一种挠性动力学模型解耦及局部迭代方法

Decoupling and Partial Iterative Calculation Method of Flexibility Dynamics

带有大型帆板、大量推进剂的航天器挠性模态阶数可以达到上百阶,其挠性动力学要实现毫秒级周期迭代运算,需要高性能的计算机。基于挠性模态η和星体转动ω解耦、局部迭代等措施避免迭代误差导致挠性动力学运算发散,解耦后的挠性动力学模型参数K_1,K_2,I^(-1)等可以离线计算,从而减小了迭代计算量,降低了对计算机的性能要求,且易于工程实现。仿真验证了解耦及迭代运算方法的有效性,仿真结果表明计算速度可以提高约2个数量级。

Some spacecrafts have large solar panels and a lot of propellant.These spacecrafts with flexible modes can reach hundreds of order.High-powered computers are needed for these spacecrafts' flexibility dynamics iterative operation within several milliseconds.The measures of decoupling flexibility vibration from body rotation and partial iterative calculation were applied to avoid no convergence of the flexibility dynamics iterative operation because of iterative computing error.The parameters of flexible dynamics model which were decoupled could be calculated off-line.The amount of calculation was decreased for the decoupled flexibility dynamics model as parameters could be computed before simulation.The method doesn't need high-powered computer and is applicable to engineering application.The simulation result validates the decoupling and the iterative operation.The calculation speed can be improved by about two orders of magnitude.