Ji Yi, Zhang Huan
School of Astronautics, Harbin Institute of Technology, Harbin, 150001, China.
Frontier Science Center for Interaction between Space Environment and Matter, Harbin, 150001, China.
Sci Rep. 2025 May 3;15(1):15525. doi: 10.1038/s41598-025-99967-w.
With the development of aerospace technology, rigid-flexible coupling spacecraft with strong nonlinearity dominates, bringing huge challenges for numerical tools. This paper aims to accurately and quickly analyze the dynamic behavior of rigid-flexible coupling spacecraft. In our work, rigid body and flexible body are both described by Euler parameters for avoiding singular angles. Then, for this type of strong nonlinear dynamic system, the BN-stable method that is unconditionally stable for nonlinear initial value problems proposed by the first author is introduced to solve the transient responses. To keep the accuracy of the numerical rotation matrix, the relation between the angular velocity and Euler parameters, and the constraint in the level of velocity, are introduced to reformulate the original BN-stable method. Through the dynamic analysis for rigid satellite bodies and flexible solar wings, we find that the proposed strategy can effectively simulate the dynamic responses of spacecraft, and compared to the currently popular strategy, our strategy enjoys considerable advantages in accuracy, stability, and dissipation.
随着航天技术的发展，具有强非线性的刚柔耦合航天器占据主导地位，这给数值工具带来了巨大挑战。本文旨在准确、快速地分析刚柔耦合航天器的动力学行为。在我们的工作中，刚体和柔性体均采用欧拉参数进行描述，以避免奇异角。然后，针对这类强非线性动力系统，引入了第一作者提出的对非线性初值问题无条件稳定的BN稳定方法来求解瞬态响应。为保持数值旋转矩阵的精度，引入角速度与欧拉参数之间的关系以及速度层面的约束，对原有的BN稳定方法进行重新表述。通过对刚性卫星本体和柔性太阳翼的动力学分析，我们发现所提出的策略能够有效模拟航天器的动力学响应，并且与当前流行的策略相比，我们的策略在精度、稳定性和耗散方面具有相当大的优势。
