Lockheed Martin Corporation

Stephen G Justice

Joseph M Wurts

Steven P Ericson

Brian Quayle

Edward L Burnett

Kenneth G Gousman

Scott D Van Weelden

Grant E Carichner

Scott Wan Weelden

Larry Lipera

Michael C Carter

Paul H Nicholas

James W Taylor

John W Vinson

Charles D Erb

A vehicle is disclosed having a hull with a longitudinal, vertical and lateral axis, the hull further having front end and rear ends and first and second sides. A turbofan engine mounted in said hull, said engine having an exhaust duct. First and second front exhaust nozzles are mounted on the first and second sides of the front end of the hull. First and second rear exhaust nozzles are coupled to the first and second sides of said hull at said rear. All of the exhaust nozzles are rotatable from a vertically downward position to at least a partially horizontal direction and incorporating shudders to adjust the flow rate of exhaust gas from said turbofan engine therethrough. A duct system for coupling the exhaust duct of the turbofan engine to all of the nozzles.

Vehicle

The invention is an exhaust nozzle for an after-burning turbojet engine having an exhaust passage mounted in an aircraft, The exhaust nozzle includes a duct having an open first end coupled to the exhaust passage of the turbojet engine, a open second end, and a generally shallow U shape from the first end to the second end. The duct includes top, bottom and side walls, the top and bottom walls converging toward and diverging away from each other along the length of duct from the first to second ends and with the minimum cross-sectional area of the duct or throat positioned down stream of the lowest point of the V. The top wall is pivotally mounted to the aircraft at the first end of the duct so that the throat cross-sectional area can be adjusted to accommodate the increased gas flow when the after-burner is in operation. The bottom wall aft of the throat includes a surface contour for producing a coanda effect.

Exhaust nozzle for a turbojet engine

JASSM missile

The invention is a sealing assembly for reducing the gap between an aircraft's movable flight control member and adjacent structure thereto, the flight control member and structure having external surfaces and side surfaces facing each other. In detail, the assembly includes first and second flexible bulb seals mounted on the periphery of the side surface of both the flight control member and the adjacent structure forming an extension of the external surface of both. Each of the bulb seals includes a compressible foam bulk absorber core; the core having a bottom surface, a top surface generally parallel to the bottom surface, an outer side surface, and an inward facing surface at an acute angle to the top surface. A first sheet of dielectric material is bonded to the bottom surface of the core. A second sheet of flexible resistive material is bonded to the top, and sides of the core. A third sheet of flexible magnetic radar absorbing material is bonded to the second sheet. A fourth sheet of flexible abrasion resistant material is bonded over the third sheet.

Sealing assembly for reducing gaps between movable control surfaces of

The invention is an airborne vehicle. In detail, the invention includes a main body having a longitudinal, lateral and vertical axis. A pair of wings are pivotally mounted to the main body that are movable about an axis of rotation from a retracted position to an extended position external of the main body along the lateral axis. A linkage assembly for controlling the position of the wings is mounted within the vehicle that includes a guide assembly having an open ended slot aligned with the longitudinal axis thereof. First and second links have their first ends pivotally connected to the wings at a position offset from the axis of rotation of the wings, and the second ends thereof pivotally coupled to each other. A pin is rotatably coupled to the second ends of the first and second links and is movable from a first position within the slot wherein the first and second links are at an acute angle to each other to a second position external of the open end of the slot wherein the first and second links are rotated to a greater angular relationship. A spring is incorporated for urging the first and second links to the greater angular relationship. A latch is incorporated for securing the first and second links in the greater angular relationship after the pin exits the open end of the slot. An actuator is used to move the pin from the first position to the second position and, additionally, along the lateral axis when the pin is in the second position.

Airborne vehicle with wing extension and roll control

Growing community of inventors

Santa Clarita, CA, United States of America

Stephen G Justice