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Device for unbiased flight along conservative force action track

A technology of conservative force and action, applied in the field of aerospace, can solve the problem of unable to maintain centimeter-level and higher-precision autonomous navigation, and achieve the effect of improving navigation accuracy and improving technical effects

Active Publication Date: 2019-05-28
INST OF MICROELECTRONICS CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The embodiment of the present application provides a device for unbiased flight along the conservative force trajectory, which solves the technical problem in the prior art that it cannot maintain centimeter-level and higher-precision autonomous navigation, and achieves the ability to eliminate the impact of non-conservative forces , construct a high-precision flight orbit for the star that is only perturbed by the conservative force, make the orbit determination accuracy of the star as close as possible to the accuracy limit of the conservative force model, and maximize the navigation accuracy of the satellite

Method used

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  • Device for unbiased flight along conservative force action track
  • Device for unbiased flight along conservative force action track
  • Device for unbiased flight along conservative force action track

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Embodiment 1

[0039] Fig. 1(a) is a schematic structural diagram of a device that flies along a conservative force trajectory without deviation and enters the orbit provided by the embodiment of the present application. As shown in Figure 1, the structure includes:

[0040] Satellite body 8;

[0041] Specifically, the satellite body 8 described in the embodiment of the present application is an artificial satellite, and an artificial satellite can generally also be called a satellite. Artificial satellites are devices built by humans and launched into space by space vehicles such as rockets and space shuttles, and orbit the earth or other planets like natural satellites.

[0042] Further, the attitude determination and control system 9 , the attitude determination and control system 9 is arranged inside the satellite body 8 to control the operating attitude of the satellite body 8 .

[0043] A pure inertial system module (not shown), the pure inertial system module is arranged inside the ...

Embodiment 2

[0065] In order to explain the technical solution of the present application more clearly, the embodiment of the present application provides an explanation of the working principle of a device that flies along the conservative force trajectory without deviation.

[0066] Before the satellite enters the predetermined orbit, the levitation mass 1 is in a state fixed by the lock release mechanism 4, when the satellite enters the predetermined orbit, the levitation mass 1 is released by the lock release mechanism 4, and operates only by the lock release mechanism 4. Under the action of conservative force, the satellite body 8 slows down under the action of atmospheric resistance, so that the suspended mass 1 is suspended inside the shell 2 .

[0067] Figure 4 It is the control strategy diagram of the microthruster of the device flying on the unbiased trajectory. When the satellite body 8 is running in a predetermined orbit, when the suspended mass 1 released by the locking rele...

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Abstract

The embodiment of the invention provides a device for unbiased flight along a conservative force action track and relates to the technical field of spaceflight. The device comprises a satellite body,a pure inertia system module arranged inside the satellite body and providing an operating environment only subjected to a conservative force action for a suspended mass block, and a micro-thruster control system rigidly and fixedly connected with the satellite body, receiving the relative displacement information sent by a differential optical shadow sensor array, and adjusting the satellite bodyto track the flying of the suspended mass block according to the relative displacement information. The technical problem in the prior art is solved that centimeter-level and higher-precision autonomous navigation cannot be maintained, and the technical effects of enabling the orbit determination precision of a star to approach the precision limit of a conservation force model as much as possibleand improving the navigation precision of a satellite to the maximum extent are achieved.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a device for unbiased flight along a trajectory of conservative force action. Background technique [0002] With the development of science and technology, people's exploration of the universe is getting deeper and deeper, and the level of exploration is gradually improving. In the future, there will be an unprecedented urgent demand for high-precision space nodes and long-term autonomous navigation, and the requirements for centimeter-level or even higher precision for autonomous navigation of space nodes. [0003] As we all know, at present, the construction and maintenance of only a single spatial reference node needs to be at the expense of national or even global joint measurement and control resources. [0004] However, in the process of realizing the technical solution of the invention in the embodiment of the present application, the inventor of the present applicatio...

Claims

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Application Information

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IPC IPC(8): G05D1/10G01C21/24G01C21/00
Inventor 蔡建甘庆波贾少霞金婷杨景华刘芳芳
Owner INST OF MICROELECTRONICS CHINESE ACAD OF SCI
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