Rapid rolling target de-rotation cell sail facing in-orbit service and operation method thereof

A working method and cell technology, which can be applied to tools, space navigation equipment, transportation and packaging, etc., can solve the problems of secondary damage to the uncontrolled satellite body, low racemization efficiency, low racemization cost, etc., so as to shorten the racemization time, Effects of reduced complexity and reduced power requirements

Active Publication Date: 2015-12-30
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to solve the possible secondary damage caused by the current non-contact derotation scheme to the out-of-control satellite body, as well as the problems of complex structure, low derotation efficiency and low cost of derotation, and then provide on-orbit service The rapid tumbling target racemic cell sail and its working method

Method used

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  • Rapid rolling target de-rotation cell sail facing in-orbit service and operation method thereof
  • Rapid rolling target de-rotation cell sail facing in-orbit service and operation method thereof
  • Rapid rolling target de-rotation cell sail facing in-orbit service and operation method thereof

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specific Embodiment approach 1

[0028] Specific implementation mode 1: Combine 1 to Figure 5 In this embodiment, the fast-rolling target for on-orbit services and its working method are used to derotate the cell sail and its working method. The race is completed by the parent star and the cell sail. The parent star is the carrier of the laser and is the energy source of the derotation torque. At the same time, as the sending end of the control command, it is the control center of the cell sail, and the cell sail, as an angular momentum racer attached to an out-of-control satellite, is a specific implementing agency for the race.

specific Embodiment approach 2

[0029] Specific implementation manner two: combination Figure 1 to Figure 5 To illustrate this embodiment, the working method of this embodiment includes the following steps:

[0030] Step 1. The cell sail is separated from the maternal service satellite;

[0031] Step 2: Under the control of the laser propulsion launched by the parent star, the cell sail approaches the uncontrolled rolling target;

[0032] Step 3. The cell sail is in contact with the surface of the out of control satellite, and the bionic gecko claws on the cell sail are used to produce adhesion to the surface of the out of control satellite;

[0033] Step 4: Perform angular momentum racemization on the target based on the cell sail;

[0034] Step 5. The cell sail measures the angular velocity of the out-of-control satellite through the gyroscope. When the angular velocity is less than the preset 10 -3 At the threshold of rad / s, the cell sail sends instructions to the parent star through the communication system, and ...

specific Embodiment approach 3

[0036] Specific implementation mode three: combination Figure 1 to Figure 5 To explain this embodiment, the laser propulsion control is used in step 2 of this embodiment. The specific principle is: the cell sail surface adopts photonic graphene material. Based on the principle of photonic graphene emitting electrons under light irradiation, the parent star passes through Launch the laser and aim at the graphene light sail structure on the cell sail. The photonic graphene material absorbs energy under the laser irradiation and ejects electrons outward, generating a counteracting thrust. The amount of thrust is changed by changing the intensity of the laser or changing the light sail. The area is controlled, and the direction of thrust is controlled by changing the position of the light sail surface. The other composition and connection relationship are the same as in the second embodiment.

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Abstract

The invention relates to a rapid rolling target de-rotation cell sail facing in-orbit service and an operation method thereof, relates to an operation method of the de-rotation cell sail, and is used for solving the problems of the existing noncontact de-rotation scheme that an out-of-control satellite body can be secondarily damaged, the structure is complicated, the de-rotation efficiency is low and the de-rotation cost is low. In the invention, a de-rotation satellite consists of a mother satellite and a cell sail, wherein the cell sail is used as an angular momentum de-rotation device which is attached to the out-of-control satellite and is a specific execution mechanism for executing the de-rotation task, the mother satellite is an energy source of a de-rotation torque and is also a control center, before the de-rotation, the cell sail is hidden in the mother satellite, and when in work, the cell sail is cooperated with the mother satellite to complete the de-rotation of the out-of-control satellite by virtue of a series of process such as approaching, adsorption, de-rotation, recovering and the like. The rapid rolling target de-rotation cell sail is suitable for eliminating the rotation of a rapid rolling target in the space.

Description

Technical field [0001] The invention relates to a fast-rolling target derotation cell sail for on-orbit service and a working method thereof, and belongs to the technical field of spacecraft on-orbit service. Background technique [0002] Repairing and de-orbiting out-of-control spacecraft is one of the core tasks of on-orbit services. Most out-of-control targets will rotate at a high speed. If they are directly operated, it will cause difficulties in orbiting operations such as the service spacecraft’s grasping or docking, or cause impact damage to the grasping or docking mechanism, or even cause damage to the service spacecraft. Instability. Therefore, it is necessary to eliminate the angular momentum of rapid rollover before repairing or de-orbiting an out-of-control spacecraft. In 2006, a certain type of resource satellite in my country quickly rolled and then malfunctioned due to the gyro stalled. The first rescue work was to eliminate the rotation of the entire satellite ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G4/00
Inventor 张世杰罗振杰聂涛顾远凌江雨南范一迪
Owner HARBIN INST OF TECH
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