CAJ | 학술논문

研究了变推力固体火箭发动机调节参数对调节特性的影响，对流场进行了三维数值模拟，在考虑中心对称流场对喷管侧向力作用的情况下，得出发动机工作过程参数。针对不同的喉部装配结构，分析了推力调节范围和结构所受滚转扭矩的变化，发现喉部结构间隙使得调节范围和滚转扭矩减小。对导致调节过程推力延迟的关键因素进行了分析，发现调节速度和自由容积与流场参数延迟时间关系密切。计算结果与实验数据吻合较好，可为变推力发动机的设计提供参考。
연구료변추력고체화전발동궤조절삼수대조절특성적영향，대류장진행료삼유수치모의，재고필중심대칭류장대분관측향력작용적정황하，득출발동궤공작과정삼수。침대불동적후부장배결구，분석료추력조절범위화결구소수곤전뉴구적변화，발현후부결구간극사득조절범위화곤전뉴구감소。대도치조절과정추력연지적관건인소진행료분석，발현조절속도화자유용적여류장삼수연지시간관계밀절。계산결과여실험수거문합교호，가위변추력발동궤적설계제공삼고。
In order to understand the regulating characteristics of variable thrust motor, simulation of 3D flow field during thrust regulating was implemented. The torsional moment caused by centrosymmetric flow field was considered.By means of numerical sim-ulation, the regulating characteristics were obtained,and assembly clearance of nozzle structure was analyzed at the same time.Regu-lating speed and free volume were investigated as the main influence factor on the delay of thrust regulating.It was found that assem-bly clearance reduce thrust regulating range and axial moment significantly.High regulating speed and big free volume delay the time of flow field stabilization.Numerical result can provide a reference for structure and regulating design of variable thrust SRM.