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A method for deploying a space-flexible solar cell array

A solar cell array, flexible technology, applied in photovoltaic power generation, electrical components, photovoltaic modules, etc., can solve the problems of unstable deployment process, unstable driving process, complex mechanical structure, etc., to achieve stable deployment process, flexible design, mechanical simple structure

Active Publication Date: 2017-04-12
苏州智新复合材料有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to solve the problems existing in the existing inflatable or mechanical space deployable structures, such as complicated mechanical structure, complex driving mechanism, unstable deployment process, unstable driving process, and easy damage to the structure vibration, etc., and provides a The deployment method of space flexible solar cell array

Method used

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  • A method for deploying a space-flexible solar cell array
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  • A method for deploying a space-flexible solar cell array

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specific Embodiment approach 1

[0024] Specific implementation mode one: combine figure 1 , 2 , 3, 4, 5, 6, 7, and 8 illustrate this embodiment, a method for deploying a spatially flexible solar cell array in this embodiment, which is specifically prepared according to the following steps:

[0025] Step 1, according to the shape and size of the solar cell array, synthesize a shape memory polymer film of similar shape and size, and cover the electrothermal film on the shape memory polymer film to obtain a shape memory polymer film covered with an electrothermal film;

[0026] The shape memory polymer is one or more of epoxy-based thermoplastic shape-memory polymers, epoxy-based thermosetting shape-memory polymers, polyimide shape-memory polymers, and cyanate-based shape-memory polymers. kind;

[0027] Step 2. Fixing the solar cell array on the shape memory polymer film covered with the electric heating film to obtain a space flexible solar cell array based on the shape memory polymer with active unfolding f...

specific Embodiment approach 2

[0030] Embodiment 2: This embodiment differs from Embodiment 1 in that: the shape memory polymer material contains reinforcing materials.

[0031] Other steps and parameters are the same as those in Embodiment 1.

specific Embodiment approach 3

[0032] Embodiment 3: The difference between this embodiment and Embodiment 1 or 2 is that the shape-memory polymer film has a mesh structure or a solid surface structure (the film surface has no holes or gaps, and is an integral planar structure) .

[0033] Other steps and parameters are the same as those in Embodiment 1 or Embodiment 2.

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Abstract

The invention relates to an unfolding method of a space flexible solar battery array, and aims to solve problems of complex mechanical structure, complex driving mechanism, unstable unfolding process, unstable driving process and defect of enabling the structure to vibrate and be damaged easily of an existing inflatable or mechanical space deployable structure. The unfolding method is specifically implemented according to the steps of first, synthesizing a shape memory polymer film, and covering an electrothermal film on the shape memory polymer film; second, fixing the solar battery array on the shape memory polymer film covered with the electrothermal film, and acquiring a shape memory polymer based space flexible solar battery array; third, acquiring a flexible solar battery array which is solidified into a curled shape; and fourth, electrifying and heating the electrothermal film of the flexible solar battery array which is solidified into the curled shape, wherein the flexible solar battery array with the curled shape is recovered to a straight state, and unfolding of the shape memory polymer based space flexible solar battery array is completed. The unfolding method provided by the invention is applied to the field of spaceflight.

Description

technical field [0001] The invention relates to a method for deploying a space flexible solar cell array. Background technique [0002] Spacecraft is the carrier of human space development, deep space exploration and other space missions. At present, solar energy is the most widely used energy source in space missions. Materials with photoelectric conversion characteristics are made into solar cells and arranged in a certain order and installed on the structure. The structure of the solar cell array is formed on the surface. "Generally, the structure of the solar cell array is an overhanging structure with one end connected to the spacecraft and the other end extending freely." This structure is usually called a solar panel or a solar cell wing. The technology has the characteristics of safety and environmental protection, and can replace nuclear radioisotope thermal motors to perform near-planetary missions. When the spacecraft is in the launch state, the solar cell array ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H02S30/20
CPCH02S30/00Y02E10/50
Inventor 刘彦菊赵伟刘立武冷劲松杜海洋
Owner 苏州智新复合材料有限公司
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