CAJ | 학술논문

为了保证某火箭炮闭锁机构具有统一的闭锁力，提出了一种施加闭锁机构预紧力的控制方法。通过试验测试了闭锁机构闭锁力的大小，结果表明该控制方法可靠，闭锁机构的闭锁力达到设计值；为了研究闭锁机构发射条件下的工作性能，基于有限元动力学理论，建立了发射条件下闭锁机构的有限元模型。通过计算，得到了闭锁机构在不同预紧力下的响应参数，并分析了发射时定向钮与闭锁机构之间的相互作用历程，指出闭锁机构的闭锁力为发射时定向钮所受的最大约束力。
위료보증모화전포폐쇄궤구구유통일적폐쇄력，제출료일충시가폐쇄궤구예긴력적공제방법。통과시험측시료폐쇄궤구폐쇄력적대소，결과표명해공제방법가고，폐쇄궤구적폐쇄력체도설계치；위료연구폐쇄궤구발사조건하적공작성능，기우유한원동역학이론，건립료발사조건하폐쇄궤구적유한원모형。통과계산，득도료폐쇄궤구재불동예긴력하적향응삼수，병분석료발사시정향뉴여폐쇄궤구지간적상호작용역정，지출폐쇄궤구적폐쇄력위발사시정향뉴소수적최대약속력。
In order to ensure the unified force of the locker of some rocker launcher,a control method of applying pre-tightening was proposed. The locking force was tested via experiments and the results indicate that the control method is reliable and the locking force of the locker meets the design value. To study the working property of the locker under launch conditions,the finite element model of the locker was estab-lished based on finite element dynamics theory. By calculation,the response parameters of the locker were obtained under different pre-tightening force,and the analysis of history interaction between the guide knob and the locker was presented. It is pointed out that the maximum binding of the guide knob is the locking force of the locker.