Orbital dynamics of gravity tractor spacecraft employing artificial halo orbit
Orbital dynamics of gravity tractor spacecraft employing artificial halo orbit
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DOI：
10.1016/j.actaastro.2022.06.009
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发表时间：
2022-06
影响因子：
3.5
通讯作者：
Kohei Yamaguchi;Ji Hyun Park;Xinbo Gu;T. Inamori
中科院分区：
文献类型：
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作者：
Kohei Yamaguchi;Ji Hyun Park;Xinbo Gu;T. Inamori
在本文中，运动方程的建模航天器附近的威胁地球的小行星的建议和研究偏转小行星使用重力牵引器，有效地拖曳小行星的相互引力吸引。航天器的运动由两个物体之间的分离距离、表示航天器-小行星系统姿态的两个欧拉角及其导数表示;假设航天器和小行星由可变长度的重力系绳连接。利用所提出的方程研究了人造晕轨道（AHO）中航天器的运动。这些方程适用于研究，因为AHO中的航天器以恒定的角速度和距离在圆形轨道上运动。结果表明，AHO是不稳定的，将需要一个线性二次型调节器来控制航天器。数值模拟结果表明，AHO-AHO转移可以实现通过采用控制律，线性化所提出的方程。可实现的偏转距离产生的1000天的牵引使命计算虚构的地球撞击器，结果表明，所提出的系统是可行的进行长期模拟。
In this paper, the equations of motion for modeling a spacecraft near an earth-threatening asteroid are proposed and studied for deflecting the asteroid using a gravity tractor that effectively tows the asteroid with mutual gravity attraction. The motion of the spacecraft is expressed by separation distance between the two objects, two Eulerian angles expressing the attitude of the spacecraft–asteroid system, and their derivatives; it is assumed that the spacecraft and asteroid are connected with a variable-length gravity tether. The motion of the spacecraft in an artificial halo orbit (AHO) is investigated using the proposed equations. These equations are suitable for the investigation because the spacecraft in the AHO moves in a circular orbit at a constant angular velocity and distance from the asteroid. The results indicate that the AHO is unstable, and a linear quadratic regulator will be required to control the spacecraft. Numerical simulation results suggest that the AHO–AHO transfer can be realized by employing a control law that linearizes the proposed equations. The achievable deflection distance yielded by 1000 days of a towing mission is calculated for fictional Earth impactors; the results indicate that the proposed system is feasible for conducting long-term simulations.