大倾角轨道航天器双轴驱动太阳翼构型参数优化方法

Configuration Parameter Optimization Method of Dual-axis Solar Wing for Spacecraft on Large Inclination Orbit

针对双轴驱动太阳翼展开后的运动包络对航天器设备产生的视场遮挡和空间干涉问题,基于机构运动学分析技术提出了一种太阳翼构型参数优化方法。首先,基于自然坐标方法建立太阳翼机构运动学模型,完成太阳翼运动状态的模拟;然后,分析太阳翼运动包络的影响因素,并明确可用于优化设计的参数,同时根据机构装配关系及视场要求形成约束条件;最后,建立以摆动角为目标的优化函数并进行优化分析。以轨道倾角86.4°、轨道高度780 km的航天器双轴驱动太阳翼构型优化为例,对其构型进行优化设计和优化结果验证分析,结果表明:优化后可获得太阳翼的最大摆动角为32°,此时太阳翼基板边缘与天线、敏感器视场最小距离为5 mm,太阳翼运动过程对设备视场不产生遮挡影响,满足工程应用要求,验证了优化方法的有效性,可为太阳翼工程设计提供理论参考,同时为航天器上可动设备构型优化及设备布局设计提供一种新的途径。

To avoid the occlusion of field of view and spatial interference for the spacecraft equipment caused by the motion envelop of dual-axis solar wing,a configuration parameter optimization method is proposed based on kinematic analysis of mechanism in this paper.Firstly,a kinematics model of the solar wing based on the natural coordinates method is built and its envelope state is simulated.Secondly,the influencing factors of the motion envelop are analyzed and the parameters that can be used to optimize are clarified,and the constraint equations according to the mechanism assembly relationship and the field of view constraints are established.Finally,the optimization function with the swing angle as the target is formed and solved.Taking the dual-axis solar wing of spacecraft whose orbit inclination is 86.4°and orbit altitude is 780km as the study case,the configuration parameters are optimized and verified.The results show that the maximum swing angle of the solar wing can be obtained is 32°,and the minimum distance between the edge of the solar wing and the field of view of antenna/optical sensor is 5mm under this condition.The motion envelope of the solar wing doesn’t block the field of view of the equipment and the results meet the requirement of engineering application.The optimization parameters provide a theoretical reference for the design of the solar wing and the validity of the method proposed is verified.The configuration parameter optimization method adopted in the paper also provides a new way for the layout design of equipment with movable components on spacecraft.