Abstract: An improvement to close an opening formed in the leading edge of an airfoil when a slat is moved to its deployed position. The track which deploys the slat has a downward component of motion which leaves an opening in the wing leading edge that can cause premature stall in the opening is not closed. To close this opening, there is a door which is mounted about an axis of rotation that is positioned in a vertical plane generally parallel to the movement of the track. Further, the axis of rotation is slanted so that the door moves upwardly, rearwardly and laterally to its retracted position so as to permit the track to be retracted, and when the track is extended, a spring moves the door into its deployed position to close the opening.

Abstract: The present invention relates to a polymaneuverable canopy and to a process for its control by a parachutist. This canopy comprises windows distributed symmetrically in relation to a main plane of symmetry XY, and control lines connecting together the various windows in such a manner that a pull on one line (3) causes a rotation of the canopy to the right, while a pull on two lines (3, 4) causes a braking or rearward displacement of the canopy when the lines are situated one on each side of the plane of symmetry, and a pull on two lines (3, 5) situated on the same side of the plane of symmetry XY brings about a straight lateral displacement of the canopy.

Abstract: A shading device capable of compactly storing a flexible shade on a biased, window-shade type spring roller and controlled to deliver the shade selectively to either its operative shading or compact storage orientation.

Abstract: A work platform and helicopter assembly for working on a high-voltage power line such as an EHV power line. A work platform comprising a rectangular base of electrically conductive material is disposed transversely across a pair of helicopter skid tubes that extend longitudinally beneath the helicopter fuselage. The work platform is attached to the skid tubes such that the skid tubes may be laterally displaceable, upon landing, or take-off, with respect to the work platform. The work platform includes a workman supporting portion that extends laterally from the side of at least one skid tube to support a workman working on a high-voltage power line. The work platform, skid tubes and helicopter are electrically connected so that they will all be at the same electrical potential when working on a power line. The work platform may include a portion adapted to carry cargo between the skid tubes.

Abstract: A whistle kite is provided and contains a sound making device on its outer periphery which includes a flexible strap for emitting a sound like an airplane propeller as air passes by when the kite flies. In a modified form an adjustable tension holder is used which is activated by wind speed to vary pitch of the sound emitted by the flexible strap.

Abstract: A system for counteracting the effect of helicopter vibrations on a seat in the helicopter which seat includes a plurality of controllable air cells includes a means for varying the pressure of the cells and transducer means for sensing cell pressure and vibrations and for providing electrical signals representative thereof. Control means provide signals for controlling the means for varying and processing means process the electrical signals and provide driving signals for driving the control means. A processing means converts the electrical signals to provide driving signals which drive the control means to control the means for varying so as to counteract the changes in pressure in the air cells due to vibrations to eliminate or reduce the changes in pressure with this system, the pilot is isolated from the helicopter compared with prior art systems where the seat is isolated from the helicopter.

Abstract: An economical method of, and apparatus for, de-icing the skin panels (25) of aircraft employs electromagnetic solenoid actuators (1) which use normal supply voltages (43) available on aircraft to flex the skin panels slowly and rely upon abrupt termination (S) of the flexing pressure and the consequent fast natural elastic relaxation of the panels to break the bond between the panels and the ice accreted thereon, to shrug off the ice from the panels.

Abstract: An annular ring parachute intended for low altitude deployment with a low te of descent. This parachute comprises an annular ring parachute canopy having a central vent. Suspension lines are connected at one end to the outer edge of the canopy and at the other end to risers attached to a load-bearing harness. A restraining device is connected to the canopy which slows the opening of the central vent while the canopy inflates during deployment of the parachute. A pilot chute connected to the restraining means is adapted when inflated to apply a force to the restraining means to slow the opneing of the central vent.

Abstract: The invention provides a device for carrying under an aircraft and ejecting loads which are suspended from hooks which may be raised so as to be set under support arms hinged about longitudinal pins, lowering of the arms against a load which is hooked on allows automatic positioning of stops automatically limiting the raising of the arms under the action of springs to different levels depending on the diameter of the load hooked on. The stops may form part of stepped cams urged by springs into the position bringing the lowest possible stop into action.

Abstract: This is a device for suspending a store 66 from an aerodynamic support surface, such as an aircraft wing 12, and more specifically for improving upon single pivot decoupler pylons by reducing both frequency of active store alignment and alignment system space and power requirements. In the described embodiment, two links 36 and 42 suspend a lower pylon/rack section 60, and releasably attached store 66, from an upper pylon section 16 mounted under wing 12. Links 36 and 42 allow lower pylon section 66 to rotate in pitch about a remote pivot point 68. A leaf spring 30 connected between lower section 60 and electrical alignment system servomechanism 18 provides pitch alignment of the lower section 60/store 66 combination. Servomechanism 18 utilizes an electric servomotor 20 to drive gear train 21 and reversibly move leaf spring 30, thereby maintaining the pitch attitude of store 66 within acceptable limits. Damper 54 strokes when lower section 60 rotates to damp large oscillations of store 66.

Abstract: On a shaft (2) which carries a wheel there are mounted: firstly a toothed sector (3) which meshes with a rack (4) on a piston rod (5) which is a part of a double-acting hydraulic actuator (8); and secondly a cam (12) which acts on two rocking levers (13, 14) to apply a bolt (13B, 14B) against a stop face (10A, 10B) of the rod (5) when, by directly swivelling the wheel, the toothed sector (3) is disengaged from the rack (4).

Abstract: Emergency oxygen system of the type where masks are in compartments in the backs of aircraft seats uses an underseat compartment located under the plane of the seat cushion to house the large canister of chemicals which generate the oxygen when the canister is activated. A spring loaded cable connects the two compartments so that when any of the tether cords connected to each mask is pulled, a locking pin is pulled free from a release mechanism for the cable. Once released, the cable spring immediately moves the cable axially so its lower end can actuate another release mechanism in the canister compartment to activate the canister and produce oxygen. Since the canister can reach a temperature of over 500.degree. F., its removal from the seat back reduces any possibility of burns to passengers while allowing for a lower back height and less back thickness, thereby providing more passenger living space and less obstruction to viewing of visual entertainment.

Abstract: Landing gear mechanism includes a restrictor assembly containing a primary orifice for controlling the rate of instroke of the gear during landing and a taxi instroke bypass valve which provides for increased flow of hydraulic fluid within the gear whenever the gear engages a bump during taxiing to reduce the damping loads that would otherwise occur if all of the hydraulic fluid were required to flow through the primary orifice. The taxi instroke bypass valve assembly includes a bypass passage around the primary orifice, and a slide member which is axially movable relative to the orifice restrictor assembly for opening and closing the bypass passage.