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Space debris tethered towed deorbital target attitude nutation suppression control method and system

A technology of space debris and target attitude, applied in the direction of control/regulation system, non-electric variable control, mechanical pressure/force control, etc., to achieve the effect of strong engineering realization

Pending Publication Date: 2020-08-18
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The existing technologies all assume that the target can provide sufficient motion state information, such as target attitude angular rate, capture state, etc.
For non-cooperative targets such as space debris, the existing technology can only measure their attitude information, based on the limitations of current measurement technology

Method used

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  • Space debris tethered towed deorbital target attitude nutation suppression control method and system
  • Space debris tethered towed deorbital target attitude nutation suppression control method and system
  • Space debris tethered towed deorbital target attitude nutation suppression control method and system

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Embodiment Construction

[0030] Such as Figure 1~4 , a space debris tether dragging off-orbit target attitude nutation suppression control method, comprising the following steps:

[0031] Establish the dynamics model of tethered dragging system through the Euler equation of rigid body rotational motion; Described tethered dragging system comprises tugboat spacecraft, space debris and tether; Described tether comprises main rope and sub-rope, and one end of the main rope Connect the tugboat spacecraft, and the other end is connected to the sub-rope through the knot point; the sub-rope has several pieces, which are respectively connected to the corresponding parts of the space debris;

[0032] According to the dynamic model of the tethered dragging system, and based on the dissipation of mechanical energy, a switch tension control law is obtained;

[0033] The position of the rope node is observed, and the observed position of the rope node is combined with the switching tension control law to control...

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Abstract

The invention discloses a space debris tethered dragging deorbiting target attitude nutation suppression control method and system, and belongs to the field of spacecraft attitude dynamics and control. The implementation method comprises the following steps: after assuming that a fragment target and a rope net assembly adopt a rigid body, establishing a kinetic model of a tethered dragging systemby adopting an Euler equation of rigid body rotation motion; analyzing and designing a constant tension switching control method based on dissipation of mechanical energy; indirectly reflecting the motion of the rope node by measuring the distance between the rope node and the connecting line of the two satellites or observing the included angle between the tether direction and the connecting lineof the two satellites, and providing a basis for selection of switching conditions of a switching tension control method. The method is used for quickly and effectively inhibiting the posture nutation of the debris target in the dragging deorbiting process after the space debris is subjected to flying net capture, it is guaranteed that the risks of tether winding and the like do not occur in thedragging process, and a technical support is provided for safely and efficiently completing the space debris active clearing task.

Description

technical field [0001] The invention relates to a space debris tether dragging off-orbit target attitude nutation control method and system, and belongs to the field of spacecraft attitude dynamics and control. Background technique [0002] Space debris covers the upper stages of rockets, failed satellites, discarded objects from space missions, and derivatives of spacecraft disintegration or collisions with each other. For example, the collision between the US Iridium satellite and the Russian satellite in 2009 resulted in an increase of nearly 3,000 space debris over 10cm in size, which greatly increased the safety risk of spacecraft in orbit. [0003] In order to meet the needs of non-cooperative target acquisition tasks such as recovery of faulty satellites and space debris removal in the future, research institutions at home and abroad have proposed a flexible acquisition mode using a flexible flying net as a means of acquisition, which has the advantages of light weigh...

Claims

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Application Information

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IPC IPC(8): G05D15/00B64G4/00
CPCG05D15/00B64G4/00Y02T90/00
Inventor 刘付成姜泽华卢山刘禹徐晨王焕杰吕若宁
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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