导弹抛底罩过程建模与分析

导弹冷发射采用底罩保护一级发动机,发射后需要将底罩抛离。为了防止底罩撞击地面设备,采用了铰链连接的利用弹簧作为分离能源的侧抛分离方案。对分离运动及动力学特性进行了研究,建立了底罩旋抛过程的运动学和动力学模型。对导弹底罩分离过程中受到的气动力、弹簧力和空气负压力等多种不确定性因素进行了灵敏度分析,通过仿真得到了底罩脱离角度和弹簧相关参数对分离过程的影响,并进行了参数优化。最后对考虑多个偏差影响下的分离方案进行正交仿真试验,得到了主发动机点火时底罩质心散布范围和底罩落点范围。

Modeling and analysis of separation for missile tail cover

Tail cover, which is used to protect the first stage engine during cold launch of missile, should be thrown after launch. In order to prevent the tail cover from hitting the ground equipment, the detailed separation scheme of lateral fling with connected hinge is adopted using spring as separation energy in the separation. The separation movements and dynamic characteristics are studied, and the kinematics and dynamics models of separation are built. The sensitivity analyses of multiple uncertain factors influencing tail cover are conducted such as aerodynamic force, spring force and negative air pressure during separation. Moreover, the impacts of separation angle of tail cover and the related coefficients of spring on separation process are obtained by simulating and optimizing the coefficients. Ultimately, centroid spreading range when the main engine gets started and landing point's range of tail cover are achieved by the orthogonal test for separation scheme considering complex deviations.