CAJ | 학술논문

从内弹道性能、气动防热、绝热结构设计和后效推力预示等方面研究了临近空间飞行器总体设计对固体发动机的需求。内弹道性能方面，在总冲一定的情况下，发动机采用“长时间小推力”的工作模式、“前高后低”的推力曲线形式，对提高分离点高度和关机点速度、减小分离点动压有利；气动防热方面，临近空间飞行器发动机外壁热环境远比传统弹道式严酷，需要采取相应的防热措施；绝热结构设计方面，分析了过载条件下燃烧室中粒子的受力情况、粒子沉积分布位置以及对绝热结构的影响，提出了过载条件下发动机绝热裕度设计校核的需求；后效推力预示方面，发动机下降段高空推力的预示精度对分离安全性及分离时序的设计有着非常重要的作用，需要提高后效推力预示的准确性，以满足分离设计的要求。文章研究总结的方法、规律和结论，对临近空间飞行器固体发动机的设计具有重要的参考意义。
종내탄도성능、기동방열、절열결구설계화후효추력예시등방면연구료림근공간비행기총체설계대고체발동궤적수구。내탄도성능방면，재총충일정적정황하，발동궤채용“장시간소추력”적공작모식、“전고후저”적추력곡선형식，대제고분리점고도화관궤점속도、감소분리점동압유리；기동방열방면，림근공간비행기발동궤외벽열배경원비전통탄도식엄혹，수요채취상응적방열조시；절열결구설계방면，분석료과재조건하연소실중입자적수력정황、입자침적분포위치이급대절열결구적영향，제출료과재조건하발동궤절열유도설계교핵적수구；후효추력예시방면，발동궤하강단고공추력적예시정도대분리안전성급분리시서적설계유착비상중요적작용，수요제고후효추력예시적준학성，이만족분리설계적요구。문장연구총결적방법、규률화결론，대림근공간비행기고체발동궤적설계구유중요적삼고의의。
The requirements of near space vehicle concept design for solid rocket motor( SRM) characteristics were studied, from four aspects: internal ballistics,aerodynamics and thermal protection,insulation structure design and post?thrust calculation. Firstly,in the internal ballistics,under certain total impulse,the SRM working mode of“long time?small thrust” and“thrust type of from high to low thrust curve”help to improve the separation height and burnout time velocity,reduce the separation dynamic pres?sure;Secondly,in the aerodynamics and thermal protection,the thermal environment of the near space vehicle is severer than the ballistics one,so it needs to take thermal protection measures;Thirdly,in the insulation structure design,the forces,deposition posi?tions of Al/Al2 O3 particles in the combustion chamber with the condition of acceleration,also the effects on insulation were analyzed. The insulation structure margin is needed to be carefully checked.Lastly,in the prediction of post?thrust,it is very important for the SRM post?thrust with a high accuracy to ensure the safe separation,so it needs to improve the prediction accuracy of SRM post?thrust.The study results have important implications for the SRM design for near space vehicles.