Abstract: Protectors for certain elements such as fuel injectors and flameholders used in conjunction with the ramjet phase of an integral rocket ramjet.In the preferred embodiment slip-on caps of a high temperature material such as graphite are used to protect the fuel injectors and flameholders. The caps are installed and the solid boost propellant packaged about them. Following boost burnout the initial fuel pressurization for transition to ramjet operation would remove the caps allowing operation in a ramjet mode.

Abstract: An air bag landing system for an aircraft. The landing system has an air bag assembly which is stored in the fuselage of the aircraft during cruise and which extends for landing. The assembly consists of a rigid arm with either two or three folding portions and an inflatable bag attached to the underside of the arm. The inflatable bag cushions the impact of the aircraft at landing. Actuators are provided to extend and retract the assembly.

Abstract: An inlet for a supersonic aircraft capable of varying capture area. The inlet is of a rectangular shape, and has a ramp attached to the top and bottom of its fore end. The ramps are positioned to maximize air capture area during supersonic flight. At subsonic speeds, the ramps are moved to a position which slightly reduces the capture area. The ramps may have a blunt edge or sharp edge, and are controlled by an actuator located within the aircraft and connected to the ramps by suitable linkage. The ramps have a smooth contour provided by a flexible outer skin to reduce aerodynamic drag during operation of the aircraft.

Abstract: An air cushion landing system for an aircraft. The landing system has an air cushion assembly which is stored in the fuselage of the aircraft during cruise and which extends for landing. The assembly consists of a rigid arm with two folding portions, inflatable bags attached to the underside of the arm, and flaps to define an area of cushion air. The inflatable bags provide primary attenuation of landing impact. Actuators are provided to retract the assembly following takeoff and extend it for landing.

Abstract: A novel flap actuator control unit for a hydrofoil craft. The control unit includes an actuator disposed in a submerged housing located in proximity to the hydrofoil control flaps, thus eliminating long, precise, and costly linkages needed on conventional flap actuator control units. To prevent sea water leakage into the actuator housing, the housing is filled with an inert fluid, such as oil, from a surge tank disposed above the waterline. When the hydrofoil is underway, the fluid is compressed or expanded by a free floating piston which responds to the external dynamic pressure thereby a balance between internal and external pressure is maintained and leakage into the actuator housing avoided.