【作者】 朱卫兵； 张宪亮； 吴限德； 宋婷；

【Author】 ZHU Weibing;ZHANG Xianliang;WU Xiande;SONG Ting;Harbin Engineering University;Northwestern Polytechnical University;

【机构】 哈尔滨工程大学； 西北工业大学；

【摘要】 针对挠性航天器在轨运动过程中的动力学建模问题,综合考虑航天器在轨运动过程中存在的姿轨运动耦合、挠性振动耦合因素,利用对偶四元数的方法,建立挠性航天器姿轨一体化动力学模型,并对航天器的轨道、姿态与挠性振动之间的耦合关系进行定量分析。挠性航天器姿轨一体化动力学模型可以紧凑描述挠性航天器的姿态-轨道-振动耦合关系,模型简单、计算高效,为实现挠性航天器高精度控制奠定基础。通过数学仿真对建立的动力学模型进行验证,证明了模型的正确性。更多还原

【Abstract】 A dynamic modeling method of the flexible spacecraft is proposed in this paper. Considering the attitude and orbit coupling and flexible vibration coupling factors,the dual quaternion method is used to establish the dynamic model. On the basis,the coupling relationship among the orbit motion,attitude motion and flexible vibration is analyzed.The integrated dynamics model proposed in this paper can compactly describe the attitude-orbit-vibration coupling relationship of the flexible spacecraft. The model is simple and computationally efficient,which lays the foundation for the realization of high-precision control of the flexible spacecraft. Finally,mathematical simulation is provided to verify the validity of the model.更多还原