点火状态对固体火箭燃气流动影响的实验研究

AN EXPERIMENTAL STUDY ON INFLUENCE OF IGNITION STATE ON FLOW PARAMETERS OF SOLID ROCKET MOTOR JET

结合固体火箭燃气射流的特点 ,开发了基于皮托管技术的多点压力参数实验测量装置 ,运用实验的方法 ,对燃气射流流场进行了研究 .针对不同的发动机点火状态 ,在射流轴线的不同距离上对一系列测点位置的总压参数进行了测量 .研究证明该试验测试装置对燃气射流流场的测试是适宜的 ,实验数据分析表明高低温点火状态对固体火箭燃气流场具有一定的影响作用 。

Considering the features of solid rocket motor jet, a kind of experimental equipment based on the pitot tube technology for measuring the multi-point pressures was developed. The motor jet flow was studied with experimental methods. According to the different motor ignition states, a series of total pressure values of observed points on the respective jet axis distances was measured. The relevant results prove that this equipment is suitable for testing motor jet flow. The analysis of the experimental data indicates that ignition state in high and low temperatures has some influences on the flow of solid rocket motor jet. The conclusion is significant to the research of solid rocket weapons.