Suspension spinning mechanism and microgravity rollover state simulation system

A suspension lifting and suspension technology, which is applied in the field of suspension spinning mechanism and microgravity rollover state simulation system, can solve the problems of waste of GEO orbital resources and difficulty in capturing on-orbit, and achieve simple and convenient adjustment method and simple operation Effect

Active Publication Date: 2019-08-13
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

However, with the rapid development of space missions, many uncontrollable or abandoned satellites have accumulated in the GEO belt (GEO ± 200km), and these satellites lead to a serious waste of GEO orbital resources
For in-orbit failed satellites, in terms of attitude characteristics, due to energy dissipation effects such as star solar wings and propellant sloshing, they will eventually show a rolling attitude, and it is a major difficulty to capture them on-orbit

Method used

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  • Suspension spinning mechanism and microgravity rollover state simulation system
  • Suspension spinning mechanism and microgravity rollover state simulation system
  • Suspension spinning mechanism and microgravity rollover state simulation system

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Embodiment Construction

[0054] It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. In addition, all directions or positional relationships (such as "upper", "lower", "front", "back", "left", "right") mentioned in the embodiments of the present application are based on the drawings The positional relationship is only for the convenience of understanding the application and simplifies the description, and does not imply a specific orientation that the referred devices or elements must have, and should not be construed as limiting the application.

[0055] The present invention aims to propose a suspension upswing mechanism to realize the ground simulation of the rolling attitude of the target under the space microgravity state, so as to verify the rationality and technical feasibility of the space task scheme on the basis of the ground test.

[0056] The present invention will be described in ...

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Abstract

The invention provides a suspension spinning mechanism and a microgravity rollover state simulation system, and relates to the technical field of on-orbit service and maintenance. The suspension spinning mechanism includes a spinning device, a rigid-flexible restraint conversion device and an angle and eccentricity adjusting device, wherein the spinning device is suitable for enabling a suspensiontarget to spin around a spin axis; the rigid-flexible restraint conversion device is suitable for the situation that the suspension mechanism and the suspension target are switched between rigid restraint and flexible restraint; and the angle and eccentricity adjusting device is suitable for adjusting the deflection angle and the eccentricity position of the suspension target. According to the suspension spinning mechanism, the spinning of the suspension target around the spin axis can be realized, the swing of the suspension target spin axis can be realized, and the rigid and flexible restraint states of the suspension target can be arbitrarily switched, thus the ground simulation of a possible attitude rollover state of an on-orbit fault satellite is realized.

Description

technical field [0001] The invention relates to the technical field of on-orbit service and maintenance, in particular to a suspension spinning mechanism and a microgravity rolling state simulation system. Background technique [0002] Geostationary orbit (GEO) is an important earth orbit resource for human beings, and the on-orbit resources are limited by the orbital position and are extremely scarce. However, with the rapid development of space missions, many uncontrollable or abandoned satellites have accumulated in the GEO belt (GEO ± 200km), and these satellites lead to a serious waste of GEO orbital resources. For in-orbit failed satellites, in terms of attitude characteristics, due to energy dissipation effects such as star body solar wings and propellant sloshing, they will eventually show a rolling attitude, and it is a major difficulty to capture them on-orbit. In order to solve this difficulty, it is urgent to carry out research on key technologies related to on-...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G7/00
CPCB64G7/00
Inventor 李志黄龙飞黄剑斌于登云孙立宁蒙波李伟达张志民庞羽佳韩旭王尹
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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