Abstract: A self-staging parachute apparatus including a drogue parachute and a main parachute each encapsulated in a respective packing bag with the main parachute packing bag defining a side pocket through which a specialized retention bridle extends from the suspension lines of the drogue chute directly to a load line connected to the load. The load thus utilizes a single point of attachment for both the drogue parachute and the main parachute with the retention bridle of the drogue parachute in movable engagement extending through the pocket of the main parachute deployment bag. The main parachute and drogue parachute when packed are designed to form a generally cylindrical shape which is adapted to be easily placed within cylindrical payloads such as flares or the like to facilitate deployment thereof after the rocket motor has been separated.

Abstract: A drive and guide mechanism for a flap such as a landing flap arranged in an aircraft wing, especially in the trailing edge of the wing includes a carriage to which the flap is pivoted. The carriage is movable along a support and guide rail. A drive arm and control system is operated by a drive mechanism (8) with a drive lever (9) which connects a drive rod (10) to the carriage. The kinematic drive mechanism (8) includes a control link (5), a two armed lever or control link (6), a control rod (7), and the drive rod (10). The two armed control link (6) is journalled to the carriage (4) in a tiltable manner. One arm of the two armed link (6) and the control link (5) connect the carriage with the flap (2). The one arm (6a) and the control link (5) form a four bar link with a section of the carriage and a section of the flap. The second arm (6b) of the control link (6) is connected with the drive lever (9) through a drive rod (10).

Abstract: A connector device is constructed for fixing and holding of structural components to each other, more specifically of secondary components to a primary support component. The primary support component may, for example, be a support rail with a clamping gap and the secondary components may be cross beams for carrying floor panels and the like, for example, in an aircraft. The connector device has a base plate and a carrier body extending from the base plate as well as connector flanges secured to the carrier body and preferably also to the base plate. A central bore passing through the carrier body and through the base plate receives a clamping bolt that grips with its head under rail edges forming a gap. A nut on the clamping bolt rests against a shoulder in or on the carrier body.

Abstract: A device for elastic coupling between two parts, especially the principal transmission box and the fuselage of an aircraft with rotating wings, such as a helicopter, includes first and second inner and outer tubular bodies, and an elastic connection, housed in the annular space existing between the first and second bodies and coupling the first and second bodies in a leaktight fashion. The annular space is separated by the elastic connection into first and second chambers filled with a liquid, the first and second chambers being in communication with the inside of the first body. On the inside of said first body, there is a liquid distributor provided with an elastic damping connection and including two pistons, which are coupled by a piston rod and separated from each other by the distance separating orifices in the first and second chambers.

Abstract: An aircraft landing gear damping mechanism improvement of a damper containing piston means in a chamber of a housing, an orifice in the piston means and Belleville springs disposed in the chamber between the wall of the chamber and the piston means on opposite sides thereof. The improvement comprises means, e.g. in the form of a member having slots therein, and disposed between one end of the Belleville springs and the adjacent chamber wall, providing fluid communication of the inner cavity and outer cavity of the chamber below and above the Belleville springs.

Abstract: A helicopter flight control system includes an automatic turn coordination system which provides a coordinating yaw command signal to the tail rotor of the helicopter. The system stores on command a trim attitude (e.g., signals indicative of bank angle, lateral ground speed, and lateral acceleration) about which automatic turn coordination is provided, thus providing the pilot with automatic turn coordination about attitudes other than wings level.

Abstract: An inflatable airfoil-shaped kite, which is framed by a front spar extending along the leading edge of the airfoil envelope, a rear spar extending along the envelope trailing edge, and two side spars extending along the side edges of the envelope. Upper and lower control lines are attached to end portions of the front and rear spars. Two control handles are attached to the opposite ends of the control lines, such that a person can manipulate the handles to move the kite through different maneuvers, e.g., reverse flight, power turning or pinwheeling. Each spar has end portions that can flex to generate localized drag forces which cause the kite to execute different maneuvers, as dictated by signals transmitted from the control handles through the control lines to end areas of the individual front, rear, and side spars.

Abstract: A helicopter fly-by-wire flight control system (21) includes a model following control system architecture which provides the pilot with maneuvering feel. Maneuvering feel is generated by varying the gain of a rate model (52) in the control system to schedule a constant sidearm controller force per g of load factor currently on the helicopter main rotor. This gain variation works in conjunction with control logic which requires the pilot to apply a nose up pitch command during steep banked turns in order to offset a control system induced downward (pitch) bias of the aircraft nose. The control system induced bias is generated only during steep banked turns, thus allowing the pilot to fly shallow banked coordinated turns without having to apply a nose up pitch command.

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 low speed 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: An elevated passenger car having an emergency exit feature. The passenger car is of the type supported such that there are substantially no obstructions between the underside of the car and the ground below it. The car includes a body having a passenger compartment and an opening through the body generally at one end thereof defining an exit from the passenger compartment to outside the body. An end section is pivotally mounted on the body at the one end. Fluid pressure actuated cylinders swing the end section between a closed position in which the end section closes the exit and an open position in which said exit is opened to the outside. An elevator supported by the end section in its open position lowers passengers from the elevated passenger car.

Abstract: Methods and apparatus for stability and maneuver control using rotatable nose strakes to control forebody vortices at medium to high angles of attack are disclosed. In one form, small left and right nose strakes are supported on a member or members forming the forward most contours of the forebody. Supporting of the two strakes on a single member allows rotation of the two in unison, the angular position thereof controlling the asymmetry of the forebody vortices at higher angles of attack, while support of each strake on a separate forebody nose member allows individual strake control for the same purpose. In another embodiment, the strakes may be mounted on a nose boom for rotation about the axis of the nose boom, whereby rotation of the strakes about the nose boom axis affects the development of the forebody vortices and the asymmetry thereof. Various embodiments and methods of operation thereof are disclosed.

Abstract: An improved mounting and carrying assembly for avionics displays including a swing handle with edge mounted sliding spring latches thereon for cooperating with holding pins disposed on a side of the display bezel that is not the front or viewing side.

Abstract: An improved brake system for use on moveable tool storage cabinets, hospital crash carts and the like which is comprised of brakes and a brake actuator and a brake release means, both operatively connected to the brakes. The improved brake system additionally contains an actuator bracket, whereby the actuation of the brake actuator causes the actuator bracket to swing and use available leverage, thereby allowing the brake system to be actuated using minimal force and to allow for the easy adjustment of tension of the brake system. The brake actuator and the brake release are both foot operated as well as being remotely located from the brakes. The brake system is adjustable and is capable of being fitted with a plurality of brakes.

Abstract: A satellite attitude control system is usable in the absence of any inertial yaw attitude reference, such as a gyroscope, and in the absence of a pitch bias momentum. Both the roll-yaw rigid body dynamics and the roll-yaw orbit kinematics are modelled. Pitch and roll attitude control are conventional. The model receives inputs from a roll sensor, and roll and yaw torques from reaction wheel monitors. The model produces estimated yaw which controls the spacecraft yaw attitude.

Abstract: A wave spring having uniformly positioned surface projections and predetermined consistent spring tension deflection is disclosed. The wave spring includes; a spring ring having projections in the ring's radial wall at predetermined positions within the wall thereby producing a wave spring having specific predetermined spring tension deflecting in response to specific loads. Deflection capability is maintained due to the position and heights of the projections. A wave spring which can be utilized in bayonet or non-bayonet style electrical connectors to provide a specified and predetermined spring tension deflection is also disclosed. A method of fabrication for a wave spring having uniformly positioned surface projections and predetermined consistent spring tension deflection is also described.

Abstract: A launcher for radio controlled flights of a model airplane, which releases the previously restrained model airplane upon the depression of a foot pedal thereof, thereby eliminating the need for any person to place his or her head in or nearby the exhaust stream of the operating engine at takeoff time, supporting: rotatable, releasible, restraining, spaced, arms, which, when raised, obstruct the forward motion of the model airplane, via the stabilizers thereof; the foot pedal; and a linkage system interconnecting the foot pedal with the rotatable, releasible, restraining, spaced arms.

Abstract: An all metal energy dissipator construction for dissipating kinetic energy force (F) by rolling balls (26) which are forced by a tapered surface (32) on an expandable sleeve (22) to frictionally load a force rod (15). The balls (26) are maintained in an initial position (FIG. 1) by a plate member (48) which is biased by a spring member (50). A spring member (52) returns the force rod (15) to its initial position after a loading force (F) is removed.

Abstract: There is suggested a circuit configuration for an electronically controlled anti-lock brake system, wherein upon the commencement of braking pressure control pressure fluid is pumped out of a supply reservoir (13) into the pressure chambers 7, 8) of the tandem master cylinder (1) which closes the inlet valves (14 to 17) of all wheels at the onset of the control action. It regulates the braking pressure on the imminently locking wheels by opening and closing the inlet valves and outlet valves (14 to 17 and 22 to 25) in a known fashion, while on the non-locking wheels it slowly adapts the braking pressure to the pressure prevailing in the tandem master cylinder (1) by way of pulsewise actuation at a predefinable pulse-pause ratio, that means opening and closing of the inlet valves (14 to 17).

Abstract: A helicopter flight control system (21) includes a model following control system architecture which operates in a velocity command mode at low ground speeds. The control system processes information from a variety of helicopter sensors (31) in order to provide a command signal to the main rotor (11) of the helicopter which results in a ground speed which is proportional to the input provided via a sidearm controller (29).

Abstract: A double-pivoting deployment system for aerosurfaces, such as wings or fins, for use on aerospace vehicles. Each aerosurface has an inner segment and an outer segment. The inner segment is pivotally connected at a first axis of rotation to the support structure of the aerospace vehicle. An outer side portion of the inner segment is pivotally connected at a second axis of rotation to an inner side portion of the outer segment. In operation, the outer segment is stowed adjacent to the body of the aerospace vehicle such that the surface plane of the outer segment is longitudinally aligned with the longitudinal axis of the aerospace vehicle, and the aerosurface span is longitudinally aligned with, the longitudinal axis of the aerospace vehicle. From the stowed position, the outer segment is first rotated substantially 90.degree.