Satellite screen display system and solar cell array substrate integrated device

Abstract

The embodiment of the invention discloses a device for integrating a satellite screen display system and a solar cell array substrate, relates to the technical field of satellite design, realizes installation of a star screen by utilizing the solar cell array substrate of a satellite, has relatively high flexible adaptation and implementation, and can be applied to the field of satellite design. As the star screen is mounted on the non-patch surface of the solar cell array substrate, normal use of the solar cell array substrate is not affected, and the star screen can be opened along with rotation of the solar cell array substrate when needed, and can be recovered along with rotation of the solar cell array substrate and attached to the outer wall of the satellite deck when not used. When dismounting and position adjustment are needed, only the solar cell array substrate needs to be separated from the solar cell array substrate, the layout of the satellite body is not affected by design and assembly, and the solar cell array substrate is simple and reliable in structure, low in implementation difficulty, low in design cost and good in on-satellite application effect.

Description

Technical Field

[0001] The present application relates to the field of satellite design technology, and in particular to a device integrating a satellite screen display system with a solar cell array substrate. Background Art

[0002] The star screen display system of traditional satellites is assembled in the satellite cabin panel, which is not easy to disassemble and adjust the position. If the position of the star screen needs to be adjusted, there are many design barriers. For example, the entire satellite cabin panel needs to be redesigned and processed, so the cost of the change is high. In addition, for different types of satellites, the satellite space shooting device needs to be specially designed and implemented, and the adaptation freedom and iterability are not high, and the project cost between different satellites is high. Summary of the invention

[0003] The main purpose of the present application is to provide a device integrating a satellite screen display system with a solar cell array substrate, aiming to solve the problem in the prior art that the position of the satellite screen is inconvenient to adjust.

[0004] The technical solutions adopted in this application are as follows:

[0005] A device integrating a satellite screen display system and a solar cell array substrate, comprising: a solar cell array substrate, a star screen and a satellite cabin board, wherein the solar cell array substrate is rotatably arranged on the outer wall of the satellite cabin board so as to fit the outer wall of the satellite cabin board after being rotated and retracted, and the star screen is arranged on a non-patch surface of the solar cell array substrate so as to face one side of the satellite cabin board when the solar cell array substrate is rotated and opened.

[0006] Optionally, the device further comprises a heat insulation component, which is arranged between the star screen and the solar cell array substrate.

[0007] Optionally, the thermal insulation component includes multiple functional unit layers and an outermost layer, each functional unit layer includes a reflective layer and a spacer layer, wherein the reflective layer is located between the surface layer and the internal layers of the functional unit layer and is used to reflect incident thermal radiation and light radiation, the spacer layer is located between the reflective layers, and the outermost layer is located on the surface of the thermal insulation component and is used to protect the functional unit layer.

[0008] Optionally, the reflective layer is made of an aluminum-plated film or a metal foil.

[0009] Optionally, the spacer layer is made of polyester mesh or polyimide film.

[0010] Optionally, the outermost layer is made of alumina or silicate.

[0011] Optionally, the device also includes a star screen camera, which is arranged on the satellite cabin board and is used to take pictures of the star screen when the solar cell array base plate is rotated and opened.

[0012] Optionally, the device also includes a star screen camera bracket, and the star screen camera is installed on the satellite cabin board through the star screen camera bracket.

[0013] Optionally, the device further comprises a locking structure, which is used to lock the state of the solar cell array substrate when the solar cell array substrate is retracted, and is used to unlock the state of the solar cell array substrate when the solar cell array substrate needs to be opened.

[0014] Optionally, the star screen is mounted on the non-mount surface of the solar cell array substrate by titanium screws.

[0015] Compared with the prior art, the beneficial effects of this application are:

[0016] The embodiment of the present application proposes a device that integrates a satellite screen display system and a solar cell array substrate. The installation of the star screen is achieved by using the solar cell array substrate of the satellite. The device has high flexibility, adaptability and feasibility. Since the star screen is installed on the non-patch surface of the solar cell array substrate, it will not affect the normal use of the solar cell array substrate. The star screen can be opened when needed along with the rotation of the solar cell array substrate. When not in use, the star screen can be recovered and adhered to the outer wall of the satellite cabin panel along with the rotation of the solar cell array substrate. When it needs to be disassembled or the position adjusted, it only needs to be separated from the solar cell array substrate. The design and assembly do not affect the layout of the satellite body. The device has a simple and reliable structure, low implementation difficulty, low design cost, and good on-board application effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 An axonometric diagram of a device integrating a satellite screen display system and a solar cell array substrate provided in an embodiment of the present application;

[0018] Figure 2 A side view of a device integrating a satellite screen display system and a solar cell array substrate provided in an embodiment of the present application;

[0019] Figure 3 A top view of a device integrating a satellite screen display system and a solar cell array substrate provided in an embodiment of the present application;

[0020] Figure 4 A thermal control diagram of a device integrating a satellite screen display system and a solar cell array substrate provided in an embodiment of the present application;

[0021] Description of the reference numerals in the accompanying drawings:

[0022] 1-satellite cabin panel, 2-star screen, 3-solar cell array substrate, 4-cables, 5-star screen camera, 6-star screen camera bracket, 7-cable connector, 8-titanium screws, 9-thermal insulation assembly, 10-thermal insulation pad. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0024] It should be noted that all directional indications in the embodiments of the present application (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0025] In this application, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0026] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present application, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing in the full text includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme that satisfies both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in the field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0027] The embodiment of the present application provides a device integrating a satellite screen display system and a solar cell array substrate, as shown in the attached Figure 1 -Attached Figure 4As shown, it includes: a solar cell array substrate 3, a star screen 2 and a satellite cabin panel 1, wherein the solar cell array substrate 3 is rotatably set on the outer wall of the satellite cabin panel 1 so that it can fit the outer wall of the satellite cabin panel 1 after being rotated and retracted, and the star screen 2 is set on the non-patch surface of the solar cell array substrate 3 so that it faces one side of the satellite cabin panel 1 when the solar cell array substrate 3 is rotated and opened.

[0028] In this embodiment, the installation of the star screen 2 is achieved by utilizing the solar cell array substrate 3 of the satellite, which has high flexibility, adaptability and feasibility. Since the star screen 2 is installed on the non-patch surface of the solar cell array substrate 3, it will not affect the normal use of the solar cell array substrate 3, and the star screen 2 can be opened with the rotation of the solar cell array substrate 3 when needed, and can be recovered and adhered to the outer wall of the satellite cabin panel 1 with the rotation of the solar cell array substrate 3 when not in use. When it needs to be disassembled or adjusted in position, it only needs to be separated from the solar cell array substrate 3. The design and assembly do not affect the layout of the satellite body, and the structure is simple and reliable, with low implementation difficulty and low design cost, and has a good on-board application effect.

[0029] In one embodiment, since the temperature variation range of the solar cell array substrate on orbit is -90°C to +90°C, the temperature variation in the light and shadow areas is drastic and the temperature variation range is wide, the star screen 2 needs to be installed with heat insulation to ensure that the star screen 2 can work normally in the space environment; as shown in the attached Figure 4 As shown, the device also includes a heat insulation component 9, which is arranged between the star screen 2 and the solar cell array substrate 3; the star screen 2 can be installed by raising the heat insulation pad 10, the material of the heat insulation pad 10 can be fiberglass. As in the embodiment of the present application, the 5mm heat insulation pad 10 is selected according to the thickness of the multi-layer heat insulation component attached to the installation surface, that is, the size of the gap between the star screen 2 and the solar cell array substrate 3 after the star screen 2 is raised and installed.

[0030] FRP has good insulation properties and can effectively block current and heat. FRP is made of synthetic resin and glass fiber through a composite process. It has the characteristics of light weight and high specific strength, and can maintain the stability and safety of the structure. The installation of the thermal insulation pad 10 can reduce the installation contact area between the star screen 2 and the solar cell array substrate 3, greatly reducing the heat transfer. For the satellite size used in the embodiment of this application, the covering area is about 0.069m 2 , reducing heat leakage by about 7 W. The other areas of the installation surface are covered with multi-layer insulation components to isolate the radiation heat exchange between the installation surface of the star screen 2 (the installation surface of the star screen 2 is on the surface where the insulation pad 10 is installed) and the sailboard.

[0031] Furthermore, the radiation heat exchange between the insulating mounting surface and the sailboard may cause the internal temperature of the star screen 2 to be unstable, exceeding the operating temperature range of the internal electronic devices, resulting in the malfunction of the internal electronic devices. Maintaining the temperature of the star screen 2 is very important for the normal operation of the internal electronic devices. The thermal insulation component 9 includes a plurality of functional unit layers and an outermost layer, each of which includes a reflective layer and a spacer layer, wherein the reflective layer is located between the surface layer and the internal layers of the functional unit layer, and is used to reflect incident thermal radiation and light radiation, the spacer layer is located between the reflective layers, and the outermost layer is located on the surface of the thermal insulation component, and is used to protect the functional unit layer.

[0032] The reflective layer, also known as the reflective screen, is usually made of a low-emissivity double-sided aluminized film or metal foil (such as aluminum foil). It is located between the surface layer and the internal layers of the functional unit layer to reflect incident thermal radiation and light radiation. It is required to have a high reflectivity and a low emissivity in order to effectively reflect heat flow. Aluminized film has the characteristics of both plastic film and metal. The function of aluminum plating on the surface of the film is to block light and prevent ultraviolet radiation. It has replaced aluminum foil to a certain extent and is also cheap and has good barrier properties.

[0033] The spacer layer is usually made of low thermal conductivity materials, such as polyester mesh, polyimide film, etc., and is located between the reflective layers to increase the interlayer thermal resistance. The spacer layer can further reduce the thermal conductivity of the multi-layer insulation assembly and improve the insulation effect. Polyester mesh is a polyester fiber product with a wide range of uses. Polyester mesh is not only extremely elastic and not easy to deform, but also has excellent flame retardant effect. Polyimide has excellent thermal stability, chemical corrosion resistance and mechanical properties, and stable chemical properties.

[0034] The outermost layer is usually made of high temperature resistant and radiation resistant materials, such as alumina and silicate, which is used to protect the internal reflective layer and spacer layer from the erosion of the space environment. At the same time, the outermost layer can absorb and scatter the incident thermal radiation, further reducing the absorption and conduction of heat. Alumina is a high hardness compound with a melting point of 2054℃ and a boiling point of 2980℃. It is an ion crystal that can be ionized at high temperatures and is often used to make refractory materials; silicate refers to the general term for compounds formed by the combination of silicon, oxygen and other chemical elements (mainly aluminum, iron, calcium, magnesium, potassium, sodium, etc.).

[0035] In one embodiment, as shown in the attached Figure 1 , Attachment Figure 2 As shown, the device also includes a star screen camera 5, which is arranged on the satellite cabin board 1 and is used to take pictures of the star screen 2 when the solar cell array substrate 3 is rotated and opened. Figure 1As shown, the star screen camera 5 can be installed on the satellite cabin board 1 through the star screen camera bracket 6. When the satellite enters the space environment, the star screen 2 is unfolded along with the solar cell array substrate. The star screen 2 can play the uploaded content. The star screen camera 5 shoots the playback content displayed by the star screen 2 at a predetermined position. The captured background can display the earth in the playback background of the star screen 2 through satellite attitude control. Then the playback content of the star screen 2 with the earth background captured by the star screen camera 5 is transmitted back to the ground for research.

[0036] As attached Figure 3 As shown, the power supply of the star screen 2 is realized through the cable 4. The number and type requirements of the cable connectors 7 of the star screen 2 are determined according to the specific task requirements, such as how many external single machines are required, such as external cameras or power supply interfaces, etc. The connector required by the task requirements in the embodiment of the present application is a J30J connector, which is mainly used for power supply and data transmission.

[0037] In one embodiment, the device further includes a locking structure, which is used to lock the state of the solar cell array substrate 3 when the solar cell array substrate 3 is retracted, and is used to unlock the state of the solar cell array substrate 3 when the solar cell array substrate 3 needs to be opened. As in the above embodiment, the state of the solar cell array substrate 3 is stabilized by the locking structure to ensure stable operation of the satellite, such as controlling the state of the rotating part by the locking device to fix the solar cell array substrate 3 at a certain position on the rotation stroke, or providing a mutually cooperating plug-in locking structure on the non-patch surface of the solar cell array substrate 3 and the outer wall of the satellite cabin board 1, such as a separation nut to achieve connection locking and separation between the movable end of the solar cell array substrate 3 and the satellite cabin board 1.

[0038] In one embodiment, as shown in the attached Figure 4 As shown, the star screen 2 is mounted on the non-patch surface of the solar cell array substrate 3 by titanium screws 8; the patch surface of the solar cell array substrate 3 refers to the side with the solar cell attached, which is usually facing outward when the solar cell array substrate 3 is unfolded to absorb solar energy, and the non-patch surface is the other side of the solar cell array substrate 3, which is usually described as the back side. As in the above embodiment, the titanium screw 8 is a titanium alloy screw, which is lighter than ordinary steel screws. Titanium alloy is a high-strength material that can provide reliable fastening force to ensure that the connection between the various components of the satellite is firm and reliable; satellites need to face extreme high temperatures, low temperatures, radiation and other harsh environments in space. Titanium alloy screws have excellent corrosion resistance and can operate stably for a long time in these harsh environments without loosening or failure due to corrosion. This is crucial to ensure the firm connection between the various components of the satellite and the long-term stable operation of the satellite.

[0039] In summary, the device of integrating a satellite screen display system and a solar cell array substrate proposed in the embodiment of the present application utilizes the solar cell array substrate of the satellite to realize the installation of the star screen, and has high flexibility, adaptability and feasibility. Since the star screen is installed on the non-patch surface of the solar cell array substrate, it will not affect the normal use of the solar cell array substrate, and the star screen can be opened with the rotation of the solar cell array substrate when needed, and can be recovered and adhered to the outer wall of the satellite cabin panel with the rotation of the solar cell array substrate when not in use. When it needs to be disassembled and the position adjusted, it only needs to be separated from the solar cell array substrate. The design and assembly do not affect the layout of the satellite body, and the structure is simple and reliable, with low implementation difficulty and low design cost, and has a good on-board application effect.

[0040] The above description is only a preferred embodiment of the present application and is not intended to limit the present application. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present application should be included in the protection scope of the present application.

Claims

1. A device integrating a satellite screen display system with a solar cell array substrate, characterized in that: include: A solar cell array substrate, a star screen and a satellite cabin panel, wherein the solar cell array substrate is rotatably arranged on the outer wall of the satellite cabin panel so as to be attached to the outer wall of the satellite cabin panel after being rotated and retracted, and the star screen is arranged on the non-patch surface of the solar cell array substrate so as to face one side of the satellite cabin panel when the solar cell array substrate is rotated and opened.

2. The device for integrating a satellite screen display system with a solar cell array substrate according to claim 1, characterized in that: The device also includes a heat insulation component, which is arranged between the star screen and the solar cell array substrate.

3. The device for integrating a satellite screen display system with a solar cell array substrate according to claim 2, characterized in that: The thermal insulation component includes multiple functional unit layers and an outermost layer, each of the functional unit layers includes a reflective layer and a spacer layer, wherein the reflective layer is located between the surface layer and the internal layers of the functional unit layer, and is used to reflect incident thermal radiation and light radiation, the spacer layer is located between the reflective layers, and the outermost layer is located on the surface of the thermal insulation component, and is used to protect the functional unit layers.

4. The device for integrating a satellite screen display system with a solar cell array substrate according to claim 3, characterized in that: The reflective layer is made of aluminum-plated film or metal foil.

5. The device for integrating a satellite screen display system with a solar cell array substrate according to claim 3, characterized in that: The spacer layer is made of polyester net or polyimide film.

6. The device for integrating a satellite screen display system with a solar cell array substrate according to claim 3, characterized in that: The outermost layer is made of aluminum oxide or silicate.

7. The device for integrating a satellite screen display system with a solar cell array substrate according to claim 1, characterized in that: The device also includes a star screen camera, which is arranged on the satellite cabin board and is used to take pictures of the star screen when the solar cell array substrate is rotated and opened.

8. The device for integrating a satellite screen display system with a solar cell array substrate according to claim 7, characterized in that: The device also includes a star screen camera bracket, and the star screen camera is installed on the satellite cabin board through the star screen camera bracket.

9. The device for integrating a satellite screen display system with a solar cell array substrate according to claim 1, characterized in that: The device further comprises a locking structure, which is used to lock the state of the solar cell array substrate when the solar cell array substrate is retracted, and is used to unlock the state of the solar cell array substrate when the solar cell array substrate needs to be opened.

10. The device for integrating a satellite screen display system with a solar cell array substrate according to claim 1, characterized in that: The star screen is mounted on the non-mounting surface of the solar cell array substrate by titanium screws.

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