Solar cell panel deployment mechanism, system and method

A technology of solar cell and deployment mechanism, applied in the field of aerospace satellites, can solve the problems of complex deployment mechanism structure, and achieve the effects of being less prone to deployment failure, reducing volume, and reducing weight

Pending Publication Date: 2018-05-08
星际漫步(北京)航天科技有限公司
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  • Claims
  • Application Information

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Problems solved by technology

[0004] Based on this, it is necessary to provide a simple structure and reliable solar panel deployment mechanism for the complex structu

Method used

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  • Solar cell panel deployment mechanism, system and method
  • Solar cell panel deployment mechanism, system and method
  • Solar cell panel deployment mechanism, system and method

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[0043] In order to make the objectives, technical solutions, and advantages of the present invention clearer, the following examples are used in conjunction with the accompanying drawings to further describe the solar panel deployment mechanism, deployment system and deployment method of the present invention in detail. It should be understood that the specific embodiments described here are only used to explain the present invention, but not to limit the present invention.

[0044] It should be noted that when an element is referred to as being "fixed to" another element, it can be directly on the other element or a central element may also exist. When an element is considered to be "connected" to another element, it can be directly connected to the other element or an intermediate element may be present at the same time. In contrast, when an element is referred to as being "directly on" another element, there are no intervening elements. The terms "vertical", "horizontal", "le...

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Abstract

The invention relates to the technical field of space satellites, in particular to a solar cell panel deployment mechanism. The solar cell panel deployment mechanism comprises a first supporting frame, a second supporting frame, a retractable assembly and an elastic piece. The first supporting frame and the second supporting frame are arranged in a spaced mode and can move relatively. The retractable assembly is used for applying drive force to the second supporting frame, so that the second supporting frame moves in the direction close to the first supporting frame. The elastic piece is arranged between the first supporting frame and the second supporting frame, and when the retractable assembly releases the drive force applied to the second supporting frame, the second supporting frame moves in the direction away from the first supporting frame under the elastic effect of the elastic piece. The solar cell panel deployment mechanism is deployed through relative motion of the two supporting frames after a satellite is launched in an orbit, the structure is simple and reliable, and a deployment failure phenomenon is unlikely to happen. Due to the fact that the deployment process mainly depends on the elastic force effect of the elastic piece, an extra deployment drive structure does not need to be arranged, and the weight is effectively reduced.

Description

technical field [0001] The invention relates to the technical field of aerospace satellites, in particular to a solar cell sail panel deployment mechanism, deployment system and deployment method. Background technique [0002] For satellites, solar panels are currently the main power supply system of satellites and one of the core components of the entire satellite system, which directly affects the performance of the entire satellite. However, it is difficult for general satellite and spacecraft systems to carry more solar cells due to the volume and weight of solar cell sail panels. In addition, in order to solve the problem of the volume occupied by the solar battery sail, an expandable solar battery sail mechanism has emerged as the times require. [0003] However, the traditional solar panel deployment structure is mainly unfolded by rigid folding. It is necessary to set up a hinge structure between two adjacent solar panel panels, and it is necessary to design and dri...

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Application Information

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IPC IPC(8): B64G1/44H02S30/20
CPCH02S30/20B64G1/44Y02E10/50
Inventor 吴前进
Owner 星际漫步(北京)航天科技有限公司
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