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.

Abstract: The suspension device is interposed between the rotor and the fuselage of the helicopter for filtering the vibration exciting forces and moments coming from the rotor. In this helicopter, a speed reducer (1) is provided in a housing mounted on the fuselage (22) by rigid oblique bars (28). According to the invention, there are disposed around the housing of the speed reducer, in a number equal to the number of rigid oblique bars (28), monodirectional antiresonant means (20,21,23,23a,23b,25) connecting the upper ends of the rigid oblique bars (28) to the speed reducer (1).

Abstract: An improved shuttle with variable internal volume is provided by the present invention. Space shuttle orbiter 10 includes a telescoping main propulsion unit 20. This main propulsion unit 20 contains the main rocket engines 22 and fuel tanks 21 and telescopes into the shuttle. A variable cavity 30 is located between this unit 20 and the crew compartment 25. Accordingly, the positioning of the telescoping main propulsion unit 20 determines the volume of the variable cavity 30. Thus, the volume of the variable length of the entire shuttle 10 may be increased or decreased to achieve desired configurations for optimal storage. In one embodiment of the present invention, paylod 35 also telescopes within variable cavity 30.

Abstract: The present invention provides a vertical takeoff and landing aircraft vehicle in which a ducted fan with upwardly directed inlet discharges air generally horizontally across a segmented circular wing. Said wing segments are individually controllable in pitch and each includes a spoiler and split flaps to increase effectiveness and sensitivity in lifting and controlling the aircraft. Directional stability and thrust for horizontal movement is provided by controls directing different proportions of total airflow to the various segments around the aircraft and varying the direction of said airflow both radially and vertically. Power failure protection is provided by means for maintaining free rotation of the fan until needed to provide lift at touchdown.

Abstract: A satellite adapted to be spin-stabilized in geostationary orbit having, coaxial with a spin rotation axis, a satellite surrounded with a solar generator. At least two equipments including an apogee maneuver system are disposed along the rotation axis. A set of generally annular antennas including at least one picture transmission antenna is disposed on one of the NORTH and SOUTH faces of the satellite so as to leave at its center a cylindrical space along the spin rotation axis to house one of the equipments. The other of the equipments is disposed on the other of the NORTH and SOUTH faces.

Abstract: Airfoil canopy for paragliders made of non-porous cloth and comprised of a number of parallel primary air chambers (12) having upper surfaces (14), lower surfaces (16), open front ends (18), tail ends (20) and ribs (22). Secondary chambers (30) are provided within each primary chamber together with an opening (36) to the secondary chamber and a flap or curtain member (40) for blocking the back flow of air out of the secondary chamber in the event of air pressure loss in the primary chamber.

Abstract: An engine and lift unit for rotary wing aircraft together with means for balancing of the rotational torque of the said wings is shown. The rotational torque is balanced by a blower propeller, disposed horizontally below the rotor, inside an enclosure including a vertical duct surrounding the blower propeller and whose lower open end exits under the fuselage of the aircraft. A horizontal duct opens into an intermediate zone of the vertical duct and exits out the rear of the aircraft. An adjustable shutter assembly is disposed in the junction of the two ducts allowing the creation of two adjustable air flows, one directed vertically downwards and the other directed towards the rear of the aircraft. The aircraft also has fixed wings, flaps, rudders and controls so the pilot can operate the aircraft in flight.