Satellite screen display system integrated with solar cell array substrate

Abstract

The embodiment of the application discloses a satellite screen display system and solar cell array substrate integrated device, relates to the technical field of satellite design, and utilizes the solar cell array substrate of the satellite to realize the installation of the star screen, has higher flexible adaptation and implementation, since the star screen is installed on the non-patch surface of the solar cell array substrate, the normal use of the solar cell array substrate is not affected, and the star screen can be opened along with the rotation of the solar cell array substrate when use is needed, is recycled along with the rotation of the solar cell array substrate when use is not needed, and is attached to the outer wall of the satellite cabin plate, when disassembly and position adjustment are needed, the star screen can be separated from the solar cell array substrate, the design and assembly do not affect the layout of the satellite main body, and the device has the advantages of simple and reliable structure, low implementation difficulty, low design cost and good on-satellite application effect.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of satellite design, in particular to a device integrating a satellite screen display system and a solar cell array substrate. BACKGROUND

[0002] A conventional satellite screen display system is assembled in a satellite cabin plate and is not easy to disassemble and adjust the position. If the position of the satellite screen needs to be adjusted, there are many design barriers, for example, the entire satellite cabin plate needs to be redesigned and processed, so that the cost of change is high, and the satellite space shooting device needs to be specially designed and implemented for different types of satellites, and the adaptive freedom and iteration are not high, and the project cost is high between different satellites. SUMMARY

[0003] The main purpose of the application is to provide a device integrating a satellite screen display system and a solar cell array substrate, which aims to solve the problem that the position of the satellite screen in the prior art is not convenient to adjust.

[0004] The technical scheme adopted by the application is as follows:

[0005] A device integrating a satellite screen display system and a solar cell array substrate, comprising: a solar cell array substrate, a satellite screen and a satellite cabin plate, wherein the solar cell array substrate is rotationally arranged on the outer wall of the satellite cabin plate, so as to be attached to the outer wall of the satellite cabin plate after being rotated and retracted, and the satellite screen is arranged on the non-pasting surface of the solar cell array substrate, so as to be directed to one side of the satellite cabin plate when the solar cell array substrate is rotated and opened.

[0006] Optionally, the device further comprises a heat insulation assembly arranged between the satellite screen and the solar cell array substrate.

[0007] Optionally, the heat insulation assembly comprises a plurality of functional unit layers and an outermost layer, each functional unit layer comprises a reflection layer and a spacing layer, wherein the reflection layer is located between the surface layer and the internal layers of the functional unit layer, and is used for reflecting incident heat radiation and light radiation, and the spacing layer is located between the reflection layers, and the outermost layer is located on the surface of the heat insulation assembly, and is used for protecting the functional unit layers.

[0008] Optionally, the reflection layer is made of an aluminized film or a metal foil.

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

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

[0011] Optionally, the device further comprises a satellite screen camera arranged on the satellite cabin plate, which is used for shooting the picture of the satellite screen when the solar cell array substrate is rotated and opened.

[0012] Optionally, the device further comprises a star screen camera support, and the star screen camera is installed on the satellite cabin plate through the star screen camera support.

[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 release the state locking of the solar cell array substrate when the solar cell array substrate needs to be opened.

[0014] Optionally, the star screen is installed on the non-pasting surface of the solar cell array substrate through titanium screws.

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

[0016] The satellite screen display system integrated with the solar cell array substrate device provided by the embodiment of the present application uses the solar cell array substrate of the satellite to install the star screen, has high flexible adaptation and implementation, and since the star screen is installed on the non-pasting surface of the solar cell array substrate, it will not affect the normal use of the solar cell array substrate. In addition, the star screen can be opened by rotating the solar cell array substrate when it needs to be used, and can be retracted and pasted to the outer wall of the satellite cabin plate by rotating the solar cell array substrate when it is not used. When it needs to be disassembled and 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 main body, and the structure is simple and reliable, the implementation difficulty is low, the design cost is low, and it has good on-satellite application effect. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 The isometric view of the satellite screen display system integrated with the solar cell array substrate device provided by the embodiment of the present application;

[0018] Figure 2 The side view of the satellite screen display system integrated with the solar cell array substrate device provided by the embodiment of the present application;

[0019] Figure 3 The top view of the satellite screen display system integrated with the solar cell array substrate device provided by the embodiment of the present application;

[0020] Figure 4 The thermal control diagram of the satellite screen display system integrated with the solar cell array substrate device provided by the embodiment of the present application;

[0021] Explanation of reference numerals in the drawings:

[0022] 1-satellite cabin plate, 2-star screen, 3-solar cell array substrate, 4-cable, 5-star screen camera, 6-star screen camera support, 7-cable connector, 8-titanium screw, 9-thermal insulation component, 10-thermal insulation pad. DETAILED DESCRIPTION

[0023] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by a person of ordinary skill in the art without creative effort are within the protection scope of the present application.

[0024] It should be noted that all direction indications (such as up, down, left, right, front, back, and the like) in the embodiments of the present application are only used to explain the relative position relationship, movement condition and the like between components in a certain posture (as shown in the drawings), and if the certain posture changes, the direction indications also change accordingly.

[0025] In the present application, unless specifically defined and limited otherwise, the terms "connection", "fixed", and the like should be understood in a broad sense, for example, "fixed" can be fixed connection, or detachable connection, or integral; can be mechanical connection, or electrical connection; can be direct connection, or indirect connection through an intermediate medium; can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise specifically limited. For a person of ordinary skill in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0026] In addition, if the present application has a description of "first", "second", etc., the description of "first", "second", etc. is only for the purpose of description, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first", "second" can explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing throughout the text includes three parallel solutions. For example, "A and / or B" includes A solution, or B solution, or A and B solution. In addition, the technical solutions of each embodiment can be combined with each other, but it must be based on the realization of a person of ordinary skill in the art, and when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, and is not within the protection scope of the present application.

[0027] The present application provides a satellite screen display system and a solar cell array substrate integrated device, as shown in the accompanying drawings Figure 1 -attached Figure 4As shown, the satellite comprises: a solar cell array substrate 3, a star screen 2, and a satellite cabin plate 1, wherein the solar cell array substrate 3 is rotationally arranged on the outer wall of the satellite cabin plate 1, so as to be attached to the outer wall of the satellite cabin plate 1 after being rotationally retracted, and the star screen 2 is arranged on the non-pasting surface of the solar cell array substrate 3, so as to be directed to the side of the satellite cabin plate 1 when the solar cell array substrate 3 is rotationally opened.

[0028] In the embodiment, the star screen 2 is mounted on the solar cell array substrate 3 of the satellite, which has high flexibility and implementation. Since the star screen 2 is mounted on the non-pasting surface of the solar cell array substrate 3, the normal use of the solar cell array substrate 3 is not affected. The star screen 2 can be opened with the solar cell array substrate 3 when needed, and can be retracted and attached to the outer wall of the satellite cabin plate 1 with the solar cell array substrate 3 when not in use. When disassembly or position adjustment is needed, the star screen 2 only needs to be separated from the solar cell array substrate 3. The design and assembly do not affect the layout of the satellite main body. The structure is simple and reliable, the implementation difficulty is low, the design cost is low, and the satellite application effect is good.

[0029] In an embodiment, since the in-orbit temperature of the solar cell array substrate changes in the range of -90℃ to +90℃, the temperature in the light and shadow areas changes dramatically and the temperature change range is wide. Therefore, the star screen 2 needs to be installed in thermal insulation to ensure that the star screen 2 works normally in the space environment. As shown in the accompanying drawings, Figure 4 As shown, the device further comprises a thermal insulation assembly 9 arranged between the star screen 2 and the solar cell array substrate 3. The star screen 2 can be installed by a thermal insulation pad 10. The material of the thermal insulation pad 10 can be glass fiber reinforced plastic. In the embodiment, the 5mm thermal insulation pad 10 is selected according to the thickness of the multiple thermal insulation assemblies installed on the mounting surface, that is, the gap between the star screen 2 and the solar cell array substrate 3 after the star screen 2 is installed by the thermal insulation pad 10.

[0030] The glass fiber reinforced plastic has good insulation performance and can effectively block current and heat energy. The glass fiber reinforced plastic material is made of synthetic resin and glass fiber through a composite process and has the characteristics of light weight and high specific strength, which 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 reduce the heat conduction and heat transfer amount, and for the satellite size applied in the embodiment, the coating area is about 0.069m 2 , and the heat leakage is reduced by about 7W. The multiple thermal insulation assemblies installed on the other areas of the mounting surface can insulate the radiation heat exchange between the star screen 2 mounting surface (the mounting surface of the star screen 2 is the surface on which the thermal insulation pad 10 is installed) and the sail plate.

[0031] Further, the radiation heat exchange between the installation surface and the sailboard can cause the temperature inside the star screen 2 to be unstable, exceeding the working temperature range of the internal electronic devices, causing the internal electronic devices to fail to function. It is important to keep the temperature of the star screen 2 stable for the normal operation of the internal electronic devices. The heat insulation assembly 9 includes a plurality of functional unit layers and an outermost layer. Each functional unit layer includes a reflective layer and a spacing layer. The reflective layer is located between the surface layer and the internal layers of the functional unit layer, and is used to reflect the incident thermal radiation and light radiation. The spacing layer is located between the reflective layers. The outermost layer is located on the surface of the heat insulation assembly, and is used to protect the functional unit layers.

[0032] The reflective layer, also known as a reflective screen, is usually made of a double-sided aluminized film or a metal foil (such as an aluminum foil) with low emissivity. It is located between the surface layer and the internal layers of the functional unit layer, and is used to reflect the incident thermal radiation and light radiation. It is required to have high reflectivity and low emissivity in order to effectively reflect the heat flow. The aluminized film has the characteristics of both plastic film and metal. The aluminized surface of the film serves as a light shield and protects against ultraviolet radiation, replacing the aluminum foil to some extent. It also has the advantages of low cost and good barrier properties.

[0033] The spacing layer is usually made of a material with low thermal conductivity, such as a polyester mesh or a polyimide film. It is located between the reflective layers and serves to increase the thermal resistance between the layers. By providing a spacing layer, the thermal conductivity of the multi-layer heat insulation assembly can be further reduced, improving the heat insulation effect. The polyester mesh is a polyester fiber product with a wide range of applications. It has excellent elasticity and is extremely resistant to deformation. It also has excellent flame retardant properties. Polyimide has excellent thermal stability, chemical corrosion resistance, and mechanical properties, and is chemically stable.

[0034] The outermost layer is usually made of a material that is resistant to high temperatures and radiation, such as alumina or silicate. It is used to protect the internal reflective layers and spacing layers from the space environment. At the same time, the outermost layer can also absorb and scatter incident thermal radiation, further reducing the absorption and conduction of heat. Alumina is a high-hardness compound with a melting point of 2054°C and a boiling point of 2980°C. It is an ionized crystal at high temperatures and is commonly used in the manufacture of refractory materials. Silicate refers to a 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 FIGS. 1-3, the device further includes a star screen camera 5 disposed on the satellite deck 1. The star screen camera 5 is used to capture the image of the star screen 2 when the solar cell array base plate 3 is turned on. Figure 1 Figure 2 The star screen camera 5 is used to capture the image of the star screen 2 when the solar cell array base plate 3 is turned on. Figure 1 ​As shown, the star screen camera 5 can be installed on the satellite cabin panel 1 through the star screen camera support 6. When the satellite enters the space environment, the star screen 2 is unfolded with the solar cell array base plate. The star screen 2 can play the uploaded content. The star screen camera 5 captures the playing content displayed by the star screen 2 at a predetermined position. The background of the captured content can be displayed on the star screen 2 by controlling the attitude of the satellite. Then, the playing content of the star screen 2 with the background of the earth captured by the star screen camera 5 is transmitted back to the ground for research.

[0036] As shown in the accompanying drawings, Figure 3 The power supply of the star screen 2 is realized through the cable 4. The number and type of the cable connector 7 of the star screen 2 are determined according to the specific task requirements. For example, the number of external single machines such as a camera or a power supply interface is required. In the task requirement of the embodiment of the present application, a J30J connector is required, which is mainly used for power supply and data transmission.

[0037] In an embodiment, the device further comprises a locking structure for locking the state of the solar cell array base plate 3 when the solar cell array base plate 3 is retracted, and for unlocking the state of the solar cell array base plate 3 when the solar cell array base plate 3 needs to be opened. As in the above embodiment, the state of the solar cell array base plate 3 is stabilized by the locking structure to ensure the stable operation of the satellite. For example, the state of the rotating part is controlled by the locking device to fix the solar cell array base plate 3 at a certain position on the rotating stroke, or the locking structure is inserted and matched on the non-pasting surface of the solar cell array base plate 3 and the outer wall of the satellite cabin panel 1, such as a split nut, to realize the connection and separation of the movable end of the solar cell array base plate 3 and the satellite cabin panel 1.

[0038] In an embodiment, as shown in the accompanying drawings, Figure 4 The star screen 2 is installed on the non-pasting surface of the solar cell array base plate 3 through the titanium screw 8. The pasting surface of the solar cell array base plate 3 refers to the surface on which the solar cell pieces are pasted. When the solar cell array base plate 3 is unfolded, it usually faces outward to facilitate the absorption of solar energy. The non-pasting surface of the solar cell array base plate 3 is usually described as the back surface. As in the above embodiment, the titanium screw 8 is a titanium alloy screw, which has a lighter weight compared to ordinary steel screws. Titanium alloy is a high-strength material that can provide reliable fastening force to ensure the firm and reliable connection between the components of the satellite. The satellite needs to face extreme high and low temperatures, radiation and other harsh environments in space. The titanium alloy screw has excellent corrosion resistance and can operate stably in these harsh environments for a long time without loosening or failure due to corrosion, which is crucial for ensuring the firm connection between the components of the satellite and the long-term stable operation of the satellite.

[0039] In summary, the satellite screen display system and the device integrated with the solar cell array substrate provided by the embodiments of the present application use the solar cell array substrate of the satellite to realize the installation of the star screen, have high flexible adaptation and implementation, and do not affect the normal use of the solar cell array substrate since the star screen is installed on the non-pasting surface of the solar cell array substrate. In addition, the star screen can be opened by rotating with the solar cell array substrate when it is needed to be used, and can be recycled by rotating with the solar cell array substrate and pasting the outer wall of the satellite cabin plate when it is not used. When it is needed to be disassembled and adjusted in position, it only needs to be separated from the solar cell array substrate, and the design and assembly do not affect the layout of the satellite main body. In addition, the structure is simple and reliable, the implementation difficulty is low, the design cost is low, and the satellite application effect is good.

[0040] The above only describes the preferred embodiments of the present application and is not intended to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall 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: The solar cell array substrate, the star screen, and the satellite compartment panel are provided. The solar cell array substrate is rotatably mounted on the outer wall of the satellite compartment panel so that it can fit against the outer wall of the satellite compartment panel after being rotated back. The star screen is disposed on the non-patch surface of the solar cell array substrate so that it faces the side of the satellite compartment panel when the solar cell array substrate is rotated open.

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 disposed 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 functional unit layer includes a reflective layer and a spacer layer. 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. The outermost layer is located on the surface of the thermal insulation component and is used to protect the functional unit layer.

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 thin 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 mesh 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 alumina 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 mounted on the satellite module and is used to capture images of the star screen when the solar array substrate is rotated open.

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, through which the star screen camera is mounted on the satellite module.

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 includes 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 to release the state lock 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-patch surface of the solar cell array substrate using titanium screws.

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