大L脉冲发动机内弹道性能的实验研究

A STUDY OF SWIRLING SOLID ROCKET MOTOR

本文介绍了远程火箭中间段制导地面动态联试用的大Ｌ＊脉冲发动机内弹道性能实验研究的情况，包括静态点火试验、动态旋转试验和高低温环境试验的情况。试验数据与设计数据符合良好。试验结果表明，脉冲发动机的主要性能满足与弹上控制系统动态联试的要求，但也带有大Ｌ＊发动机的某些明显特点。

Abstract The effect of swirling on solid rocket motor performance is investigated analytically and expermentally.The investigation on burning rate sensitivity in detail is completed.The prediction programs of transient burning rate,steady state burning rate and internal ballistic performance are established,the calculation results are compared with the experimental data.The effect of propellant ingredients on the swirling solid motor performance is also revealed.Through a series of researches,the following conclusions are reached:if the aluminium content of the propellant remains constant,the greater the diameter of aluminium particles,the higher the burning rate sensitivity;if the diameter remains constant,the greater the content,the higher the sensitivity.For a high burning rate propellant,there exist a higher threshold of acceleration and a lower burning rate sensitivity.For star grain motor,the effect of swirling flow on its internal ballistic performance is smaller,than in the motor with conocyl grain.The prediction results of the theoretical model are consistent with the experimental results.The theoretical model can be applied to engineering design.