Abstract: A composite wing for an aircraft comprises a plurality of elongated hollow one-piece composite spars arranged in juxtaposed generally parallel relation in an array defining an airfoil with a composite skin disposed about said assembled spars.

Abstract: A near supersonic aircraft comprising an airframe that maintains subsonic air flow thereover within the flight envelope of the aircraft. The airframe comprises a right circular conical forward fuselage section, a right circular cylindrical intermediate fuselage section defining a passenger compartment, and an aft fuselage section having a generally circular frontal cross section and a generally rectangular aft cross section.A submerged semi circular air inlet is disposed between the intermediate and aft fuselage sections at the top thereof. A pair of forwardly swept wings are joined to the fuselage adjacent the circumferentially spaced ends of the air inlet whereby air flow over the fuselage and along the leading edges of the wings is directed into the air inlets at subsonic speeds and at all attitudes of the aircraft within its flight envelope.

Abstract: A medium bypass turbofan engine including a fan mounted on a low pressure shaft and positioned at the inlet of the engine; an intermediate pressure single-stage axial compressor carried by the low pressure shaft and positioned to receive a working airstream portion of the air discharged by the fan; a single-stage high pressure centrifugal compressor positioned to receive the output of the intermediate pressure compressor and carried by a high pressure shaft received telescopically over the low pressure shaft; an annular burner positioned to receive the output of the high pressure compressor; an annular slinger carried by the low pressure shaft and arranged to inject fuel into the burner; a high pressure single-stage axial turbine positioned to receive the output of the burner and carried by the high pressure shaft; and a low pressure multi-stage axial turbine positioned to receive the output of the high pressure turbine and carried by the low pressure shaft.

Abstract: The disclosure relates to an improved recuperative heat exchanger for a turbine engine. Heat exchanger modules have discrete passages therein for the relatively high pressure compressor discharge air and relative low pressure exhaust gases. A continuous seal is provided at each end of the exhaust passages in the heat exchanger that is expandable into positive engagement with the heat exchange module.

Abstract: The disclosure relates to a vehicle that is sustained in flight solely by thrust from a jet engine and directionally controlled by shifting the center of gravity of the vehicle relative to the thrust axis of the engine.