Supporting and positioning mechanism of satellite multi-layer heat insulation assembly

Abstract

The utility model discloses a mechanism for supporting and accurately positioning a multi-layer heat insulation assembly. The mechanism comprises a supporting cylinder, a flanging structure and a heat insulation base. According to the mechanism, multiple layers can be supported to the required height, meanwhile, the multiple layers can be accurately positioned, the heat insulation effect of the multiple layers can be guaranteed, and therefore the problems of flexible multiple-layer trepanning and positioning are effectively solved.

Description

Technical Field

[0001] The utility model relates to the technical field of spacecraft thermal control, in particular to a supporting and positioning mechanism for a multi-layer thermal insulation component. Background Art

[0002] In the aerospace field, multi-layer thermal insulation components are almost an indispensable passive thermal control material. By coating multi-layer thermal insulation components, the impact of high and low temperature environments inside and outside the spacecraft on the equipment can be reduced, and the temperature fluctuation of the equipment can be reduced and maintained within the required range.

[0003] In the application of multi-layer thermal insulation components, it is often necessary to perform operations such as opening holes and fixing edges of multiple layers according to the actual surface conditions of the equipment. In traditional multi-layer thermal implementation, in order to facilitate implementation, the holes of multiple layers are generally enlarged in a certain proportion according to the required apertures, and the edges of the multi-layer holes are fixed with Velcro or silicone rubber after coating.

[0004] The above-mentioned traditional multi-layer opening and implementation methods are suitable for some equipment components with low precision requirements such as temperature and field of view. However, for some optical equipment with small apertures and high temperature and field of view requirements, the selection of flexible multi-layer opening aperture size and fixing method is more difficult. On the one hand, if the opening design value is larger than the actual value and there is not enough multi-layer insulation, it is easy to affect the temperature of the internal equipment; if the opening is small, it will block the field of view of the equipment and affect performance. In addition, for multi-layer materials, it is difficult to make 1:1 openings strictly according to the actual size. On the other hand, since the multi-layer is a flexible product, the multi-layer near the hole position must be reliably fixed, otherwise it is easy to drift, resulting in inaccurate hole positioning. Therefore, the refined opening of the multi-layer and the positioning and fixation during installation are problems that increasingly miniaturized satellites will inevitably face and need to be solved urgently. Utility Model Content

[0005] The purpose of the utility model is to provide a mechanism for supporting and fixing a multi-layer thermal insulation assembly, which can support the multiple layers to the required height and accurately position them, and is sufficient to ensure the thermal insulation effect of the multiple layers, thereby effectively solving the opening and positioning problems of the flexible multiple layers.

[0006] In order to solve the above technical problems, the utility model provides a support and positioning mechanism for a satellite multi-layer thermal insulation assembly, comprising a support and positioning cylinder and a thermal insulation base;

[0007] The upper edge of the supporting and positioning cylinder is provided with an upper edge flange structure, and the upper edge flange structure is used to connect and fix the multi-layer heat insulation assembly;

[0008] The lower edge of the supporting and positioning cylinder is provided with a lower edge flange structure, the lower edge flange structure is an ear-shaped connection structure formed by flanging the lower edge of the supporting and positioning cylinder, and then milling and chamfering the lower edge, and a threaded hole for connecting with the heat insulation base is provided on the lower edge flange structure;

[0009] The upper edge flange structure and the lower edge flange structure are integrally formed with the supporting and positioning cylinder;

[0010] The heat-insulating base is integrally processed and cut to form a plurality of cylinder base connection bosses corresponding to the threaded holes on the lower edge flange structure. A through hole is provided at the center of the cylinder base connection boss. The screws are connected from bottom to top through the through hole at the center of the cylinder base connection boss and the threaded holes on the lower edge flange structure to achieve a fixed connection between the supporting and positioning cylinder and the heat-insulating base. The design of the boss can effectively reduce the contact area at the connection between the cylinder and the base, reduce heat leakage from the cylinder to the base, and further enhance the heat insulation effect.

[0011] Furthermore, a glass fiber reinforced plastic threaded sleeve is pre-installed on the threaded hole on the lower edge flange structure to further reduce heat leakage.

[0012] Furthermore, the upper edge flange structure is provided with a plurality of small holes, and flame-retardant wire is passed through the small holes to bundle and fix the multi-layer heat insulation assembly.

[0013] Furthermore, the thickness of the connecting boss of the cylinder base is 0.8-1.2 mm.

[0014] Furthermore, the supporting and positioning cylinder is made of metal, and the heat-insulating base is made of fiberglass.

[0015] Furthermore, the heat-insulating base is provided with a plurality of base-body connection holes, which are installed on the satellite body by screw connection.

[0016] In the mechanism provided by the utility model, the requirement of supporting multiple layers to the required height is achieved through the height design of the supporting cylinder itself; through the openings of the supporting cylinder, it is no longer necessary to rely on the openings of the multiple layers, so there is no need to consider the enlargement or reduction of the aperture, and it is only necessary to design the aperture of the supporting cylinder according to the actual aperture size, thereby solving the problem that the hole position of the multiple layers is too large, which affects the heat insulation effect, and the hole diameter is too small, which blocks the line of sight; through the small holes designed at the flange of the upper edge of the cylinder, the multiple layers are bundled and fixed with flame-retardant wire, which can further reinforce the multiple layers and avoid the problems of flexible multi-layer shaking and hole position drift; through the method of insulating the base, designing the boss and reducing the connection contact area, the heat leakage is effectively reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural explosion diagram of a support and positioning mechanism according to an embodiment of the utility model.

[0018] FIG. 2( a ) and FIG. 2( b ) are overall schematic diagrams of a support and positioning mechanism according to an embodiment of the present invention.

[0019] Figure 3 It is a partial cross-sectional view of a supporting and positioning mechanism according to an embodiment of the utility model.

[0020] As shown in the figure: 1-supporting and positioning cylinder; 2-upper edge flanging structure; 3-lower edge flanging structure; 4-insulating base; 5-cylinder base connecting boss; 6-base star connecting hole. DETAILED DESCRIPTION

[0021] The supporting and positioning mechanism proposed in the utility model is further described in detail below in combination with the accompanying drawings and specific embodiments. The advantages and features of the utility model will become clearer according to the following description and claims. It should be noted that the accompanying drawings are all in a very simplified form and are not in precise proportions, and are only used to facilitate and clearly assist the purpose of the embodiments of the utility model.

[0022] In addition, unless otherwise stated, features in different embodiments of the present invention may be combined and eliminated with each other.

[0023] The core idea of ​​the utility model is to provide a mechanism to solve the problem of multi-layer support and positioning of satellites and ensure their reliability and heat insulation effect.

[0024] In order to realize the above idea, the utility model provides a support and positioning mechanism for a satellite multi-layer thermal insulation assembly, including: a support cylinder and a flange structure, the upper edge flange structure is evenly provided with through holes for connecting and fixing the multi-layer thermal insulation assembly, and the lower edge flange structure is provided with threaded holes for connecting with the thermal insulation base;

[0025] Specifically, Figure 1 As shown in Figures 2(a) and 2(b), the support and positioning mechanism provided by the utility model includes a supporting and positioning cylinder 1, an upper edge flanging structure 2, a lower edge flanging structure 3, an insulating base 4, a cylinder base connecting boss 5, and a base star connecting hole 6.

[0026] The upper edge flange structure 2 and the lower edge flange structure 3 are integrally formed with the supporting and positioning cylinder 1, and the lower edge is milled and chamfered after flanged to form an ear-shaped connection structure to prevent stress concentration. The flange shape and size can also be adjusted according to the actual installation position and space conditions in application.

[0027] The heat insulating base 4 can be integrally processed with the cylinder base connecting boss 5 and then cut and formed. The design of the boss can effectively reduce the contact area at the connection between the cylinder and the base, reduce the heat leakage from the cylinder to the base, and further enhance the heat insulation effect. The thickness and shape of the boss can be adjusted according to the actual application conditions. The thickness of the boss is positively correlated with the heat insulation performance, but its mechanical properties will be weakened to a certain extent, so it needs to be considered comprehensively.

[0028] Figure 1 2(a) and 2(b) only schematically indicate the relative positional relationship of the components and do not represent the actual size.

[0029] The supporting and positioning cylinder 1 is usually made of metal materials, such as aluminum alloy, to ensure the strength and rigidity of the mechanism; the heat-insulating base 4 is generally made of heat-insulating materials, such as fiberglass, to weaken the thermal conductivity of the mechanism.

[0030] When the support cylinder 1 and the insulation base 4 are made of metal and fiberglass, it is difficult to process threaded holes in fiberglass, so the installation method is usually to connect the base to the cylinder with screws, that is, the fiberglass base is designed with through holes, and the metal cylinder has threaded holes, which is connected from bottom to top. Figure 3 The cross-sectional view of the mechanism more clearly shows the structural design of the cylinder and the connection mode with the base from bottom to top. In addition, the glass fiber reinforced plastic screw sleeve can be pre-installed on the threaded hole to further reduce heat leakage.

[0031] The heat-insulating base 4 is installed on the satellite body by screw connection.

[0032] The structure of the utility model has been put into practical application and verified on a certain on-orbit model. In this satellite model, the surface needs to have holes in the lens in the multi-layer, and it is exposed to direct sunlight in orbit, with poor external heat flow. In addition, the temperature requirement is relatively high, and the temperature fluctuation needs to be controlled at around 22 degrees, and the temperature fluctuation does not exceed 1 degree. The traditional multi-layer opening and coating used in the initial sample stage cannot guarantee the temperature requirements, and the multi-layers drift, which will block the field of view of the lens. The utility model mechanism is applied to the prototype and the launch part. Tests and on-orbit data show that both the temperature and field of view can meet the requirements, solving the problem of multi-layer opening and positioning.

[0033] In summary, the above embodiments provide a detailed description of the support and positioning mechanism of the multi-layer thermal insulation assembly. Of course, the present invention includes but is not limited to the configurations listed in the above embodiments. Any changes based on the configurations provided in the above embodiments fall within the scope of protection of the present invention. Those skilled in the art can draw inferences based on the contents of the above embodiments.

[0034] The above description is only a description of the preferred embodiment of the utility model, and is not any limitation on the scope of the utility model. Any changes and modifications made by ordinary technicians in the field of the utility model based on the above disclosure shall fall within the scope of protection of the claims.

Claims

1. A support and positioning mechanism for a satellite multi-layer thermal insulation assembly, Features : comprising a supporting and positioning cylinder (1) and a heat-insulating base (4); The upper edge of the supporting and positioning cylinder (1) is provided with an upper edge flange structure (2), and the upper edge flange structure (2) is used to connect and fix the multi-layer heat insulation assembly; The lower edge of the supporting and positioning cylinder (1) is provided with a lower edge flange structure (3), the lower edge flange structure (3) is an ear-shaped connection structure formed by flanging the lower edge of the supporting and positioning cylinder, followed by milling and chamfering, and the lower edge flange structure (3) is provided with a threaded hole for connection with the heat insulation base (4); The upper edge flange structure (2) and the lower edge flange structure (3) are integrally formed with the supporting and positioning cylinder (1); The heat insulating base (4) is integrally processed and cut to form a plurality of cylinder base connecting bosses (5) corresponding one to one with the threaded holes on the lower edge flange structure (3); a through hole is provided at the center of the cylinder base connecting boss (5), and screws are connected from bottom to top through the through hole in the center of the cylinder base connecting boss and the threaded holes on the lower edge flange structure to achieve a fixed connection between the supporting positioning cylinder and the heat insulating base.

2. A support and positioning mechanism for a satellite multi-layer thermal insulation assembly according to claim 1, Features : A glass fiber reinforced plastic threaded sleeve is pre-installed on the threaded hole on the lower edge flange structure (3).

3. A supporting and positioning mechanism for a satellite multi-layer thermal insulation assembly according to claim 1, Features The upper edge flange structure (2) is provided with a plurality of small holes, and a flame retardant wire is passed through the small holes to bundle and fix the multi-layer insulation assembly.

4. A supporting and positioning mechanism for a satellite multi-layer thermal insulation assembly according to claim 1, Features The thickness of the cylinder base connecting boss (5) is 0.8-1.2 mm.

5. A supporting and positioning mechanism for a satellite multi-layer thermal insulation assembly according to claim 1, Features The supporting and positioning cylinder (1) is made of metal, and the heat-insulating base (4) is made of fiberglass.

6. A supporting and positioning mechanism for a satellite multi-layer thermal insulation assembly according to claim 1, Features The heat-insulating base (4) is provided with a plurality of base star body connection holes (6) and is mounted on the satellite star body by screw connection.

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