Development of a Fluidic Control System for an Aircraft Ejection Seat

摘要

The objective of this program was to develop a fluidic control system capable of stabilizing an ejection seat in the pitch plane during the rocket motor burn portion of an ejection. This document describes the design, fabrication, and laboratory testing phase of the fluidic control system development. The control system consists of a fluidic vortex rate sensor and five fluid amplifiers. During laboratory test the system has demonstrated the capability to sense input rotation and provide as an output a high-pressure, high-flow corrective signal. This corrective signal is designed to produce a control moment by being injected into a rocket motor nozzle through secondary injection ports. The next phase of this program is to install the control system on an injection seat and demonstrate the performance of an actual seat ejection. (Author)