Abstract

An approach to the development of a dynamic model of one of the key stages of the flight of rocket and space systems is presented: the separation of large-sized structures. The importance of taking into account the elastic properties of separated objects is justified. Based on the assumptions typical of the process under study (small angular velocities of relative motion during separation compared to the lower frequencies of the separated objects), the partial differential equations of elastic vibrations are replaced with a system of ordinary differential equations describing the excitation of a limited number of lower order modes, which made it possible to formulate an efficient approach that allows a clear mechanical interpretation: the general motion during separation is decomposed into a transport motion (rotational and translational as a whole) and small elastic relative vibrations, described in a universal modal formulation. The process of separation of an aerospace aircraft and a launch vehicle is analyzed. The effect of loss of the relative separation velocity due to elastic vibrations is revealed, and a recommendation for the rational arrangement of separation tools is formulated.

中文翻译：

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大型弹性结构分离动力学模型

摘要

提出了一种开发火箭和空间系统飞行关键阶段之一的动态模型的方法：大型结构的分离。考虑分离物体的弹性特性的重要性是合理的。基于所研究过程的典型假设（与分离物体的较低频率相比，分离过程中相对运动的角速度较小），弹性振动的偏微分方程被替换为描述激发的常微分方程组有限数量的低阶模式，这使得可以制定一种有效的方法，从而提供清晰的机械解释：分离过程中的一般运动被分解为传输运动（旋转和平移作为一个整体）和小的弹性相对振动，描述在通用模态公式中。分析了空天飞机与运载火箭分离的过程。揭示了弹性振动导致的相对分离速度损失的影响，并提出了合理布置分离工具的建议。