwardly of such a body moving at high speed with respect to the atmosphere and, in a preferred embodiment of this invention ignites by interaction with the oncoming atmosphere and forms a sustained zone of combustion that, in effect, acts as a maintained "fireball" that explodes away ambient atmosphere transversely of the moving body so that there is generated a zone of low atmospheric density immediately in front of the forwardmost portion of the body. A supply of ejectable material and equipment for forcibly driving the same through a nozzle are carried with the body. The ejected material is preferably pressurized to render it flowable before ejection.
Abstract: An actuation device for a slat, a rail for guiding and moving the slat into and out of an aircraft wing has the slat pivoted on the rail in a particular point (8); a thrust rod has one end hinged to the slat and a drive crank is connected to a second end of the thrust rod; a lever assembly connects the rail additionally to the slat at points on the rail and the slat different from the particular point and for pivoting and steering the slat relative to the particular point, for holding the rear end of the slat against the wing in a first protraction range and opening a gap upon further protraction.
Abstract: An air-borne craft is provided with at least two pairs of propellers with substantially vertical axes. One pair of the propellers is provided on the front portion of the craft, the other pair on the rear portion with one propeller of each pair on the left side and the other propeller of the same pair on the right side of the body of the craft. The propellers are provided on their rear directions with flaps which can open and close relative to the profiles of the propellers. The arrangement of at least four propellers secures an economical operation in case of emergency landing and at flight. In case of an engine failure the craft has still a forwardly directed speed. This speed will open the flaps and the flow of air against the flaps will revolve the propellers. Thereby at least one arm of each of the propellers remains acting like a helicopter blade and the four propellers can carry the craft in a gliding procedure, flying forwardly with an angle of descent, towards the ground for the emergency landing.
Abstract: A process and an apparatus for hooking of a band of a flexible material, intended to be subjected to tensile forces, to a fixation piece, for hooking onto the fixation piece of an envelope of which the end portion is divided along a given length, into a plurality of bands of equal width, the process comprising longitudinally folding one extremity of the band upon itself, at least one time, in such a manner as to form at least one hem (14, 15), transversely gathering the hem in accordian fashion in such a manner as to form a flange presenting a fan-shaped configuration, using a fixation piece provided with a groove of a wedge-shape conjugate to the shape of the flange, the groove having a longitudinal extremity opening toward its apex, and arranging the flange within the groove, the band extending through the open extremity of the groove in such a manner as to create a self-locking of the flange when the band is placed in tension.
Abstract: An improved structure for the shrouded propeller tail duct or "ring tail" of a rotary wing aircraft providing rotor torque counteracting and aircraft yaw control forces in all flight conditions of hovering and high speed cruising flight. The rear portion of one lateral side of the shrouded propeller duct comprises a plurality of overlying arcuate segments that are pivotally supported for rotation relative to each other about a vertical axis between a retracted position for high speed flight in which the segments are in a mutually overlying position constituting one side of the duct and an extended position in which the segments are in a mutually adjoining relationship with their edges only overlapping and extending obliquely transversely of the duct interior in the form of a continuous, rearwardly projecting and transversely extending arcuate extension of the interior wall of one side of the duct.
Abstract: A single aft located prop aircraft having an X-axis in alignment with the line of thrust of the aircraft; a Y-axis transverse to the X-axis, the Y-axis being in parallel with the length of a single main wing; and a Z-axis transverse to the plane defined by the X and Y-axes. The fuselage exhibits Y-axis symmetry about the thrust line and, in addition, substantial X-axis symmetry about a line defined by the forward edge of the main wing. The fuselage assembly includes a substantially conical cone, the cone having its root at the beginning of the pilot's cabin, and the cone subtending a vertex in the range of 15 to 20 degrees. The fuselage nose possesses an X-axis length to Z axis base diameter ratio in the range of 2 to 3. The aircraft further includes a single main wing secured on top of the upper fuselage in which the XY plane of the wing is in alignment with the line of thrust of the aft-located prop.
Abstract: A hybrid wing assembly is made up of a load supporting center frame with laterally outwardly extending, articulated, wing sections. A parafoil is attached to the wing sections by flexible lines in flight, and rigid rods hold the parafoil in spaced relation to the wing at rest. Control lines extend from the parafoil to the user for controlling the assembly.
Abstract: A ground-air-water craft comprises a fuselage body with a passenger compartment mounted thereon, a box-type main wing connected to the fuselage and extending outwardly on both sides thereof, the main wing comprising an upper wing and a lower wing which are substantially horizontal and which have a total wing span in the range of 5 to 10 feet, as well as a right side member and a left side member, each side member extending substantially vertically and connected between the lateral ends of the upper and lower wings on the respective right and left sides of the craft. The craft also comprises a control or canard wing connected to the fuselage and extending outwardly on both sides of the fuselage with a wing span no greater than 10 feet.
Abstract: The reserve parachute is folded and disposed in a covering. A pilot chute overlies the reserve parachute outside of the covering. A disc overlies the pilot chute and bears against a compression spring maintained under compression by a single centrally positioned cord connected between the disc and a single release pin on the opposite side of the covering. The cord extends centrally through the compression spring and is connected centrally of the disc. Handling, packing and releasing of the reserve parachute and deployment of the pilot chute is thereby simplified.
Abstract: A superagile tactical fighter aircraft and a method of flying it are disclosed. The superagile aircraft is characterized by articulatable air inlets, articulatable exhaust nozzles, highly deflectable canard surfaces, and control thruster jets located around the nose of the fuselage, on the top and bottom surfaces of the propulsion system near the exhaust nozzles, and on both sides of at least one vertical tail. The method of operating the superagile aircraft comprises the step of articulating the air inlets and exhaust nozzles, deflecting the canard surfaces, and vectoring the thruster jets so that supernormal flight is attained. Supernormal flight may be defined as flight at which the superagile aircraft operates at an angle of attack much greater than the angle of attack which produces maximum lift. In supernormal flight, the superagile aircraft is capable of almost vertical ascents, sharp turns, and very steep descents without losing control.
Abstract: A transfer vehicle for use in a system for transferring payloads from an earth-launch vehicle in one space trajectory to another space trajectory. The system includes a space launch vehicle (FIG. 9) with primary propulsion and guidance systems, a transfer vehicle (FIG. 1) carrying a payload which is stowed in the cargo bay during earth-launch and insertion of the earth-launch vehicle into low-earth transfer trajectory. An engine module (FIG. 3) carrie on-board mission equipment, rocket engine, related fuel supply, guidance equipment, attitude control equipment and electrical power supply equipment (FIGS. 11-20). A grapple system on the earth-launch vehicle (FIG. 9) deploys the transfer vehicle and cargo and restows it for on-orbit repair/modification for earth-return. The transfer vehicle may be multi-staged (FIG. 21) and may be provided with multiple engines (FIG. 23).
Abstract: A wing (2) has a trailing edge at which jet flow is deflected downwardly to provide lift. A retractable member (4, 4') has a sharp forward edge (6, 6'). When deployed, member (4, 4') extends along at least a portion of the span (preferably substantially the entire span) of the wing (2) at the leading edge of wing (2). Member (4, 4') projects forwardly and upwardly from wing (2). Member (4, 4') causes flow around wing (2) rearwardly of itself to separate from wing (2) to reduce suction and leading edge thrust. Preferably, reattachment of flow is induced at a location spaced rearwardly from member (4, 4'). A jet of high velocity gas is blown along wing (2) in a generally spanwise direction. This induces reattachment to maintain trailing edge thrust so that jet deflection at the trailing edge will efficiently provide lift during a short distance landing.
Abstract: Landing gear comprising a pivoting strut (1) receiving the rod of a shock absorber (2) which projects downwardly from the strut and is movable in an axial direction (3) relative thereto, a rocking beam (4) mounted to tilt at the bottom end of the shock absorber rod (2) and supporting leading and trailing wheel sets (6), a torque linkage comprising a top branch (7) and a bottom branch (8) which are hinged to each other, the top branch (7) being hinged to the strut (1) and the bottom branch (8) being hinged to the rocking beam, and locking means (9, 15) for limiting a downwards pivot movement of the top branch (7) of the torque linkage while the shock absorber rod (2) is not fully extended.
June 8, 1988
Date of Patent:
January 9, 1990
Michel Derrien, Jacques Veaux, Jean-Pierre Hainaut