Accession Number : ADD006116

Title :   Ejection Seat with Pitch, Roll and Yaw Control.

Descriptive Note : Patent Application,

Corporate Author : DEPARTMENT OF THE NAVY WASHINGTON DC

Personal Author(s) : Stone,W James ; Thomas,Lovic P

Report Date : 24 May 1979

Pagination or Media Count : 12

Abstract : The present invention provides an aircraft ejection seat having two gimballed rocket motors which may be attached either below or behind the seat. A control circuit causes the gimballed rocket motors to rotate in response to pitch and yaw command signals. A pitch command signal alone causes both gimballed rocket motors to have identical angular displacements so that the thrust vectors from the gimballed rocket motors are always parallel. A yaw command signal, either alone or combined with a pitch command signal, causes the gimballed rocket motors to have different angular displacements; and the non-parallel thrust vectors cause a torque about the yaw axis of the ejection seat. The gimballed rocket motors are moved by servo-controlled hydraulic actuators connected between the rocket motor housings and the frame of the ejection seat. A yaw rate signal is processed by a computer to determine the yaw angle of the seat. Yaw rate and yaw angle signals are combined by a summer to produce a negative yaw feedback signal which is connected to the input of the control system.

Descriptors :   *Patent applications, *Ejection seats, *Thrust vector control systems, Rocket engines, Gimbals, Hydraulic actuators, Hydraulic servomechanisms, Pitch(Motion), Yaw, Roll

Subject Categories : Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE