多体飞行器展开过程动力学特性研究

Dynamics modeling and flight characteristics of folded multi-body aircraft

基于多刚体系统动力学理论研究了折叠型多体飞行器动力学建模的方法,考虑多体飞行器为一个完整的多刚体系统,建立了能够完整描述多体飞行器水平发射后自由展开过程的动力学模型。在多体动力学模型的基础上,添加了飞行单元之间柔性连接的卷曲弹簧力矩和阻尼力矩模型。以某折叠型三段翼飞行器为算例进行了数值仿真计算,研究了飞行单元之间的柔性连接刚度系数对折叠型多体飞行器自由展开过程动力学特性的影响以及柔性连接刚度与最大初始折叠角之间的相互关系,并确定了柔性连接刚度系数与最大初始折叠角之间的稳定域包线。

This paper studies the dynamic modeling method of fold-able multi-body aircraft based on the dynamics theory of multi-body system.Considering the multi-body aircraft as a complete multi-rigid body system,the dynamic model for the free unfolding process of the multi-body aircraft after horizontal launch is established.On the basis of the multi-body dynamics model,the coil spring moment model and the damping moment model for the flexible connection between the flight units are added.Taking a certain type of fold-able three-section wing aircraft as an example,the numerical simulation calculation is carried out.The influence of the flexible connection stiffness coefficient between the flight unit on the dynamic characteristics of the fold-able multi-body aircraft in the free deployment process and the relationship between the stiffness of the flexible connection and the maximum initial folding angle are studied.Finally,the stability envelope between the stiffness coefficient of the flexible connection and the maximum initial folding angle is determined.