Optimal deorbit method for tethered towing of space debris

A technology of space debris and tethers, applied in the direction of attitude control, etc., to achieve the effect of maintaining stable attitude, small error, and reducing fuel consumption

Active Publication Date: 2019-05-24
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0003] The technical problem to be solved by the tethered towing optimal deorbiting method for space debris disclosed in the present invention is: to keep the attitude of the tethered towed system sta

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  • Optimal deorbit method for tethered towing of space debris
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  • Optimal deorbit method for tethered towing of space debris

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Embodiment Construction

[0058] In order to better illustrate the purpose and advantages of the present invention, the specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0059] This embodiment discloses an optimal de-orbiting method for tethered towing of space debris. In order to verify the method, a tethered towing system operating on a circular orbit with a radius of 42164 km is selected as the main research object. Its system parameters are shown in the table below.

[0060] Table 1 Structural parameters of the tethered drag system.

[0061]

[0062] Step 1: The attitude-orbit coupling dynamics model in the orbit plane of the tethered drag system is established by the Lagrangian method.

[0063] The Lagrangian method is shown in formula (17):

[0064]

[0065] Wherein, T is the kinetic energy of the system, and q represents the generalized coordinates of the system. In this embodiment, V g r...

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Abstract

The invention discloses an optical deorbit method for tethered towing of space debris and belongs to the field of spacecraft attitude and orbit dynamics and control. The implementation method includes: establishing a coupling dynamics model of the in-plane orbit of a tethered towing system through a Lagrange method; solving the optimal fuel problem of transfer orbit by adopting an optimization method for orbit transfer and ensuring a wide range of optimal orbit transfer of the tethered towing while system stabilizing the altitude of tethered towing system; at the end of towing, controlling thedebris by swinging and releasing to enable the debris to gain the maximum initial velocity and fly to the farther orbit, and completing the debris removal task while reducing fuel consumption duringthe debris removal process. With the method, wide range optimal orbit transfer of the tethered towing system can be guaranteed, and meanwhile, the attitude of the tethered towing system can be kept stable to remove the space debris stably; besides, the final swing control makes the debris fly further into the orbit, and fuel consumption during the debris removal process is reduced.

Description

technical field [0001] The invention relates to an optimal de-orbiting method for tether dragging of space debris, in particular to an optimal design method for a transfer orbit of a spacecraft considering attitude motion, and belongs to the field of spacecraft attitude and orbit dynamics and control. Background technique [0002] In the deorbiting research of space debris dragged by tethered satellites, it is the research focus of the debris removal mission to rationally design the orbit control strategy so that the fuel consumption can be kept as low as possible while the debris is removed smoothly. Literature (Wang, B.H., Meng, Z.J., Huang, P.F. "Attitude Control of Towed Space Debris Using Only Tether."Acta Astronautica 138(2007):1-16) aimed at the debris deorbiting process, only studied the tether's impact on the tugboat. Forced tugboat orbital motion model and Hohmann transfer to remove space debris. The literature (Linskens, H.T.K., and Mooij, E. "Tether Dynamics Ana...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 杨科莹张景瑞张尧王典军经姚翔陈士明
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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