All-carbon fiber microsatellite solar wing substrate
By using a microsatellite solar panel substrate with an all-carbon fiber structure, the problems of high production cost and low efficiency in existing technologies have been solved, achieving efficient and low-cost mass production and excellent mechanical properties.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-17
- Publication Date
- 2026-03-10
AI Technical Summary
Existing microsatellite solar panel substrate materials mostly use aluminum/aramid honeycomb core materials, which have problems such as high production costs and low production efficiency, making it difficult to meet the needs of mass production.
It adopts a full carbon fiber structure, including upper and lower carbon fiber mesh panels, carbon fiber honeycomb and metal embedded parts, which are bonded by adhesive film and foam and molded to achieve efficient mass production.
It achieves significant weight reduction, lower production costs, improved production efficiency, meets the requirements of space environment use, and has excellent mechanical properties.
Smart Images
Figure CN223982673U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to a kind of full carbon fiber micro-satellite solar wing base plate. TECHNICAL BACKGROUND
[0002] At present, micro-satellite solar wing base plate material mostly adopts aluminum / aramid honeycomb core material, while carbon fiber honeycomb has good high specific strength, high specific modulus and other mechanical properties, and low thermal expansion coefficient, which ensures that the solar wing base plate has highly stable characteristics, and has very good weight reduction effect. Therefore, the research on using carbon fiber honeycomb core to replace aluminum / aramid honeycomb core to prepare solar wing base plate is also increasing.
[0003] While the number of micro-satellite projects is increasing significantly year by year, it is also required to change the production mode of solar wing base plate from mainly research to small batch production to batch production, reduce production cost, improve production efficiency and product quality stability. SUMMARY
[0004] To achieve high-quality, low-cost, and batch production of solar wing base plate, the utility model provides a full carbon fiber micro-satellite solar wing base plate.
[0005] The utility model provides a kind of full carbon fiber micro-satellite solar wing base plate, including upper and lower two carbon fiber grid panels, carbon fiber honeycomb and metal embedded part.
[0006] Preferably, the carbon fiber grid panel is made of 3-6mm wide carbon fiber, laid on the jig according to 0 / 90° to process into a square grid structure, and the grid side length is 3-6mm.
[0007] Preferably, the surface of the upper carbon fiber grid plate is pasted with a polyimide film with a thickness of 50μm.
[0008] Preferably, the carbon fiber honeycomb core is a regular hexagon, the honeycomb core grid length is 2-5mm, the wall thickness is 0.03-0.1mm, the honeycomb thickness is 15-25mm, and the density is 30-90kg / m 3 .
[0009] Preferably, the embedded part is 4 electric connector embedded parts and 2 pressing point embedded parts, which are all made of 2A12 aluminum alloy, and the surface of the embedded part is anodized.
[0010] Preferably, a 0.1mm thick adhesive film is used to bond between the polyimide film and the grid plate and between the grid plate and the carbon fiber honeycomb.
[0011] Preferably, foaming glue is used to bond between the embedded part and the carbon fiber honeycomb.
[0012] The utility model discloses a beneficial effect is: the utility model discloses a whole carbon fiber microsatellite solar wing base plate, the effect of weight reduction is obvious, utilizes 36kg / m 3 Specification carbon fiber honeycomb replaces 52kg / m 3 Aluminum honeycomb, and the weight reduction benefit reaches 30%; the forming cycle is short, and the manufacturing cost is low; the grid is neat and symmetrical, and the resin content is uniform; the mechanical property satisfies the design requirement. BRIEF DESCRIPTION OF DRAWINGS
[0013] Figure 1 It is a whole carbon fiber microsatellite solar wing base plate overall schematic diagram of the utility model.
[0014] Figure 2 It is a whole carbon fiber microsatellite solar wing base plate structure schematic diagram of the utility model.
[0015] Figure 1 The mark is: 1. polyimide film, 2. upper grid panel, 3. carbon fiber honeycomb, 4. lower grid panel, 5. metal embedded part. PREFERRED EMBODIMENT
[0016] The preferred embodiments of the utility model are described in detail below in combination with the drawings.
[0017] To realize the above-mentioned purpose, the utility model provides the following technical scheme: the embodiment provides a whole carbon fiber microsatellite solar wing base plate, including polyimide film [1], upper grid panel [2], carbon fiber honeycomb [3], lower grid panel [4], metal embedded part [5]. Polyimide film [1] and upper grid plate [2] are bonded into an integral whole with carbon fiber honeycomb [3] again, and metal embedded part [5] is inlaid in carbon fiber honeycomb [3], and is fixed with foaming glue.
[0018] Further, in the above scheme, the upper grid panel [2] and the lower grid panel [4] adopt M40-6K carbon fiber / epoxy 648 resin material, are cut into 3mm wide strips, and are laid on the jig according to 0 / 90 ° and are pasted into grid plates, and are cured into shape by pressing and heating.
[0019] Further, in the above scheme, the thickness of the obtained carbon fiber grid plate is 0.32mm, the grid plate size is 830X670mm, and the grid size is 3mmX3mm.
[0020] Further, in the above scheme, the thickness of the polyimide film is 50um, and the polyimide film and the grid panel are bonded into an integral whole with J-154 adhesive film with the thickness of 0.1mm.
[0021] Further, in the above scheme, the surface of the grid panel is polished rough, and the interfacial bonding strength with the polyimide film is improved.
[0022] Furthermore, in the above scheme, the embedded part includes 4 electrical connector embedded parts and 2 clamping point embedded parts, which are bonded and fixed in the carbon fiber honeycomb [3] by foam adhesive J-47D. During the molding process, a jig is used to control the position accuracy of the embedded parts.
[0023] Furthermore, in the above scheme, the carbon fiber honeycomb [3] has a thickness of 15.6 mm and a density of 36 kg / m³. 3 The honeycomb core cell has a wall thickness of 0.04 mm and a side length of 3 mm.
[0024] Furthermore, in the above scheme, the solar panel substrate is assembled in a mold. The grid panel [2][4], carbon fiber honeycomb [3], and embedded parts [5] are bonded by curing the adhesive film and foam. The mold is then placed in an oven and vacuumed at -0.05MPa. The heating temperature is 120℃ and the time is 3 hours. After the product is cooled to below 50℃ in the oven, it is demolded and the solar panel substrate is taken out. The molded solar panel substrate has good overall rigidity and stable quality; it meets the requirements of high and low temperature cycling and vacuum environments in space; the flatness tolerance of the solar panel substrate is less than 0.1mm; and the embedded parts are conductive with a resistance of less than 200 ohms.
[0025] The embodiments described above are only used to illustrate the technical ideas and features of this utility model. Their purpose is to enable those skilled in the art to understand the content of this utility model and implement it accordingly. The patent scope of this utility model should not be limited by these embodiments. That is, any equivalent changes or modifications made to the spirit disclosed in this utility model still fall within the patent scope of this utility model.
Claims
1. An all-carbon fiber micro-satellite solar wing substrate, characterized by, The solar wing base plate comprises: an upper layer carbon fiber grid panel, a lower layer carbon fiber grid panel, a carbon fiber honeycomb, a metal embedded part and a polyimide film; the upper layer carbon fiber grid panel, the lower layer carbon fiber grid panel, the carbon fiber honeycomb and the metal embedded part are fixed by glue jointing.
2. The solar wing substrate according to claim 1, characterized in that The carbon fiber grid panel is processed into a square grid structure by laying 3-6mm wide unidirectional carbon fiber 0 / 90° on a jig.
3. The solar wing substrate of claim 1, wherein, The upper layer carbon fiber grid panel is pasted with a polyimide film with a thickness of 50μm on the surface.
4. The solar wing substrate of claim 1, wherein, The carbon fiber honeycomb core is regular hexagon, core length 2-5mm; wall thickness 0.03-0.1mm, honeycomb thickness 15-25mm, density 30-90kg / m 3 .
5. The solar wing substrate of claim 1, wherein, The embedded parts are four electric connector embedded parts and two pressing point embedded parts.