Nutation suppression method of spacecraft used for on-orbit delivery by using geomagnetic energy storage in low-orbit

A spacecraft and low-orbit technology, which is applied in the direction of aerospace vehicles, aerospace vehicle docking devices, and aerospace vehicle guidance devices, can solve the problem of spacecraft system danger, non-passing spacecraft system, spacecraft system quality and center of mass Uncertainty changes and other issues, to achieve the effect of suppressing nutation problems

Active Publication Date: 2020-02-21
INST OF MECHANICS - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] When the spacecraft system uses the geomagnetic energy storage method for on-orbit delivery of targets in low-orbit space, there will be a major problem: the rotation axis of the delivery mechanism of the spacecraft system may not pass through the center of mass of the spacecraft system, which will Causes the rotational nutation phenomenon of the spacecraft system. In the environment without air damping in low orbit space, the nutation phenomenon is very dangerous for the spacecraft system
[0003] There are several factors that affect the fact that the rotation ax...

Method used

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  • Nutation suppression method of spacecraft used for on-orbit delivery by using geomagnetic energy storage in low-orbit
  • Nutation suppression method of spacecraft used for on-orbit delivery by using geomagnetic energy storage in low-orbit
  • Nutation suppression method of spacecraft used for on-orbit delivery by using geomagnetic energy storage in low-orbit

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Embodiment 1

[0056] refer to figure 1 , 2 , which is a spacecraft nutation suppression method for on-orbit delivery of low-orbit geomagnetic energy storage disclosed by the present invention, comprising the following control steps:

[0057] S1, the spacecraft system is divided into a spacecraft main body 1 and a spacecraft main body 2 fixedly connected by the main connecting shaft 3. The main connecting shaft 3 is rotated and provided with a delivery connecting rod 7 perpendicular to it. The rod 7 is slidably connected with two mass blocks 72 along the length direction, and the center of mass of the spacecraft system is adjusted through the main connecting axis 3; the specific adjustment steps are as follows:

[0058] (1) before the spacecraft system grabs the space target or de-orbit debris to be delivered, slide the two mass blocks 72 on the delivery link 7 back to the main connecting shaft 3;

[0059] (2) The linear telescopic device connected to the main connecting shaft 3 performs t...

Embodiment 2

[0074] see figure 1 , 3 , which is a spacecraft nutation suppression method for on-orbit delivery of low-orbit geomagnetic energy storage disclosed by the present invention, comprising the following control steps:

[0075] S1, the spacecraft system is divided into a spacecraft main body 1 and a spacecraft main body 2, which are fixedly connected by the main connecting shaft 3. The main connecting shaft 3 is rotated and provided with two delivery connecting rods 7 perpendicular to it. The connecting rod 7 is slidingly connected with two mass blocks 72 along the length direction, and the center of mass of the spacecraft system is adjusted through the main connecting axis 3; the specific adjustment steps are as follows:

[0076] (1) before the spacecraft system grabs the space target or de-orbit debris to be delivered, slide the two mass blocks 72 on the delivery link 7 back to the main connecting shaft 3;

[0077] (2) The linear telescopic device connected to the main connecti...

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Abstract

The invention relates to the field of geomagnetic energy storage on-orbit delivery, and discloses a nutation suppression method of a spacecraft used for on-orbit delivery by using geomagnetic energy storage in low-orbit. The method comprises the following steps that S1, a delivery connecting rod is slidably connected with two mass blocks along the length direction, and the center of mass of a spacecraft system is adjusted and passes through a main connection shaft; S2, after a space target or an off-orbit fragment is grabbed by the spacecraft system and the space target or the off-orbit fragment is kept at the corresponding position of the delivery connecting rod, the center of mass of the delivery connecting rod of the to-be-delivered space target or the off-orbit fragment is measured andcalibrated and an inertia main shaft of the delivery connecting rod of the to-be-delivered space target or the off-orbit fragment is adjusted; S3, energy storage delivery is carried out; S4, the center of mass and the moment of inertia of the delivery connecting rod which completes the delivery of the space target or the off-orbit fragment are adjusted correspondingly; S5, energy dissipation andunloading are carried out; and S6, the next space target or the off-orbit fragment is prepared to be grabbed by the spacecraft system to enter the next delivery work cycle. According to the nutation suppression method, the capability of on-orbit freely nutating of the spacecraft system is effectively inhibited before and after several states in the preparation processes of geomagnetic energy storage rotation delivery, energy dissipation and unloading and once-more delivery are suddenly changed.

Description

technical field [0001] The invention relates to the technical field of low-orbit geomagnetic energy storage on-orbit delivery technology, in particular to a spacecraft nutation suppression method for low-orbit geomagnetic energy storage on-orbit delivery. Background technique [0002] When the spacecraft system uses the geomagnetic energy storage method for on-orbit delivery of targets in low-orbit space, there will be a major problem: the rotation axis of the delivery mechanism of the spacecraft system may not pass through the center of mass of the spacecraft system, which will This causes the rotational nutation phenomenon of the spacecraft system. In the environment without air damping in low orbit space, the nutation phenomenon is very dangerous for the spacecraft system. [0003] There are several factors that affect the fact that the rotation axis of the spacecraft system does not pass through its center of mass: 1) The state of the spacecraft system itself changes, su...

Claims

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Application Information

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IPC IPC(8): B64G1/22B64G1/24B64G1/32
CPCB64G1/22B64G1/24B64G1/32B64G1/245B64G1/38B64G1/646B64G1/244B64G1/242B64G1/64B64G1/66
Inventor 李文皓张珩冯冠华张琛杨磊吕林立
Owner INST OF MECHANICS - CHINESE ACAD OF SCI
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