Rotation Formation Flying of Three Satellites Using Tethers
Rotation Formation Flying of Three Satellites Using Tethers
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DOI：
10.2514/1.14251
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发表时间：
2004-11
影响因子：
1.6
通讯作者：
K. Kumar;T. Yasaka
中科院分区：
文献类型：
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作者：
K. Kumar;T. Yasaka
探讨了利用柔性系绳实现卫星旋转编队飞行的可行性。该系统由三颗卫星组成，通过系绳连接，位于三角形结构的顶点。卫星被建模为点质量，系绳被认为是无质量的。通过拉格朗日方法，得到了在椭圆轨道上运动的系统的运动控制方程的一般形式，包括不同的卫星质量和系绳长度。开环系绳的部署和回收的法律已经制定。对所提出的约束系统的非线性运动方程进行了数值仿真，并进行了平衡分析，结果表明了实现三颗卫星在轨道平面内编队飞行的可行性。此外，平衡分析导致有用的设计准则的形式的不等式约束的系统参数。在三颗卫星质量相等的情况下，系统在轨道平面内稳定自旋运动的自旋速率临界最小值为0.58倍轨道速率。最后，各种系统参数的影响，以及系绳的部署和检索系统的响应进行了研究。
The feasibility of rotating formation flying of satellites using flexible tethers is explored. The system is composed of three satellites connected through tethers and located at the vertices of a triangle-like configuration. The satellites are modeled as point masses, and tethers are considered massless. The general formulation of the governing equations of motions of the system moving in an elliptic orbit and including different satellite masses and tether lengths is obtained through a Lagrangian approach. The open-loop tether deployment and retrieval laws have been developed. Results of numerical simulations of the nonlinear governing equations of motion of the proposed constrained system and an equilibrium analysis indicate the feasibility of achieving formation flying of three satellites in the orbital plane. Furthermore, the equilibrium analysis leads to useful design criteria in the form of inequality constraints on the system parameters. In the case when three satellites have equal masses, the critical minimum value of spin rate for system steady-spin motion in the orbital plane is found to be 0.58 times the orbital rate. Finally, the effects of various system parameters as well as the tether deployment and retrieval on the system response have been investigated.