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Abstract

A nacelle comprised of a rigid shroud and a support truss. The shroud encloses the truss and a rocket engine. The shroud is comprised of three sections, including a top section and two side sections. The top section has openings to permit the communication of lines for liquid propellant, electrical current, and hydraulic fluid between the engine and an attached flight vehicle. The two side sections are connected to each other by longitudinal field joints, and to the top section by a circumferential field joint. The rocket engine is attached to the flight vehicle by a gimbal allowing the engine to rotate relative to the flight vehicle about orthogonal pitch and yaw axes. A pair of actuators is located in the flight vehicle, one to control the rotation of the rocket engine about the pitch axis, and the other to control its rotation about the yaw axis. The truss is attached to the body of the rocket engine. The two actuators are respectively connected to the shroud at a pair of hard points where the shroud is attached to the truss. The shroud is also fastened to the rocket engine around the circumference of the nozzle's exhaust orifice, and around an attachment cone located adjacent to the gimbal. The actuator forces are transmitted to the rocket engine primarily through the truss. Since the shroud is attached to the rocket engine, the shroud rotates with the rocket engine relative to the flight vehicle.

First Claim