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Optimal collision avoidance approach for dead satellites at ultra-short distance

An ultra-close-range, satellite technology, applied in non-electric variable control, instrument, attitude control and other directions, which can solve the difficulties and challenges of the fully autonomous approximation process, and the complex configuration of failed satellites.

Active Publication Date: 2018-04-13
BEIJING INSTITUTE OF TECHNOLOGYGY +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] The active approach to the failed satellite is an important link in the task of capturing and cleaning the failed satellite. However, because the failed satellite is out of control, its attitude is often in a high-speed rotation state, and most of the failed satellites have complex configurations. Therefore, when considering Under the conditions of target attitude uncertainty and configuration complexity, its fully autonomous approach process is extremely difficult and challenging

Method used

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  • Optimal collision avoidance approach for dead satellites at ultra-short distance
  • Optimal collision avoidance approach for dead satellites at ultra-short distance
  • Optimal collision avoidance approach for dead satellites at ultra-short distance

Examples

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Effect test

Embodiment 1

[0152] A super-short-distance optimal anti-collision approach method for a failed satellite of the present invention takes a certain failed satellite with a pair of solar panels, a single antenna and other accessories whose attitude rolls over as the research object. The initial angular velocity of the target is ω t =[0,0,0.05] T rad / s, configuration parameters are as follows:

[0153] Table 1 Target configuration parameters

[0154]

[0155] Such as figure 1 As shown, the tracking star first arrives at the mooring point X 0 =[-20,10,5] T m, and aim the relative measurement sensor on the tracking star at the target, that is, the invalid satellite. From here the tracker starts the approach control process. During this process, the tracking star maneuvers along the planned safe anti-collision path, and finally arrives at the parking position X at a certain distance from the target docking and capture site within a limited time of 50s. f =[0,-4,0] T m; At the same time...

Embodiment 2

[0261] An ultra-short-distance optimal anti-collision approach method for out-of-service satellites of the present invention takes a out-of-service satellite that is severely damaged in shape, does not have solar panels, and only carries accessories such as antennas and rolls over as the research object. The initial angular velocity of the target is ω t =[0,0,0.05] T rad / s, configuration parameters are as follows:

[0262] Table 1 Target configuration parameters

[0263]

[0264] The tracking star reaches the mooring point X first 0 =[-20,10,5] T m, and aim the relative measurement sensor on the tracking star at the target, that is, the invalid satellite. From here the tracker starts the approach control process. During this process, the tracking star maneuvers along the planned safe anti-collision path, and finally arrives at the parking position X at a certain distance from the target docking and capture site within a limited time of 50s. f =[0,-4,0] T m; At the sa...

Embodiment 3

[0299] An ultra-short-range optimal anti-collision approach method for failed satellites according to the present invention rolls with a certain shape damaged, only one side (+x direction) with a solar panel, and a single antenna and other accessories The failed satellites are the research objects. The initial angular velocity of the target is ω t =[0,0,0.05] T rad / s, configuration parameters are as follows:

[0300] Table 1 Target configuration parameters

[0301]

[0302]

[0303] The tracking star reaches the mooring point X first 0 =[-20,10,5] T m, and aim the relative measurement sensor on the tracking star at the target, that is, the invalid satellite. From here the tracker starts the approach control process. During this process, the tracking star maneuvers along the planned safe anti-collision path, and finally arrives at the parking position X at a certain distance from the target docking and capture site within a limited time of 50s. f =[0,-4,0] T m; At...

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Abstract

The invention relates to a super-close optimized collision-avoidance proximity method for a failure satellite, and belongs to the technical field of spacecraft encounter. An object, namely the failure satellite, is designed into an envelope model in the sphere and ellipsoid combined form to simplify configuration of the object; posture rolling of the object is considered, a relative dynamic model of the object and a tracked star as well as constraints of the path of the tracked star are derived in the dynamic object system; positional nondeterminacy caused by navigation and measurement errors is considered, and the flight forbidden area of the tracked start is further broadened by combining the collision possibility problem; and a safe collision avoidance path is planned on the basis of the Gauss pseudospectral method, and closed-loop feedback control is carried out. According to the invention, spatial limitation in super-close proximity are considered, and requirements for a safe collision free task can be met; and the posture coupling feature of a close proximity spacecraft is emphasized, and whether the distance between the aircrafts satisfies the constraints can be directly determined.

Description

technical field [0001] The invention relates to an ultra-short-distance optimal anti-collision approach method for a spacecraft, in particular to an ultra-short-distance optimal anti-collision approach method for a failed satellite, and belongs to the technical field of spacecraft rendezvous. Background technique [0002] The active approach to the failed satellite is an important link in the operation task of capturing and cleaning the failed satellite. However, because the failed satellite is in a state of out-of-control, its attitude is often in a state of high-speed rotation, and most of the failed satellites have complex configurations. Therefore, when considering Under the conditions of target attitude uncertainty and configuration complexity, its fully autonomous approach process is extremely difficult and challenging. In the short-distance guidance section, the tracker uses relative navigation for autonomous control, and the trajectory design must meet the constraint...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
CPCG05D1/0825
Inventor 张景瑞初晓昱胡权翟光王典军蔡亚星
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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