Base plate assembly structure suitable for flexible solar wing
A component structure and flexible substrate technology, applied in the direction of electrical components, aerospace equipment, aerospace vehicles, etc., can solve the problem that the envelope size and weight cannot meet the requirements, and achieve light weight, large size, and thin thickness Effect
Pending Publication Date: 2020-11-20
SHANGHAI AEROSPACE SYST ENG INST
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Problems solved by technology
With the development of aerospace technology, the power demand of large spacecraft is increasing, which requires the area of solar cell wings to be larger and larger. If traditional rigid substrates or semi-rigid substrates are still used on large-area solar cell wings, it will It will face the problem that the envelope size and weight cannot meet the requirements after being folded, so it is urgent to develop flexible solar wing technology with small size and light weight
Method used
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[0028] The present invention will be further elaborated below in conjunction with embodiment.
[0029] combined reference figure 1 , the flexible substrate assembly provided by the present invention includes:
[0030] It consists of four parts: a flexible substrate 1, a piano hinge 2, a reinforcing bar 3, and a hanging support ring 4, and each component is glued into a whole by an adhesive. The flexible substrate assembly is divided into figure 2 There are two states of the flexible substrate assembly 1 and the flexible substrate assembly 2, and the substrate assemblies are connected by a 5-mandrel penetrating into the hinge hole. For flexible substrate components that require low-rail applications, atomic oxygen protection measures must be taken on the above components, and there is an atomic oxygen protection layer on the outer surface of the polyimide film. The atomic oxygen protection layer can be applied by brushing the anti-atomic oxygen organic silica gel on the sur...
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The invention relates to a base plate assembly structure suitable for a flexible solar wing. Each base plate assembly structure comprises a flexible base plate, piano hinges, reinforcing strips and hanging supporting rings, wherein the hanging supporting rings are fixedly installed on the two opposite sides of the flexible base plate, the piano hinges are fixedly installed on the other two sides of the flexible base plate, the reinforcing strips are installed on the two sides of the piano hinges, the flexible base plate is of a plane structure and is of a symmetrical structure when viewed fromthe cross section, the middle of the flexible base plate is a reinforcing layer, the upper layer and the lower layer close to the reinforcing layer are adhesive layers, polyimide film layers are arranged on the outer sides of the adhesive layers, the reinforcing layer and the polyimide film layers are bonded into a whole through the adhesive layers, and a plurality of base plate assemblies are connected through core shafts penetrating into the piano hinges.
Description
technical field [0001] The invention relates to a flexible solar cell wing substrate assembly structure, which can be used as an installation platform and a support carrier for large-area flexible solar wing cell circuits as a main component of a solar cell array. , to maintain the array configuration of the solar cell array after deployment in orbit, so as to meet the energy demand of the spacecraft in orbit. Background technique [0002] At present, domestic spacecraft solar wings generally adopt rigid solar wings and semi-rigid solar wings. The corresponding substrates (battery circuit installation platform and support carrier) are rigid substrates and semi-rigid substrates, and their weight is relatively heavy (area density is generally 1.0kg / m 2 ~2.5kg / m 2 ), and the size is larger after being folded (generally, the thickness of a single board is 23mm). With the development of aerospace technology, the power demand of large spacecraft is increasing, which requires t...
Claims
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Patent Timeline
Login to View More IPC IPC(8): H02S30/00H02S40/00B64G1/44
CPCH02S30/00H02S40/00B64G1/443Y02E10/50
Inventor 许文彬陈建祥咸奎成汤亮余守莉霍杰王治易张雷程雷郑宗勇
Owner SHANGHAI AEROSPACE SYST ENG INST