A composite thermal insulation component for space cameras

Abstract

This invention relates to the field of spacecraft thermal control technology, specifically providing a composite thermal insulation component for a space camera. It is positioned between the visible and infrared channels of the space camera and mainly consists of a cavity-type thermal insulation structure, mounting surfaces, a thermal insulation pad, a radiation diaphragm, and a radiation baffle. The cavity-type thermal insulation structure includes a hollow structure of a frustum or cylinder, and flanges extending outwards at both ends of the hollow structure. At least one layer of radiation baffles is disposed within the hollow structure. Mounting holes are provided on the flanges. The two mounting surfaces are respectively used to connect to the support structures of the visible and infrared channels. The thermal insulation pad is positioned between the mounting surface and the cavity-type thermal insulation structure and is covered with a radiation diaphragm. This invention provides a composite thermal insulation component for different temperature zones of the space camera. Through the cavity-type thermal insulation design, it effectively increases the thermal resistance while reducing the overall mass of the thermal insulation structure.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft thermal control technology, and particularly relates to a composite heat insulation component for space cameras. Background Technology

[0002] To achieve all-weather observation, space cameras are increasingly designed to have both visible and infrared spectral capabilities. To achieve high integration, the visible and infrared channels typically share a common aperture design, using a common optical system at the front end and a beam-splitting design at the rear end to focus the visible and infrared light onto their respective focal plane components for imaging. The visible and infrared channels share a common rear-end optical path support structure. Space cameras generally operate at room temperature for the visible spectrum, while the infrared channel, to reduce background stray light, typically operates at low temperatures, usually below -30°C. Because the camera is assembled and tested at room temperature, its support structure and the visible channel are also at room temperature, resulting in a significant temperature difference between the visible and infrared channels. In the contact area between the two, parasitic heat flow severely impacts the temperature control and heat dissipation design of each channel. Summary of the Invention

[0003] In view of this, the present invention aims to provide a composite thermal insulation component for a space camera. By adding a composite thermal insulation component between the visible channel and infrared channel support structure of the space camera and adopting a cavity-type thermal insulation structure, the heat transfer resistance and radiation resistance between different temperature zones of the space camera are increased, thereby reducing the impact of parasitic heat flow on the temperature control and heat dissipation design of each channel.

[0004] To achieve the above objectives, the technical solution created by this invention is implemented as follows:

[0005] This invention provides a composite heat insulation component for a space camera, disposed between the visible channel and the infrared channel of the space camera, comprising:

[0006] A cavity-type thermal insulation structure includes a hollow structure of a frustum or column, and flanges extending outward from both ends of the hollow structure. At least one layer of radiant baffles arranged along the axial direction is provided inside the hollow structure, and mounting holes are provided on the flanges.

[0007] The first mounting surface, at one end of which a cavity-type heat insulation structure is provided, is used to connect with the support structure of the visible channel;

[0008] The second mounting surface has the other end of the cavity-type heat insulation structure, which is used to connect with the support structure of the infrared channel.

[0009] A first heat insulation pad is provided between the first mounting surface and the cavity heat insulation structure, and a second heat insulation pad is provided between the second mounting surface and the cavity heat insulation structure; and at least one layer of radiation diaphragm is applied to the side surface of the first heat insulation pad and the second heat insulation pad facing the cavity of the cavity heat insulation structure.

[0010] Preferably, the cavity-type thermal insulation structure is made of titanium alloy.

[0011] Preferably, the first heat insulation pad and the second heat insulation pad have a plurality of protrusions evenly distributed on one or both sides of their surfaces.

[0012] Preferably, the first and second heat insulation pads are made of polyimide or fiberglass.

[0013] Preferably, the radiation diaphragm is a double-sided aluminum-coated polyimide film with an infrared emissivity of less than 0.1.

[0014] Preferably, the radiant partition is attached to the inner wall of the cavity insulation structure by double-sided pressure-sensitive adhesive tape.

[0015] Preferably, the hollow structure of the cavity insulation structure is a frustum or a cylinder.

[0016] Compared with the prior art, the present invention can achieve the following beneficial effects:

[0017] This invention adds a composite heat insulation component between the visible channel and infrared channel support structure of a space camera. The composite heat insulation component adopts a cavity-type heat insulation design. On the one hand, through the dual heat insulation structure of the cavity-type heat insulation structure and the heat insulation pad, the heat conduction path is extended, the cross-sectional area of ​​the heat conduction path is reduced, and the thermal resistance is significantly increased. On the other hand, through the radiation partition and radiation membrane inside the cavity, the radiative heat transfer through the cavity is effectively suppressed.

[0018] This invention effectively solves the thermal insulation problem between room temperature and cryogenic components in the multi-spectral common aperture design of space cameras. Compared with traditional thermal insulation components, it not only effectively increases the thermal resistance through cavity thermal insulation design, but also reduces the mass of the entire thermal insulation structure. Attached Figure Description

[0019] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments and descriptions of the invention are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0020] Figure 1 This is an overall structural diagram of the space camera composite heat insulation component provided according to an embodiment of the present invention;

[0021] Figure 2 This is a structural diagram of the cavity-type thermal insulation structure provided in an embodiment of the present invention;

[0022] Figure 3 This is a structural diagram of the heat insulation pad provided according to an embodiment of the present invention.

[0023] The reference numerals in the figures include:

[0024] 1. First mounting surface; 2. First heat insulation pad; 3. First radiant diaphragm; 4. Cavity-type heat insulation structure; 5. Radiant partition; 6. Second radiant diaphragm; 7. Second mounting surface; 8. Boss; 9. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only for explaining the invention and do not constitute a limitation thereof. Similar elements in different embodiments are referred to by associated similar element reference numerals. In the following embodiments, many details are described to facilitate a better understanding of the invention. However, those skilled in the art will readily recognize that some features may be omitted in different situations, or may be replaced by other elements, materials, or methods. In some cases, some operations related to the invention are not shown or described in the specification. This is to avoid obscuring the core parts of the invention with excessive description. For those skilled in the art, detailed description of these related operations is not necessary; they can fully understand the related operations based on the description in the specification and general technical knowledge in the art.

[0026] It should be noted that, unless otherwise specified, the embodiments and features described in this invention can be combined to form various implementations. Furthermore, the order of the steps or actions in the method description can be changed or adjusted in a manner readily apparent to those skilled in the art. Therefore, the various orders in the specification and drawings are merely for the clear description of a particular embodiment and do not imply a mandatory order, unless otherwise stated that a particular order must be followed.

[0027] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0028] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0029] The invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0030] Please see Figure 1 , Figure 2 and Figure 3 In one embodiment of the present invention, a composite thermal insulation component for a space camera is provided. This component is disposed between the visible channel and the infrared channel of the space camera, providing thermal insulation at the connection point between the infrared channel and the camera support structure. Since the visible and infrared channels of the space camera share a rear-end optical path support structure, and both operate at room temperature, a significant temperature difference exists between them. This results in parasitic heat flow at their contact structure, severely affecting their respective temperature levels and the heat dissipation design of each channel. Therefore, the present invention designs a composite thermal insulation component for the space camera to insulate both the visible and infrared channels. Traditional thermal insulation components mostly use thermal pads made of low thermal conductivity materials. While existing components can isolate most heat transfer, they are insufficient for environments with a constant large temperature difference between the visible and infrared channels. Furthermore, as the operating temperature of the infrared channel decreases, the heat transferred from the visible support structure to the infrared channel through the thermal pad still significantly impacts the temperature level and heat dissipation design of the infrared channel. Therefore, existing thermal insulation components cannot be directly used.

[0031] The space camera composite heat insulation component provided in this embodiment of the invention includes:

[0032] The cavity insulation structure 4 includes a hollow structure of a frustum or column, and flanges extending outward from both ends of the hollow structure. At least one layer of radiant baffles 5 arranged along the axial direction is provided inside the hollow structure, and mounting holes are provided on the flanges.

[0033] The first mounting surface 1 has a cavity-type heat insulation structure 4 at one end, which is used to connect with the support structure of the visible channel.

[0034] The second mounting surface 8 is provided at the other end of the cavity-type heat insulation structure 4, which is used to connect with the support structure of the infrared channel.

[0035] A first heat insulation pad 2 is provided between the first mounting surface 1 and the cavity heat insulation structure 4, and a second heat insulation pad 7 is provided between the second mounting surface 8 and the cavity heat insulation structure 4; and at least one layer of radiation diaphragm is applied to the side surface of the first heat insulation pad 2 and the second heat insulation pad 7 facing the cavity of the cavity heat insulation structure.

[0036] The first mounting surface 1 and the second mounting surface 8 are respectively used to connect with the visible channel support structure and the infrared channel mounting surface. The first mounting surface 1 and the second mounting surface 8 are provided with threaded holes for the installation and fixing of the composite heat insulation component.

[0037] The cavity-type thermal insulation structure 4 is a hollow structure resembling a frustum of a cone or cylinder. Its outer wall thickness should be reduced as much as possible while meeting basic support requirements to minimize the heat conduction cross-sectional area and reduce the overall mass of the insulation component. The cavity-type thermal insulation structure 4 uses a low thermal conductivity metallic material, such as titanium alloy. Outwardly extending flanges with mounting holes are designed on the upper and lower surfaces of the hollow structure. The cavity-type thermal insulation structure 4, made of a low thermal conductivity metallic material such as titanium alloy, is connected to the first mounting surface 1 and the second mounting surface 8 via titanium alloy screws. A first thermal insulation pad 2 is placed between the first mounting surface 1 and the cavity-type thermal insulation structure 4, and a second thermal insulation pad 7 is placed between the second mounting surface 8 and the cavity-type thermal insulation structure 4. Both the first and second thermal insulation pads 2 and 7 are made of low thermal conductivity non-metallic materials, such as polyimide or fiberglass. Furthermore, multiple layers of radiative baffles 5 are installed inside the cavity-type thermal insulation structure 4 to reduce radiative heat transfer between the first thermal insulation pad 2 at the top and the second thermal insulation pad 2 at the bottom of the composite insulation component. The radiant partition 5 is attached to the inner wall of the cavity insulation structure 4 by double-sided pressure-sensitive adhesive tape.

[0038] To further suppress radiative heat transfer, at least one layer of a first radiative diaphragm 3 is attached to the surface of the first heat insulation pad 2 facing the inner cavity of the cavity-type heat insulation structure 4, and at least one layer of a second radiative diaphragm 6 is attached to the surface of the second heat insulation pad 7 facing the inner cavity of the cavity-type heat insulation structure 4. Both the first radiative diaphragm 3 and the second radiative diaphragm 6 are made of low infrared radiation films. Specifically, double-sided aluminized polyimide film can be used, with a surface emissivity of less than 0.1, which can effectively reduce radiative heat transfer between the first heat insulation pad 2 and the second heat insulation pad 7.

[0039] To further reduce heat conduction, bosses 9 are provided near the mounting holes on both the upper and lower surfaces of the first heat insulation pad 2 and the second heat insulation pad 7. The bosses 9 are evenly distributed on both sides of the first heat insulation pad 2 and the second heat insulation pad 7. The design of the bosses 9 on the first heat insulation pad 2 can reduce its contact area with the first mounting surface 1 and the cavity heat insulation structure 4; the design of the bosses 9 on the second heat insulation pad 7 can reduce its contact area with the second mounting surface 8 and the cavity heat insulation structure 4, effectively increasing the thermal resistance.

[0040] Compared to traditional heat insulation pads, this invention features a cavity-type heat insulation structure 4, combined with a first heat insulation pad 2 and a second heat insulation pad 7. While using materials with low thermal conductivity, it effectively reduces the heat conduction surface, improves heat resistance efficiency, and increases the conductive thermal resistance of the insulation component. This invention also effectively reduces heat radiation between the first heat insulation pad 2 and the second heat insulation pad 7 through a first radiative diaphragm 3, a radiative partition 5, and a second radiative diaphragm 6. This invention not only increases conductive thermal resistance but also effectively suppresses radiative heat transfer.

[0041] As an optional embodiment, the cavity insulation structure 4 can achieve vacuum insulation by setting radiant partitions 5 at both ends and sealing them to form a vacuum cavity between the radiant partitions 5.

[0042] In summary, the above description is merely a preferred embodiment of this specification and is not intended to limit the scope of protection of this specification. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this specification should be included within the scope of protection of this specification.

[0043] The systems, apparatuses, modules, or units described in one or more of the above embodiments may be implemented by a computer chip or entity, or by a product having a certain function. A typical implementation device is a computer. Specifically, a computer may be, for example, a personal computer, a laptop computer, a cellular phone, a camera phone, a smartphone, a personal digital assistant, a media player, a navigation device, an email device, a game console, a tablet computer, a wearable device, or any combination of these devices.

[0044] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0045] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to interchangeably. Each embodiment focuses on describing the differences from other embodiments. In particular, the system embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments.

Claims

1. A space camera composite thermal shield disposed between a visible channel and an infrared channel of a space camera, characterized by, The application relates to a cavity heat insulation structure, which comprises a hollow structure of a frustum or a cylinder, flanges outwardly extending at two ends of the hollow structure, at least one layer of radiation baffles arranged in the axial direction in the hollow structure, and mounting holes arranged on the flanges. A first mounting surface is arranged at one end of the cavity heat insulation structure and is used for being connected with a support structure of a visible channel. A second mounting surface is arranged at the other end of the cavity heat insulation structure and is used for being connected with a support structure of an infrared channel. First heat insulation pads are arranged between the first mounting surface and the cavity heat insulation structure, second heat insulation pads are arranged between the second mounting surface and the cavity heat insulation structure, and at least one layer of radiation membranes is attached to the side surfaces of the first heat insulation pads and the second heat insulation pads which face the inner cavity of the cavity heat insulation structure. The cavity heat insulation structure is made of titanium alloy material.

2. The spatial camera composite thermal insulator of claim 1, wherein, The first heat insulation pads and the second heat insulation pads are provided with a plurality of uniformly distributed convex bosses on one side or both sides.

3. The spatial camera composite thermal insulator of claim 1, wherein, The first heat insulation pads and the second heat insulation pads are made of polyimide or glass steel material.

4. The spatial camera composite thermal shield of claim 1, wherein, The radiation membrane is a double-side aluminum-plated polyimide membrane, and the surface infrared emissivity is less than 0.

1.

5. The spatial camera composite thermal shield of claim 1, wherein, The radiation baffles are fixedly attached to the inner wall of the cavity heat insulation structure through double-side pressure-sensitive adhesive tapes.

6. The spatial camera composite thermal shield of claim 1, wherein, The hollow structure of the cavity heat insulation structure is a circular frustum or a cylinder.

7. The spatial camera composite thermal insulator of claim 1, wherein, ​

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