Abstract: An isolator mount assembly is disclosed which includes a support structure, a device and an isolator, disposed between the support structure and the device for reducing transmission of mechanical vibration therebetween. The isolator includes a plurality of canted-coils having an elliptical shape which are oriented for loading along a major or minor axis thereof. An elastomer may be applied to the coils and either bonded or unbonded thereto in order to provide the isolator with the capacity to be adapted to desired transmissibility and isolation efficiencies.

Abstract: An improved flight control system with an enhanced unified graphic mistrim indicator where the flight control computer provides signals to a single mistrim indicator wherein the signals represent the status of the control surfaces of the aircraft and the mistrim indicator displays a single movable reference marker, which is caused to be translated vertically in the event of pitch mistrim, is caused to be rotated right or left in the case of roll mistrim conditions, is caused to be translated right or left in the case of yaw mistrim conditions or is caused to be moved in a combination of ways either translating vertically, horizontally or rotating in order to represent a combination of pitch, roll or yaw mistrim.

Abstract: Controlling turbulence in a medium caused by injection of energy into the medium at relatively large scale with consequent dissipation of energy at relatively small scale, is achieved by introducing into the medium a broad spectrum stochastic external disturbance.

Abstract: A de-icer for a structural member of an aircraft is provided. The de-icer includes first and second heaters having first and second electrically conductive strips, respectively. The first and second conductive strips are configured to form first and second marginal portions, respectively. The first and second heaters are positioned relative to each other such that the marginal portions are overlapped.

Abstract: A flying disc capable of vertical takeoff, hovering, or powered horizontal flight. The aircraft configuration comprises a circular disc-like airfoil-shaped wing structure having a convex upper surface and a concave lower surface with a leading edge and a trailing edge. At least one thrust-producing unit is attached at each of the leading and trailing edges, respectively. A plurality of other thrust-producing units are mounted symmetrically about the circular wing structure. Each thrust-producing unit has attached thereto a thrust deflector assembly for angularly adjusting the thrust produced by the thrust-producing unit, thereby allowing the aircraft to fly both vertically and horizontally. A substantial volume of helium gas is stored encompassing the inner upper hull of the aircraft, thereby giving the flying disc greater lift capacity. The outer skin of the upper surface consists essentially of a plurality of solar panels for delivering power to a multiplicity of devices.

Abstract: The space station of the present invention makes use of a modified space shuttle orbiter vehicle to provide a pre-assembled pre-tested, modular space station. The modified orbiter vehicle has all the equipment need for manned launch, re-entry and landing removed. The modified orbiter vehicle carries a pressurized laboratory module, a solar power system, and docking apparatus. The modified orbiter vehicle provides instrumentation, attitude control, communications, and life support systems. Another configuration includes an external fuel tank permanently attached to the modified orbiter vehicle. In either configuration, all equipment is fully integrated, installed and checked out on the ground before the launch in a single unmanned launch.

Abstract: A combined application paraboloid spacecraft structure that is adapted to serve as a structural element for space transportation vehicles, and in additional applications, as a separated spacecraft. The primary structure of the combined application paraboloid spacecraft structure is shaped as the shell of a paraboloid of revolution which has focusing properties for use in such functions as a solar power concentrator, a surveillance or an astronomical telescope, or a communications antenna when deployed in space. The primary structure of this combined application paraboloid can nest and can also be used to support other single or multiple host spacecraft during launch and orbit to orbit transportation.

Abstract: An inner cowl 30 is attached to outer cowling 26. When it is opened it rotates around hinge line extension 36. Latch band 38 has an arcuate upper link 44 secured to anchor 40. A lower link 50 circumferentially slides around the cowl on opening. The latch 52 which secures the lower link is located in a lower gradient where it is visible and accessible.

Abstract: A supersonic aircraft having highly swept subsonic leading edge portions of the wings provided with boundary layer control suction slots. When the airplane is operating at high angles of attack under circumstances where noise is objectionable, air is drawn in through the suction strips to alleviate separated air flow and substantially eliminate (or at least alleviate) vortices that would otherwise develop over the upper wing surface. This improves the L/D ratio and permits the engines to be at a lower power setting, thus alleviating noise. There are shown a double delta planform configuration, and an arrow plan form configuration. Also, the boundary layer control suction can be used in conjunction with laminar flow control suction.

Abstract: The invention resides in a magnetic force system for frictionless transportation of loads, with at least one magnet (1) secured to the load (7), the magnet being arranged with respect to a ferromagnetic support profile (2). It is important that the magnet (1) be arranged with respect to the profile (2) such that the pole surfaces of the magnet (1) cooperate with at least one vertical profile wall, and are essentially parallel to that wall. A particularly good embodiment is obtained by providing magnets on both sides of a profile wall (2), the magnets having identical poles toward the wall (repulsion principle). Longitudinally, the magnets are arranged in pairs and are close-circuited in pairs by a ferromagnetic plate (4).

Abstract: A rendezvous docking optical sensor system for calculating a coordinate position/attitude of chaser and target satellites in accordance with simple calculation equations without performing a complex process such as an image process so as to allow a high-speed calculation process and for realizing a high-reliability system which does not require a high-speed CPU. In the target satellite, a light source is provided which has a function whereby the entire visual field is scanned with a knife edge having edges orthogonal to each other, and in the chaser satellite, a plurality of detectors are provided which form a pattern. Further, there are provided a processing circuit, a computer and a control section which measure the light-transmitting and light-shielding timings of the knife edge so as to calculate and control the coordinate position/attitude of the satellites.

Abstract: A vent-latch interlock assembly (22) for installation to an aircraft door (20) that is provided with a latch assembly (32) that controls the opening and closing of the aircraft door. The vent-latch interlock assembly includes a pressure vent door (40) that is positioned to be seated in an opening (42) formed in the aircraft door (20). The pressure vent door (40) is rotatably attached to a shaft (44) that is rotatably mounted to the aircraft door (20). A set of springs (68) normally biases the pressure vent door (40) away from the opening (42). A drive rod (45) connected between the latch assembly (32) and the shaft holds the pressure vent door (40) in the closed position when the aircraft door (20) is closed. An interlock cable (46) is connected between the pressure vent door and an interlock follower (48) and is located next to the latch assembly (32).

Abstract: In an aircraft, there is included a Flight Management System (FMS), Autopilot and Autothrottle for controlling the aircraft. The apparatus has a plurality of outputs for definition of the real-time targets, controlled by the Autopilot and Autothrottle, to guide the vertical position of the aircraft to a desired vertical position along the desired vertical flightplan (or profile) according to a set of operational procedures. The FMS includes an apparatus that comprises an element which provides information denoting actual vertical position of the aircraft, and an element which generates information specifying the desired vertical position of the aircraft along the predetermined desired flightplan.

Abstract: A pneumatic deicer assembly 32 for attachment to an airfoil includes a pair of plies 52, 54 which are stitched together with a zig-zag stitch line which periodically crosses over the airfoil leading edge.

Abstract: The invention relates to raisable landing gear including a shock absorbing leg that is pivotally mounted, and to a driving actuator associated therewith. According to the invention, the leg is implemented in the form of two elements that are hinged to each other about an axis parallel to the pivot axis of the leg and that are connected together by means of a shock absorber, the bottom element forming a rocker and the top element forming a panel whose free end is connected to a drive actuator which is a shock-absorbing actuator having a force threshold, said shock-absorbing actuator serving to apply a predetermined torque that maintains the leg in position during normal landing, while allowing said leg to be raised against a controlled force in the event of a crash landing.

Abstract: A cargo compartment door for a passenger aircraft having about 80 to 150 seats, wherein the cargo compartment is located underneath the cabin floor, closes a loading opening (6) that extends from approximately a connection area (3, 4) between the cabin floor and the fuselage downwardly in a circumferential direction to well beyond the center plane of the fuselage. The cargo compartment door has a work platform that extends approximately horizontally in the loading position. These features provide an optimal convenience for loading and unloading such aircraft.

Abstract: An arrangement for controlling the flight of a launch vehicle and a coupled payload, such a spaceplane, from launch to the separation of the payload from the vehicle. The launch vehicle is provided with controllable gimballed rocket engines and optionally with aerodynamic control surfaces, that are controlled by flight control systems. The payload having controlled flight surfaces has control systems that cooperate with those flight control systems carried by the launch vehicle to jointly control the coupled launch vehicle and coupled payload during coupled flight. The cooperating flight control systems provide open and closed loop control systems that react to winds measured prior to launch and atmospheric disturbances as indicated by on-board sensors during flight. The payload is mounted on the launch vehicle at a cant angle relative to the longitudinal axis of the launch vehicle to optimize its lift to the coupled launch vehicle and payload.

Abstract: A supersonic flight aircraft having a longitudinally forwardly extending axis in the direction of flight, and a wing, comprising a wing extending generally laterally relative to the axis, and having a leading edge angled forward or rearwardly relative to a normal to the axis at an angle .OMEGA., and the wing having a maximum thickness t; the angle .OMEGA. and thickness t characterized that in that in supersonic flight conditions, the forwardmost shock wave produced in association with the wing extends generally along or rearwardly of the leading edge, whereby laminar airflow conditions are maintained over the leading edge and adjacent the surface of the wing.

Abstract: An articulated wing has a fore wing portion and after wing portion connected to an articulate axis support structure which extends along the length of the wing and separates the two wing portions. Control actuators separately connect the fore and after wing portions to the articulate wing support structure in order to provide separate angular positioning capabilities for the two wing portions. Further, the articulate wing support structure itself may be rotated with respect to the mechanism it is attached to. These and other flexible controls over the wing attitude and size allow the wing to provide a number of force vector amplitudes as well as directions for any given fluid flow direction and velocity.

Abstract: An aircraft engine thrust mount includes a pair of spaced apart thrust links pivotally joined at one end to an engine first frame and at opposite ends to a lever. A platform is fixedly joined to an aircraft pylon and includes first and second spaced apart clevises and a center clevis therebetween. The center clevis is pivotally joined to a center of the lever for carrying thrust force from the first frame through both thrust links and to the platform and pylon during normal operation. A pair of pins pivotally join the thrust links to the lever and extend through apertures in the platform first and second clevises to define predetermined gaps therebetween for allowing the lever to rotate relative to the platform center clevis up to a predetermined angular rotation. In a failure mode of operation the pins contact the platform first and second clevises for transmitting thereto either tension or compression thrust loads for providing an alternate failsafe loadpath.