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Space tumbling target non-contact racemization method based on double-satellite electromagnetic formation satellite

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Pending Publication Date: 2021-11-05
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The invention provides a non-contact derotation method for space tumbling targets based on double-star electromagnetic formation satellites, in order to solve the problem that the complex tumbling motion of non-cooperative targets is difficult to capture

Method used

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  • Space tumbling target non-contact racemization method based on double-satellite electromagnetic formation satellite
  • Space tumbling target non-contact racemization method based on double-satellite electromagnetic formation satellite
  • Space tumbling target non-contact racemization method based on double-satellite electromagnetic formation satellite

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Experimental program
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Effect test

Embodiment 1

[0043] like figure 1A schematic diagram of serving satellites A and B and a space derotation target is shown. The service satellite platform bodies 1 and 7 are equipped with a superconducting coil system 2, a solar panel 3, a relative position and attitude sensor 4, and a mechanical arm grabbing mechanism 5. The body of the space robot is also provided with several propellers 8 .

[0044] A kind of non-contact derotation method of space tumbling target based on double star electromagnetic formation satellite, described non-contact derotation method comprises the following steps:

[0045] Step 1: The two service spacecraft arrive at both sides of the target, and are in the same orbit as the target, reaching a safe distance range, and the attitude control systems of the two service satellites ensure that the coils are always pointing to the target;

[0046] Step 2: Arrive at the position within the safe range of step 1. Both service satellites start the on-board superconductin...

Embodiment 2

[0075] Suppose the target is radius 2m, thickness 3mm, conductivity 3.7x10 7 S / m, inertia matrix I t =diag[8000,8000,8000]kg.m 2 , located in a circular orbit 800km above the ground. The radius of the superconducting coil carried by the formation service satellite is 1m, the line current is 90A, and the mass of the satellite is 800kg. In order to simplify the dynamic analysis, it is assumed that the service satellite reaches a distance of 8m from the target, and the coil current changes from the same direction to the opposite direction. When reaching the farthest point (11m from the target), the propeller works so that the linear velocity of the service satellite relative to the target is zero.

[0076] Figure 4 Assuming that the initial angular velocity of the target is perpendicular to the orbital plane, the simulation results prove that the method can effectively eliminate the angular velocity component of the target perpendicular to the orbital plane.

[0077] Figu...

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Abstract

The invention discloses a space tumbling target non-contact racemization method based on a double-satellite electromagnetic formation satellite. According to the method, two small satellites carrying high-temperature superconducting coils are utilized to form an electromagnetic formation to reach the two sides of a non-cooperative target, and a space controllable magnetic field for enveloping the target is built; and the two service satellites continuously approach to and move away from the target by controlling the magnitude and direction of the current of the satellite-borne coils and the attitude of the formation satellites. The non-contact electromagnetic effect of the target and the coil system is achieved through eddy current torque induced by movement of a conductor on the target relative to a coil magnetic field, the angular momentum of the target is absorbed, and the angular momentum of the service satellite system is consumed at the farthest point through a propellant. The invention aims to solve the problem that capturing is difficult to implement due to complex rolling motion of the non-cooperative target.

Description

technical field [0001] The invention belongs to the technical field of control; in particular, it relates to a non-contact derotation method for space rolling targets based on double-star electromagnetic formation satellites. Background technique [0002] With the acceleration of human exploration and application of space technology, more and more spacecraft have been sent into space. The hazards of space debris and the scarcity of orbital resources have become increasingly prominent. On the one hand, they occupy scarce orbital resources and have potential collision risks, which seriously affect the safety of spacecraft in orbit, pose a threat to the safety of astronauts, and increase the launch cost of spacecraft. On the other hand, the clearance of space debris and the rescue of invalid satellites also contain huge commercial or military value. If it is possible to perform maintenance operations on these space non-cooperative targets, perform module replacement, on-orbit...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCG05D1/0833
Inventor 岳洪浩杨飞余运锋陆一凡赵海红赵勇
Owner HARBIN INST OF TECH
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