Pulse Performance Analysis for Small Hypergolic-Propellant Rocket Engines

MALL rocket engine tests were conducted for the purpose of obtaining pulse performance data to aid in preliminary design and evaluation of attitude control systems. Performance data obtained from tests on two hypergolic rocket engines are compared with theoretical performance calculated from idealized chamber filling and evacuation characteristics. Factors which influence engine transient response during pulse mode operation are identified. The theoretical analysis is modified to obtain semiempirical performance equations for hypergolic rocket engines which are demonstrated to be reasonably accurate for two different engine configurations over a considerable range of duty cycles.