关键词: 固液混合火箭发动机;推力控制;稳定性;固体火箭发动机

Abstract: The solid rocket motor (SRM) with spray-liquid consists of control system, liquid oxidant (H2O2) extrusion system and SRM with varied section injector.At certan assumption dynamic equations have been set up for every link of the feedback control system. For time-varied nonlinear system, constant coefficient and quasi-linear governing equations at the equilibrium point have been obtained by zero dimension and linear-ization.By means of transfer function and parameter stability theory, equilibrium steady boundar equations and steady criteria have been determined and solved. Investigation indicates that thrust controllable SRM with spray-liquid differs essentially from conventional SRM in stability. Injection ratio, pressure exponent (n) and tank pressure are main design parameters affecting stability, stability analysis should centre on initial phase of motor oqeration under the small thrust stage. Analysis shows that the larger injec-ion ratio or free volume of combustion chamber is the better stability. And pressure exponent at middle or high n value is favourable to stability.

Key words: Hybrid propellant rocket engine;Thrust control;Combustion stability;Solid rocket enging