A rigid-flexible constraint conversion device and a microgravity rolling state simulation system
A conversion device and rigid constraint technology, which is applied to the simulation device of space navigation conditions, transportation and packaging, space navigation equipment, etc., can solve the problems of difficult capture on orbit, waste of GEO orbital resources, etc.
Active Publication Date: 2022-07-22
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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[0050] It should be noted that the embodiments of the present invention and the features of the embodiments may be combined with each other under the condition of no conflict. In addition, all directions or positional relationships (such as "up", "down", "front", "rear", "left", "right") mentioned in the embodiments of the present application are based on the drawings The positional relationship is only for the purpose of facilitating the understanding of the present application and simplifying the description, rather than implying a specific orientation that the indicated device or element must have, and should not be construed as a limitation on the present application.
[0051] The present invention aims to protect a rigid-flexible constraint conversion device. The rigid-flexible constraint conversion device, as a component of a suspension swivel mechanism, can be rigidly constrained before the suspension target reaches a specified rotational speed, and can be rigidly constr...
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The invention provides a rigid-flexible restraint conversion device and a microgravity roll state simulation system, and relates to the technical field of on-orbit service and maintenance. The rigid-flexible restraint conversion device includes a drive unit, a passive drive unit and a flexible suspension unit; The passive drive unit is directly or indirectly connected with the flexible suspension unit, and the passive drive unit is adapted to be selectively connected with the drive unit; the flexible suspension unit is connected to the drive unit between the passive drive unit and the drive unit. The unit is in a rigid restraint state when connected; the flexible suspension unit is in a flexible restraint state when the passive drive unit is detached from the drive unit, and at this time the flexible suspension unit is suspended by a wire rope. The rigid-flexible constraint conversion device of the present invention is a rigid constraint before the suspension target reaches a specified rotational speed, and after reaching the specified rotational speed, the rigid constraint is disengaged, and only the wire rope bears the gravity, simulating a microgravity state.
Description
technical field [0001] The invention relates to the technical field of on-orbit service and maintenance, in particular to a rigid-flexible constraint conversion device and a microgravity roll state simulation system. Background technique [0002] Geostationary orbit (GEO) is an important earth orbit resource for mankind, and the in-orbit resource is extremely scarce due to the limitation of orbital position. However, with the rapid development of space missions, the GEO belt (GEO±200km) has accumulated many uncontrollable or abandoned satellites, which lead to a serious waste of GEO orbital space resources. For satellites that fail in orbit, in terms of attitude characteristics, due to the energy dissipation effects of the star's solar wings and propellant swaying, they will eventually show a rolling attitude, and it is a big difficulty to capture them on-orbit. In order to solve this difficulty, it is urgent to carry out key technical research related to on-orbit service a...
Claims
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IPC IPC(8): B64G7/00
CPCB64G7/00
Inventor 黄剑斌李志黄龙飞蒙波李伟达张志民庞羽佳韩旭王尹耿安鸿
Owner CHINA ACADEMY OF SPACE TECHNOLOGY