失效航天器等离子羽流消旋建模与最优制导研究  

Modeling and Optimal Guidance of Plasma Plume Detumbling for Failed Spacecraft

作　　者：代洪华 左宸昊 赵弘骞 商崇余 DAI Honghua;ZUO Chenhao;ZHAO Hongqian;SHANG Chongyu(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China;The National Key Laboratory of Aerospace Flight Dynamics,Xi’an 710072,China)

机构地区：[1]西北工业大学航天学院,西安710072 [2]航天飞行动力学技术国家级重点实验室,西安710072

出　　处：《空间控制技术与应用》2023年第3期54-63,共10页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(12072270);国家重点研发计划资助项目(2021YFA0717100)。

摘　　要：为克服等离子羽流无序性强、动力学模型复杂的问题,使用神经网络建立消旋力矩快速计算模型,实现高效、高精度的消旋动力学解算.针对传统制导律难以处理复杂翻滚目标的弊端,提出章动抑制原则,并建立自旋章动耦合目标的最优羽流指向制导律.仿真结果表明基于神经网络的高效计算模型可在同等精度下大幅度减少力矩计算时间,最优制导律可实现复杂章动目标的快速稳定.本研究从在轨计算与任务执行策略两方面显著提升了消旋效率,为利用等离子羽流的在轨操控任务奠定了理论基础.In order to achieve efficient and high-precision torque calculation,a plasma flow detumbling model based on neural network is established.To address the limitations of traditional guidance laws in handling complex tumbling targets,the principle of nutation stabilization is defined,and an optimal guidance law is designed for plasma flow direction.Simulation results indicate that the rapid dynamics model based on neural network can significantly reduce the torque calculation time while maintaining the same precision.The optimal guidance law can rapidly stabilize complex nutation target.This study significantly improves detumbling efficiency from both on-orbit calculation and mission strategy,laying the theoretical foundation for on-orbit service based on plasma flow.

关 键 词：失效航天器 消旋 等离子羽流 神经网络 最优制导律 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]