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Method for establishing tethered captured satellite dynamic models through adding flexibility and fuel sloshing

A dynamic model, a technology of fuel sloshing, applied in the tether winding model, the attitude dynamics model of the tethered capture satellite considering flexibility and liquid sloshing, the establishment of the dynamic model of the tethered capture satellite, the dynamic model of the capture robot It can solve problems such as satellite and tether entanglement, satellite attitude interference, etc.

Inactive Publication Date: 2017-08-11
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

The captured non-cooperative space targets may have flexible parts (such as solar panels) and residual fuel, and their vibration and shaking will cause great disturbance to the satellite attitude
If not controlled properly, this can cause the satellite to become entangled with the tether

Method used

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  • Method for establishing tethered captured satellite dynamic models through adding flexibility and fuel sloshing
  • Method for establishing tethered captured satellite dynamic models through adding flexibility and fuel sloshing
  • Method for establishing tethered captured satellite dynamic models through adding flexibility and fuel sloshing

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Embodiment Construction

[0086] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0087] First consider the following assumptions:

[0088] Assumption 1: The satellite body is regarded as a cube;

[0089] Assumption 2: There is no relative motion between the capture robot and the satellite;

[0090] Assumption 3: The left and right solar panels are symmetrically installed on the central axis of the satellite main body;

[0091] Hypothesis 4: The solar panel only oscillates with a small amplitude, and the torsion of the panel is ignored;

[0092] Assumption 5: The fuel liquid storage tank is spherical, and the center of the sphere is located on the satellite body axis;

[0093] Hypothesis 6: The satellite entangles with the tether only once.

[0094] Based on the above assumptions, the present invention proposes a tether capture satellite dynamics model, which integrates an attitude model considering flexibility and shaking, a manipulator m...

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Abstract

The invention relates to a method for establishing tethered captured satellite dynamic models through adding flexibility and fuel sloshing. The method comprises the following steps of: firstly determining parameters and a degree of freedom of a captured satellite, and establishing a sailboard flexibility and liquid sloshing-considered satellite attitude dynamic model by utilizing the Newton's second law and the Lagrange principle; and determining parameters and a degree of freedom of a mechanical arm, and establishing a tether winding model. The method has the beneficial effects of embodying the influences, on the attitude, of sailboard flexible vibration and residual fuel sloshing of non-cooperative targets, and embodying the change of tether length in the winding process so as to analyze the influences, on the tether tension, of the winding; and by adoption of a strategy of carrying out attitude takeover and control through moving a tether connection point, dynamic response of the mechanical arm and required control force can be provided.

Description

technical field [0001] The invention belongs to the field of tethered spacecraft dynamics modeling, and relates to a method for establishing a dynamics model of a tethered capture satellite with flexibility and fuel sloshing, in particular to attitude dynamics of a tethered capture satellite considering flexibility and liquid sloshing model, capture robot dynamics model and tether winding model. Background technique [0002] The use of tethered robots to capture non-cooperative targets and tow them to a graveyard orbit is an emerging technology for active space debris removal. The captured non-cooperative space targets may have flexible parts (such as solar panels) and residual fuel, and their vibration and shaking will cause great disturbance to the satellite attitude. If not controlled properly, this can cause the satellite to become entangled with the tether. Therefore, it is necessary to establish a satellite attitude dynamics model and a tether winding model consideri...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 孟中杰王秉亨邓远旺黄攀峰刘正雄张夷斋张帆
Owner NORTHWESTERN POLYTECHNICAL UNIV
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