Abstract: A flying control system for aircraft in which a control circuit comprising a cable and quadrant pulley arrangement is arrange to effect pivotal displacement of a control surface in response to pilot's control demand, the control circuit including system disengagement means whereby if one of the cables is broken or becomes disconnected, the disengagement means will effectively isolate the control surface or pilot's control demand input means from adverse residual control forces arising as a result of the cable break or disconnect. By this arrangement the secondary or standby control system is isolated from adverse control limitations which may arise as a consequence of cable severance in , for example, the primary control device.

Abstract: A three stage rocket vehicle (11) having a large forward propellant tank (12) and a small aft propellant tank (13) axially aligned. Secured to the rear end of the aft propellant tank (13) is an engine mount structure (14) carrying rocket engines (15). Offset and secured to the propellant tanks (12,13) is a payload structure (18). The propellants from the large forward tank (12) are fed into the aft propellant tank (13) and the rocket engines (15) are fed propellants from the aft propellant tank (13). This arrangement enables the vehicle to parallel stage its use of engines and components.

Abstract: A helicopter (10) incorporates apparatus (15) for mounting a device such as an aerial or a sight (14) above a main sustaining rotor (13). The apparatus comprises first and second ring gears (16, 20) located respectively below and above the rotor, the first gear (16) being supported from helicopter structure (17) concentrically of an axis of rotation (11) of the sustaining rotor, support means (37) supporting the second gear and the device above the rotor in a manner permitting relative rotation of the rotor hub, and synchronizing means (25) rotationally fixed to the rotor hub and meshing with the first and second gears to retain the device stationary during rotation of the rotor system. In a preferred embodiment, positioning means are provided to rotate the first gear in either direction of rotation whereby the device can be rotated and selectively positioned independently of the rotation of the rotor.

Abstract: An aircraft crewman protective system properly positions the lower legs and eet of the crewman during emergency egress from an aircraft. The system includes a pair of plate members connected to swing outward from the under side of the crewman's console at each leg position and means for deploying the plate members at the time of ejection. Upon deployment, the plate members push the feet of the crewman backward guiding the feet and lower legs within a contact-free envelope during ejection without changing desired spinal position of the crewman.