An on-orbit replaceable flexible solar cell array and its on-orbit replacement method

Abstract

The application provides a replaceable flexible solar cell array in orbit, which comprises a body main structure, an on-orbit quick dismounting and mounting mechanical device, an on-orbit quick dismounting and mounting electrical connection device, an auxiliary compression interface assembly, an adapter capture interface assembly and a maintenance handrail; the on-orbit quick dismounting and mounting mechanical device is connected with the body main structure to realize mechanical on-orbit connection and fixation of the flexible solar cell array; the on-orbit quick dismounting and mounting electrical connection device is connected with the body main structure to realize on-orbit electrical connection of the flexible solar cell array; the auxiliary compression interface assembly is connected with the body main structure to realize on-orbit compression of the flexible solar cell array into a whole; the adapter capture interface assembly is connected with the body main structure to realize connection of the flexible solar cell array with a mechanical arm; and the maintenance handrail is connected with the body main structure to realize manual operation of the flexible solar cell array by astronauts; the patent has simple and reliable structure and can be replaced in orbit with the assistance of astronauts and the mechanical arm.

Description

Technical Field

[0001] This invention relates to the field of solar cell array technology, and more particularly to an on-orbit replaceable flexible solar cell array. Background Technology

[0002] With the development of my country's aerospace technology, astronauts have entered space and settled in space stations, making manned operation in space a reality. Space stations operate in orbit for a long time and have a long lifespan requirement, which requires flexible solar cell arrays to be repairable and replaceable in orbit. Through repair and replacement, they can continuously provide the space station with abundant energy. Therefore, there is an urgent need for a flexible solar cell array that is easy for astronauts to operate and can be replaced in orbit with the assistance of a robotic arm. Summary of the Invention

[0003] The purpose of this invention is to provide an on-orbit replaceable flexible solar cell array and its on-orbit replacement method. The array has a simple and reliable structure and can be replaced on-orbit with the assistance of astronauts and robotic arms.

[0004] This invention provides an on-orbit replaceable flexible solar cell array, including a main body structure, an on-orbit quick-disassembly and assembly mechanical device, an on-orbit quick-disassembly and assembly electrical connection device, an auxiliary clamping interface assembly, and an adapter capture interface assembly;

[0005] The on-orbit rapid assembly / disassembly mechanical device is connected to the main body structure to achieve mechanical on-orbit connection and fixation of the flexible solar cell array; the on-orbit rapid assembly / disassembly electrical connection device is connected to the main body structure to achieve on-orbit electrical connection of the flexible solar cell array; the auxiliary clamping interface assembly is connected to the main body structure to clamp the flexible solar cell array into a whole on-orbit; the adapter capture interface assembly is connected to the main body structure to connect the flexible solar cell array to the robotic arm.

[0006] Furthermore, it also includes a maintenance handrail; the maintenance handrail is connected to the main structure of the body and is used for hand-held operation by astronauts.

[0007] Furthermore, the on-orbit rapid disassembly and assembly mechanical device includes an M8 non-disengagement fastening device, a pressure plate, a torsion spring, and a wedge-shaped component;

[0008] The wedge-shaped component is connected to the main body structure to achieve connection and fixation of the main body structure; the pressure plate is connected to the second body to press the wedge-shaped component tightly, and the torsion spring is connected to the second body to press the pressure plate against the second body; the M8 non-disengaging fastening device is connected to the pressure plate to achieve connection and fixation between the pressure plate and the wedge-shaped component; the on-orbit rapid disassembly and assembly mechanical device achieves the mechanical connection between the flexible solar cell array and the second body.

[0009] Furthermore, the on-orbit quick-release electrical connection device includes an extravehicular astronaut-operable socket and an extravehicular astronaut-operable plug;

[0010] The extravehicular astronaut-operable socket is connected to the main structure of the main body, the extravehicular astronaut-operable plug is connected to the second body, and the extravehicular astronaut-operable socket is connected to the extravehicular astronaut-operable plug, thereby realizing the electrical connection between the flexible solar cell array and the second body.

[0011] Furthermore, the auxiliary clamping interface assembly includes a first interface component and a second interface component;

[0012] The auxiliary pressing interface assembly is provided with 4 groups, and the flexible solar cell array is connected into a whole through the first interface component and the second interface component in each group.

[0013] Furthermore, the adapter capture interface assembly includes a threaded interface, a third interface component, and a fourth interface component; after the adapter is guided and locked through the third and fourth interface components, the adapter is connected and fixed using the threaded interface.

[0014] Furthermore, the maintenance handrail includes a handrail, a first support, and a second support;

[0015] Both the first and second supports are connected to the main structure of the body, and the handrail is connected to the first and second supports.

[0016] Another technical solution of the present invention provides an on-orbit replacement method for an on-orbit replaceable flexible solar cell array, applicable to any of the on-orbit replaceable flexible solar cell arrays described above, including the removal of faulty components of the flexible solar cell array:

[0017] In the initial state, the faulty components of the flexible solar array are connected by an on-orbit rapid disassembly and assembly mechanical device and an on-orbit rapid disassembly and assembly electrical connection device. First, the astronauts use the auxiliary clamping interface assembly to fix the flexible solar array as a whole. Then, the adapter is installed at the adapter capture interface assembly, and the extravehicular robotic arm captures the adapter, thereby capturing the flexible solar array. The astronauts then disconnect the on-orbit rapid disassembly and assembly electrical connection device and the on-orbit rapid disassembly and assembly mechanical device in sequence. Finally, the extravehicular robotic arm moves the flexible solar array from the installation point to a nearby temporary extravehicular parking point 1, realizing the removal of the spare components of the flexible solar array.

[0018] Furthermore, it also includes the installation of spare parts for flexible solar cell arrays:

[0019] Initially, the flexible solar array spare parts are placed at the temporary parking point outside the cabin. An adapter is installed at the adapter capture interface assembly, and the extravehicular robotic arm captures the adapter, thereby capturing the flexible solar array. The extravehicular robotic arm moves the flexible solar array from the temporary parking point outside the cabin to the vicinity of the installation point. The astronaut holds the maintenance handle of the flexible solar array, aligns and locks its on-orbit quick-disassembly and assembly mechanical device, and sequentially connects and fixes the on-orbit quick-disassembly and assembly mechanical device and the on-orbit quick-disassembly and assembly electrical connection device to realize the installation of the flexible solar array spare parts.

[0020] The beneficial effects of the on-orbit replaceable flexible solar cell array and its on-orbit replacement method provided by this invention are as follows:

[0021] (1) The on-orbit replaceable flexible solar cell array of the present invention consists only of the main body structure, on-orbit quick disassembly and assembly mechanical device, on-orbit quick disassembly and assembly electrical connection device, auxiliary pressing interface assembly, adapter capture interface assembly, and maintenance handrail, and has a simple structure.

[0022] (2) The on-orbit replaceable flexible solar cell array provided by the present invention has an on-orbit quick disassembly and assembly mechanical device that can realize the mechanical connection between the flexible solar cell array and the second body.

[0023] (3) The on-orbit replaceable flexible solar cell array provided by the present invention has an on-orbit quick-installation and disassembly electrical connection device that can realize the electrical connection between the flexible solar cell array and the second body.

[0024] (4) The on-orbit replaceable flexible solar cell array provided by the present invention can be connected into a whole by the auxiliary pressing interface component;

[0025] (5) The on-orbit replaceable flexible solar cell array provided by the present invention has an adapter capture interface component that enables the electrical connection of the adapter.

[0026] (6) The on-orbit replaceable flexible solar cell array provided by the present invention has a maintenance handrail that allows astronauts to operate it by hand. Attached Figure Description

[0027] The invention will be further described below with reference to the accompanying drawings:

[0028] Figure 1 This is a schematic diagram of the state of an on-orbit replaceable flexible solar cell array according to an embodiment of the present invention.

[0029] Figure 2 This is a schematic diagram of an on-orbit replaceable flexible solar cell array installed in the second body state according to an embodiment of the present invention.

[0030] In the diagram, 1-Main body structure; 2-On-orbit rapid disassembly and assembly mechanical device; 3-On-orbit rapid disassembly and assembly electrical connection device; 4-Auxiliary clamping interface assembly; 5-Adapter capture interface assembly; 6-Maintenance handrail; 7-Second body; 21-M8 non-detachable fastening device; 22-Pressure plate; 23-Torsion spring; 24-Wedge-shaped component; 31-Extravehicular activity (EVA) astronaut-operable socket; 32-Extravehicular activity (EVA) astronaut-operable plug; 41-Interface component 1; 42-Interface component 2; 51-Threaded interface; 52-Interface component 3; 53-Interface component 4; 61-Handrail; 62-Support 1; 63-Support 2. Detailed Implementation

[0031] The following detailed description, in conjunction with the accompanying drawings and specific embodiments, provides a further detailed account of the on-orbit replaceable flexible solar cell array and its on-orbit replacement method proposed in this invention. The advantages and features of this invention will become clearer from the following description and claims. It should be noted that the drawings are all in a very simplified form and use non-precise ratios, and are only used to facilitate and clarify the illustration of the embodiments of this invention.

[0032] Example 1

[0033] Please refer to all factors. Figures 1 to 2 An on-orbit replaceable flexible solar array includes a main structure 1, an on-orbit quick-release mechanical device 2, an on-orbit quick-release electrical connection device 3, an auxiliary clamping interface assembly 4, an adapter capture interface assembly 5, and a maintenance handrail 6. The on-orbit quick-release mechanical device 2 is connected to the main structure 1 to achieve mechanical on-orbit connection and fixation of the flexible solar array. The on-orbit quick-release electrical connection device 3 is connected to the main structure 1 to achieve on-orbit electrical connection of the flexible solar array. The auxiliary clamping interface assembly 4 is connected to the main structure 1 to achieve on-orbit clamping of the flexible solar array into a whole. The adapter capture interface assembly 5 is connected to the main structure 1 to achieve connection between the flexible solar array and a robotic arm. The maintenance handrail 6 is connected to the main structure 1 to allow the flexible solar array to be operated by hand by astronauts. This patent has a simple and reliable structure and can achieve on-orbit replacement with the assistance of astronauts and a robotic arm.

[0034] In this embodiment, as Figure 1 , Figure 2 As shown, the on-orbit rapid assembly / disassembly mechanical device 2 includes an M8 non-detachable fastening device 21, a pressure plate 22, a torsion spring 23, and a wedge 24. The wedge 24 is connected to the main body structure 1 to achieve connection and fixation. The pressure plate 22 is connected to the second body 7 to press the wedge 24 tightly. The torsion spring 23 is connected to the second body 7 to press the pressure plate 22 against the second body 7. The M8 non-detachable fastening device 21 is connected to the pressure plate 22 to achieve connection and fixation between the pressure plate 22 and the wedge 24. The on-orbit rapid assembly / disassembly mechanical device 2 achieves the mechanical connection between the flexible solar cell array and the second body 7.

[0035] In this embodiment, as Figure 1 , Figure 2 As shown, the on-orbit rapid assembly and disassembly electrical connection device 3 includes an extravehicular astronaut-operable socket 31 and an extravehicular astronaut-operable plug 32; wherein the extravehicular astronaut-operable socket 31 is connected to the main body structure 1, and the extravehicular astronaut-operable plug 32 is connected to the second body 7. The connection between the extravehicular astronaut-operable socket 31 and the extravehicular astronaut-operable plug 32 realizes the electrical connection between the flexible solar cell array and the second body 7.

[0036] In this embodiment, as Figure 1 , Figure 2 As shown, the auxiliary pressing interface assembly 4 includes a first interface component 41 and a second interface component 42; the auxiliary pressing interface assembly 4 is provided with 4 sets, and the flexible solar cell array is connected into a whole through the first interface component 41 and the second interface component 42.

[0037] In this embodiment, as Figure 1 , Figure 2 As shown, the adapter capture interface assembly 5 includes a threaded interface 51, a third interface piece 52, and a fourth interface piece 53; after the adapter is guided and locked by the third interface piece 52 and the fourth interface piece 53, the adapter is connected and fixed by the threaded interface 51.

[0038] In this embodiment, as Figure 1 , Figure 2 As shown, the maintenance handrail 6 includes a handrail 61, a first support 62, and a second support 63; wherein the first support 62 and the second support 63 are both connected to the main structure 1, and the handrail 61 is connected to the first support 62 and the second support 63, so that the maintenance handrail 6 is connected to the main structure 1, and astronauts can use the maintenance handrail 6 to disassemble and assemble the flexible solar cell array.

[0039] In this embodiment, as Figure 1 , Figure 2 As shown, the on-orbit replacement method for an on-orbit replaceable flexible solar cell array is characterized by two steps: removal of faulty components from the flexible solar cell array and installation of spare components for the flexible solar cell array.

[0040] The steps for removing faulty components from a flexible solar array are as follows:

[0041] In the initial state, the faulty components of the flexible solar array are connected by the on-orbit rapid disassembly and assembly mechanical device 2 and the on-orbit rapid disassembly and assembly electrical connection device 3. First, the astronauts use the auxiliary clamping interface assembly 4 to fix the flexible solar array as a whole. Then, the adapter is installed at the adapter capture interface assembly 5, and the extravehicular robotic arm captures the adapter, thereby capturing the flexible solar array. The astronauts then disconnect the on-orbit rapid disassembly and assembly electrical connection device 3 and the on-orbit rapid disassembly and assembly mechanical device 2 in sequence. Finally, the extravehicular robotic arm moves the flexible solar array from the installation point to the nearby extravehicular temporary parking point 1, realizing the removal of the spare components of the flexible solar array.

[0042] The installation steps for flexible solar cell array spare parts are as follows:

[0043] In the initial state, the flexible solar array spare parts are placed at the temporary parking point 2 outside the cabin. An adapter is installed at the adapter capture interface assembly 5, and the external robotic arm captures the adapter, thereby capturing the flexible solar array. The external robotic arm moves the flexible solar array from the temporary parking point 2 outside the cabin to the vicinity of the installation point. The astronaut holds the maintenance handle 6 of the flexible solar array and aligns and locks its on-orbit quick disassembly and assembly mechanical device 2. The on-orbit quick disassembly and assembly mechanical device 2 and the on-orbit quick disassembly and assembly electrical connection device 3 are connected and fixed in sequence to realize the installation of the flexible solar array spare parts.

[0044] The contents not described in detail in this specification are prior art known to those skilled in the art. It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within the present invention.

Claims

1. An on-orbit replaceable flexible solar cell array, characterized in that, It includes the main body structure, on-orbit quick assembly / disassembly mechanical device, on-orbit quick assembly / disassembly electrical connection device, auxiliary clamping interface assembly, and adapter capture interface assembly; The on-orbit rapid assembly / disassembly mechanical device is connected to the main body structure to achieve mechanical on-orbit connection and fixation of the flexible solar cell array; the on-orbit rapid assembly / disassembly electrical connection device is connected to the main body structure to achieve on-orbit electrical connection of the flexible solar cell array; the auxiliary clamping interface assembly is connected to the main body structure to clamp the flexible solar cell array into a whole on-orbit; the adapter capture interface assembly is connected to the main body structure to connect the flexible solar cell array to the robotic arm. It also includes a maintenance handrail; the maintenance handrail is connected to the main structure of the body and is used for hand-held operation by astronauts; The on-orbit rapid disassembly and assembly mechanical device includes an M8 non-detachable fastening device, a pressure plate, a torsion spring, and a wedge-shaped component; The wedge-shaped component is connected to the main structure of the main body to achieve connection and fixation of the main structure of the main body; the pressure plate is connected to the second body to press the wedge-shaped component tightly, and the torsion spring is connected to the second body to press the pressure plate against the second body; the M8 non-disengaging fastening device is connected to the pressure plate to achieve connection and fixation between the pressure plate and the wedge-shaped component; the on-orbit quick disassembly and assembly mechanical device achieves the mechanical connection between the flexible solar cell array and the second body. The on-orbit quick-release electrical connection device includes an extravehicular astronaut-operable socket and an extravehicular astronaut-operable plug. The extravehicular astronaut-operable socket is connected to the main structure of the main body, the extravehicular astronaut-operable plug is connected to the second body, and the extravehicular astronaut-operable socket is connected to the extravehicular astronaut-operable plug, thereby realizing the electrical connection between the flexible solar cell array and the second body. The adapter capture interface assembly includes a threaded interface, a third interface component, and a fourth interface component; after the adapter is guided and locked through the third and fourth interface components, the adapter is connected and fixed using the threaded interface.

2. The on-orbit replaceable flexible solar cell array as described in claim 1, characterized in that, The auxiliary clamping interface assembly includes a first interface component and a second interface component; The auxiliary pressing interface assembly is provided with 4 groups, and the flexible solar cell array is connected into a whole through the first interface component and the second interface component in each group.

3. The on-orbit replaceable flexible solar cell array as described in claim 1, characterized in that, The maintenance handrail includes a handrail, a first support, and a second support; Both the first and second supports are connected to the main structure of the body, and the handrail is connected to the first and second supports.

4. An on-orbit replacement method for an on-orbit replaceable flexible solar cell array, applied to an on-orbit replaceable flexible solar cell array as described in any one of claims 1 to 3, characterized in that, This includes the removal of faulty components from the flexible solar cell array. In the initial state, the flexible solar array is connected by an on-orbit quick-release mechanical device and an on-orbit quick-release electrical connection device. First, the astronauts use the auxiliary clamping interface assembly to fix the flexible solar array into a whole; then, the adapter is installed at the adapter capture interface assembly, and the extravehicular robotic arm captures the adapter, thereby capturing the flexible solar array. The astronauts sequentially disconnected the on-orbit rapid assembly and disassembly electrical connection device and the on-orbit rapid assembly and disassembly mechanical device; finally, the extravehicular robotic arm moved the flexible solar array from the installation point to the nearby temporary extravehicular parking point 1, realizing the removal of the flexible solar array spare parts. This also includes the installation of spare parts for flexible solar cell arrays: In the initial state, the flexible solar cell array spare parts are placed at the temporary parking point outside the cabin. The adapter is installed at the adapter capture interface assembly, and the external robotic arm captures the adapter, thereby capturing the flexible solar cell array. The extravehicular robotic arm moves the flexible solar array from its temporary parking point to the vicinity of the installation point; the astronauts hold the maintenance handles of the flexible solar array, align and lock its on-orbit rapid disassembly and assembly mechanical device, and then connect and fix the on-orbit rapid disassembly and assembly mechanical device and the on-orbit rapid disassembly and assembly electrical connection device in sequence to realize the installation of spare parts for the flexible solar array.

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