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本文介绍运载火箭与支撑结构分离时产生瞬态响应的模拟方法。该方法利用一个不限定界面自由度数的运载火箭与支撑结构的全模型。同时通过把变化项引入运动方程的右面来考虑逐点分离时结构数学模型所发生的变化。这样,分析人员就可采用一组系统振型来模拟火箭从抑制状态到自由—自由状态的过渡。
This article describes a simulation method that produces a transient response when the launch vehicle and support structure are separated. The method utilizes a full model of launch vehicle and support structure that does not limit the degree of freedom at the interface. At the same time, by introducing the change term to the right side of the equation of motion, we consider the changes of the mathematical model of the structure in the case of point-by-point separation. In this way, analysts can use a set of system modes to model the rocket’s transition from a suppressed state to a free-free state.