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A Tethered Drag Stabilization Control Method for Space Debris

A stability control method and space debris technology, applied in the field of spacecraft relative motion and flexible tether control, and tether dragging stability control, can solve problems such as system oscillation and instability

Active Publication Date: 2020-02-04
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem of system oscillation or even instability caused by debris rotation during the process of dragging space debris by a single tether, and to provide a tether drag stability control method for space debris

Method used

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  • A Tethered Drag Stabilization Control Method for Space Debris
  • A Tethered Drag Stabilization Control Method for Space Debris
  • A Tethered Drag Stabilization Control Method for Space Debris

Examples

Experimental program
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Effect test

Embodiment 1

[0142] Firstly, the dynamic simulation is carried out for the tethered trailer system in the uncontrolled state. The initial relative motion parameters of the system are The original length of the tether was 99.126m.

[0143] Using the data of Example 1 in Table 1, the dynamics simulation of the tethered trailer system under uncontrolled conditions is carried out. Figure 4 The open-loop relative motion of the tethered trailer system is shown. The curves in the figure show that the trailer and the debris present a continuous tumbling motion in one direction under the influence of the initial angular velocity of the debris. After about 30 seconds, the system entered a chaotic state, the angular velocity of the debris and the trailer increased sharply, and the swing range of the system also increased significantly. This state of motion is likely to cause breakage of the tether and loss of control of the system, and has a destructive effect on the normal operation of the tra...

Embodiment 2

[0148] In the second embodiment, according to the size of the debris, the offset of the connection point of the tether on the debris is limited within the range of [-2, 2] meters in both the y-axis and z-axis directions. Figure 5 It shows the closed-loop relative motion of the system in the second embodiment. As shown in the figure, the attitude angle of the trailer is stably maintained near zero under the action of the attitude control torque generated by itself, and the rotation of the debris in the pitch and yaw directions is effectively slowed down under the action of the offset control strategy. and eventually converges to zero. At the same time, the center-of-mass distance l of the trailer debris gradually converges to the target value after 400 seconds, and the system exhibits a slight regular swing. Overall, through the designed control strategy, the attitude oscillation of the trailer and debris is effectively suppressed, and the overall swing of the system is also ...

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Abstract

The invention, which belongs to the attitude dynamics and control field of the spacecraft, relates to a stable tether dragging control method for space debris, especially to the relative motion and flexible tether control method of the spacecraft. According to the invention, appropriate generalized coordinates are selected and an accurate three-dimensional orbital attitude coupling dynamics modelof a tether trailer system is established by using a lagrange method, wherein the debris and the trailer are viewed as rigid bodies and the tether is considered as a mass-free spring damping. A methodfor estimating the de-tumbling capability for specific debris by the tether before de-tumbling on the debris by the tether is put forward. For the initially rotating space debris, an offset control strategy using an original tether length and a connection point offset value as control inputs is designed to realize debris de-tumbling and stabilizing the jittering of the system, so that the reliable guarantee is provided for tether dragging elimination of the space debris.

Description

technical field [0001] The invention relates to a tethered drag stability control method for space debris, in particular to a method for controlling relative motion of spacecraft and flexible tethering, and belongs to the field of spacecraft attitude dynamics and control. Background technique [0002] In the rope-trailer system, an effective strategy for derotation of debris with a single rope is the offset control method. Literature (Kumar, K.D., and Tan, B. "Nonlinear optimal control of tethered satellite systems using tethered offset in the presence of tether failure." ActaAstronautica 66.9(2010):1434-1448) uses two A control variable is used, and the nonlinear inverse optimal control method is used to suppress the oscillation of the system. In this method, the tether connection point is regarded as a variable, and the control variables are separated by obtaining the third-order derivative of the dynamic equation, so as to design the control law and complete the racemiza...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
Inventor 杨科莹张景瑞祁瑞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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