A multi-layer thermal insulation structure for a space coronagraph scientific exploration module
By employing a multi-layered thermal insulation structure design in the coronagraph scientific exploration module, and using heat-resistant adhesives and high-strength materials, the problems of easy damage and heat conduction of multi-layered thermal insulation components are solved, achieving efficient thermal insulation and structural stability, which is suitable for space coronagraph scientific exploration modules.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- NANJING INST OF ASTRONOMICAL OPTICS & TECH NAT ASTRONOMICAL OBSE
- Filing Date
- 2025-10-10
- Publication Date
- 2026-07-31
AI Technical Summary
Existing multi-layer thermal insulation components are prone to damage due to pressure changes during the launch of the coronagraph, and cannot effectively isolate heat conduction between reflectors, affecting the thermal insulation effect and structural stability.
It adopts a multi-layer thermal insulation structure design, including a face film, multiple layers, a coating thermal insulation layer and nylon fasteners. It uses heat-resistant adhesives and high-strength materials, such as nylon mesh, double-sided aluminized polyester perforated film and UGC series thermal insulation coatings. The nylon fasteners and stitching materials form an integral structure, which enhances tensile strength and thermal insulation performance.
It improves the tensile strength and thermal insulation effect of the multi-layer thermal insulation structure, and can be used stably in the range of -60℃ to +120℃. It completely isolates the heat conduction between the reflectors, reduces weight, and does not affect the thermal insulation performance.
Smart Images
Figure CN224576824U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of coronagraph technology, and more particularly to a multi-layer heat insulation structure for a space coronagraph scientific exploration module. Background Technology
[0002] The coronagraph module of the space station's exoplanet imaging system probes exoplanets around nearby stars through its scientific exploration module, studying their physical properties. The multi-layered thermal insulation assembly is a key component for the external thermal insulation and internal gas depressurization of the coronagraph's scientific exploration module. This multi-layered structure consists of overlapping nylon mesh and insulating films. During launch, the external pressure of the multi-layered thermal insulation assembly drops rapidly, and the internal flow field changes rapidly, causing structural deformation under pressure. Excessive pressure can lead to structural damage. If the multi-layered thermal insulation assembly fails due to structural damage, it cannot be repaired, severely impacting the normal operation of the coronagraph's scientific exploration module. Therefore, providing a multi-layered thermal insulation assembly structure design with good temperature resistance and high tensile strength is crucial for ensuring the safe and reliable operation of the coronagraph's scientific exploration module. Existing multi-layered structures simply place the reflectors and spacers sequentially, making the multi-layered thermal insulation assembly susceptible to damage from pressure changes and failing to completely isolate heat conduction between two reflectors, resulting in poor thermal insulation performance. Utility Model Content
[0003] Purpose of the utility model: This utility model aims to provide a multi-layer heat insulation structure for a space coronagraph scientific exploration module. It effectively solves the problems of heat dissipation through conduction, radiation, and convection between the coronagraph scientific exploration module and the external environment. It possesses strong tensile strength, corrosion resistance, and wear resistance, preventing structural damage caused by excessive pressure on the multi-layer heat insulation structure.
[0004] Technical solution: This utility model discloses a multi-layer heat insulation structure for a space coronagraph scientific exploration module, comprising a surrounding membrane and multiple internal layers; each layer of the multi-layer comprises, from top to bottom, a spacer layer, a heat-resistant adhesive, and a reflector; a heat-insulating coating layer is provided on the spacer layer at the bottom of the multi-layer; the outer edge area of the membrane is provided with Velcro, and a sewing material is provided below the Velcro.
[0005] Furthermore, the mask is a two-layer polyimide black film.
[0006] Furthermore, the multilayer adopts a 4-6 layer structure, the spacer layer is made of nylon mesh, and the reflective screen is made of double-sided aluminized polyester perforated film with an aluminization thickness of 5-7 μm.
[0007] Furthermore, the heat-resistant adhesive is 802, 804, or 902 glue; the heat-resistant adhesive is applied to the spacer layer by spraying, and the spacer layer is then bonded to the reflector screen. The thickness of the heat-resistant adhesive is 0.1~0.2mm, and the amount of adhesive used per unit area is 10~17g / m². 2 .
[0008] Furthermore, the thickness of the heat insulation layer of the coating is 0.5~2mm, and UGC series heat insulation coating is used.
[0009] Furthermore, the length of the nylon hook and loop fastener is 30mm to 100mm, and the spacing between each nylon hook and loop fastener segment is 30mm to 100mm.
[0010] Furthermore, the Velcro fastener includes a hook layer and a fleece layer.
[0011] Beneficial effects: Compared with the prior art, the present invention has the following significant advantages: The multi-layer thermal insulation structure proposed in this invention effectively solves the problems of heat dissipation through conduction, radiation, and convection between the coronagraph scientific detection module and the external environment. It possesses strong tensile strength, corrosion resistance, and wear resistance, preventing structural damage due to excessive pressure. Secondly, this multi-layer thermal insulation structure completely isolates the heat conduction between the two reflectors, achieving complete non-contact between the multiple layers of insulation, thus effectively increasing the thermal insulation effect of the multi-layer thermal insulation component. It also exhibits good temperature resistance, maintaining a long-term operating temperature range of -60℃ to +120℃, demonstrating significant thermal insulation performance. Furthermore, without altering the multi-layer thermal insulation performance, the use of a coating insulation layer structure significantly reduces weight. Attached Figure Description
[0012] Figure 1 This is a schematic diagram of the structure of this utility model.
[0013] Figure 2 This is a schematic diagram of the multi-layer structure in this utility model.
[0014] Figure 3 This is a schematic diagram of the structure of the present invention, which includes a multi-layered heat insulation coating.
[0015] Figure 4 This is a top view of the multiple layers in this utility model.
[0016] Figure 5 This is a schematic diagram of the structure of the Velcro fastener in this utility model. Detailed Implementation
[0017] The technical solution of this utility model will be further described below with reference to the accompanying drawings.
[0018] like Figure 1-3As shown, this utility model discloses a multi-layer heat insulation structure for a space coronagraph scientific exploration module, comprising a surrounding membrane 1, an inner multi-layer structure 2, and a coating heat insulation layer 5. The membrane 1 consists of two layers of polyimide black film, which wrap the multi-layer structure 2. The multi-layer structure 2 is a 5-unit multi-layer structure, and each unit includes a spacer layer 201 and a reflector screen 202 from the inside out. The spacer layer 201 is made of nylon mesh. The reflector screen 202 is made of double-sided aluminized polyester perforated film with an aluminization thickness of 6 μm. The spacer layer 201 and the reflector screen 202 are bonded together with a heat-resistant adhesive 203, which is 802, 804, or 902 glue, and the long-term operating temperature is maintained at -60℃ to +120℃. The heat-resistant adhesive 203 is applied to the spacer layer 201 by spraying, and the spacer layer 201 is then bonded to the reflective screen 202. The thickness of the heat-resistant adhesive 203 is 0.1~0.2mm, and the amount of adhesive used per unit area is 10-17g / m2. The reflective screen 202 of the multilayer 2 faces the outer surface 101 of the mask 1, and the spacer layer 201 of the multilayer 2 faces the inner surface 102 of the mask 1.
[0019] A heat insulation coating layer 5 with a thickness of 0.5~2mm is coated on the spacer layer 201 of the multilayer 2 near the inner surface 102 of the face mask 1. The heat insulation coating layer 5 uses UGC series heat insulation coating produced by Zhejiang Yangu Technology Co., Ltd., which has the characteristics of good heat insulation, high bonding strength, short drying time, low shrinkage rate and not easy to crack after drying.
[0020] like Figure 4 , 5 As shown, a Velcro fastener 4 is provided on the edge area of the outer surface 101 of the mask 1; the length of each Velcro fastener 4 is preferably 30mm~100mm, and the spacing between each Velcro fastener 4 is preferably 30mm~100mm. The Velcro fastener 4 is composed of a hook layer 401 and a fleece layer 402. When the hook layer 401 and the fleece layer 402 are pressed together, the short hooks and fleece loops are hooked together and fastened. When subjected to a tensile force greater than 10kg perpendicular to the base surface 403, the elastic hooks are straightened and detached from the fleece loops, and then the hook layer 401 returns to its original hook shape.
[0021] The stitching material 3 is located directly below the Velcro 4, stitching the mask 1, the multi-layer 2 and the Velcro 4 together to form a whole.
Claims
1. A multi-layered heat insulation structure for a space coronagraph scientific exploration module, characterized in that, It includes a four-sided mask (1) and an inner multi-layer (2); each layer of the multi-layer (2) includes a spacer layer (201), a heat-resistant adhesive (203) and a reflector (202) from top to bottom; a heat-insulating coating layer (5) is provided on the spacer layer (201) at the bottom of the multi-layer (2); the outer edge area of the mask (1) is provided with a Velcro fastener (4), and a sewing material (3) is provided below the Velcro fastener (4).
2. The multi-layer heat insulation structure for a space coronagraph scientific exploration module according to claim 1, characterized in that, The face mask (1) is a two-layer polyimide black film.
3. The multi-layer heat insulation structure for a space coronagraph scientific exploration module according to claim 1, characterized in that, The multilayer (2) adopts a 4-6 layer structure, the spacer layer (201) adopts nylon mesh; the reflective screen (202) adopts a double-sided aluminum-plated polyester perforated film with an aluminum plating thickness of 5-7 μm.
4. The multi-layer heat insulation structure for a space coronagraph scientific exploration module according to claim 1, characterized in that, The heat-resistant adhesive (203) is made of 802, 804, or 902 glue. The heat-resistant adhesive (203) is applied to the spacer layer (201) by spraying, and the spacer layer (201) is then bonded to the reflector screen (202). The thickness of the heat-resistant adhesive (203) is 0.1~0.2mm, and the amount of adhesive used per unit area is 10~17g / m². 2 .
5. The multi-layer heat insulation structure for a space coronagraph scientific exploration module according to claim 1, characterized in that, The coating insulation layer (5) has a thickness of 0.5~2mm and uses UGC series thermal insulation coating.
6. The multi-layer heat insulation structure for a space coronagraph scientific exploration module according to claim 1, characterized in that, The length of the nylon hook and loop fastener (4) is 30mm to 100mm, and the spacing between each nylon hook and loop fastener (4) is 30mm to 100mm.
7. A multi-layer heat insulation structure for a space coronagraph scientific exploration module according to claim 1 or 6, characterized in that, The nylon hook and loop fastener (4) includes a hook layer (401) and a fleece layer (402).