A space-use repeatable expandable and retractable structure forming device and forming method

Abstract

The present invention provides a space-use retractable structure forming device, comprising a stamping module, a solution pool, a first buffer device, a second buffer device, a first pressure device, a second pressure device and a protective liquid; the stamping module is located above the solution pool, and is used to press the stamped part into the solution pool; the solution pool can be retracted and expanded reciprocatingly, and has a heating function, and is filled with a protective liquid; the first pressure device and the second pressure device are flat pressure structures, respectively arranged on both sides of the solution pool; the first buffer device and the second buffer device are respectively located between the first pressure device and the solution pool, and between the second buffer device and the solution pool. The retractable structure forming method of the present invention has a simple structure, an easy-to-control forming process, and good protection performance, which improves the reliability of solar cell array power supply transmission products.

Description

Technical Field

[0001] The present invention relates to the technical field of power transmission of space solar cell arrays, and in particular to a device and method for forming a space-use repeatable expandable and retractable structure. Background Art

[0002] Flexible cable is a transmission line widely used in aerospace, automobile and other fields. It can be used to transmit power and signals. With the development of aerospace technology, the demand for power supply is getting higher and higher, reaching hundreds of kilowatts or even higher power. The area of ​​the solar cell wing is hundreds of square meters or even thousands of square meters. Therefore, the structure of the solar cell wing and its power transmission method have also changed. For example, a certain space mission in my country uses a flexible solar cell wing and a flexible cable transmission method, which has the characteristics of light weight, small folding envelope, and repeatable expansion and contraction. At the same time, the power transmission structure for space can work for a long time in a space environment, such as working for 10 -4 Vacuum environment below Pa, temperature difference environment of ±100℃ or even higher, 10 22 aton / cm 2 The above atomic oxygen environment puts higher requirements on the space environment performance and repeated expansion and contraction performance of the cable.

[0003] After investigation, Xie Zongwu et al.'s "A Review of Space Solar Cell Array Technology" elaborated on the technical development direction of solar arrays, which will be towards lightweight (flexible solar array) technology in the future. Among them, AEC-Able used the FAST articulated deployment structure for application on the International Space Station. The article did not provide a detailed description of the solar wing power transmission line.

[0004] Liu Fang et al.’s “Calculation and Analysis of In-Orbit Loads on Flexible Battery Wings of Space Stations” conducted a mechanical analysis of large flexible solar arrays and cables. However, the paper did not analyze the repeatable deployment and retraction structure of the flexible battery wings.

[0005] Zhu Yaxiong et al. proposed a flexible cable repetitive retraction torque test device in "A space-based flat inter-board cable expansion and contraction torque test device" to standardize the mechanical properties of the expansion structure. The paper did not study the repetitive expansion and contraction function of the power transmission part.

[0006] In order to solve the problem of repeatable deployment and retraction technology for power transmission part for space and space environment protection, the industry urgently needs a method for forming a repeatable deployable and retractable structure for space use. Summary of the invention

[0007] The technical problem to be solved by the present invention is: in order to effectively solve the problem that the power supply and transmission part of a space solar cell array has the function of repeated expansion and contraction and realize high-reliability connection, the present invention provides a space-use repeatable expansion and contraction structure forming device and forming method, which is suitable for the forming of a spacecraft flexible cable repeatable expansion and contraction structure to realize the repeatable expansion and contraction function of the power supply and transmission part of a space solar cell array.

[0008] The technical solution adopted by the present invention is: a space-use retractable structure forming device, comprising a stamping module, a solution pool, a first buffer device, a second buffer device, a first pressure device, a second pressure device and a protective liquid;

[0009] The stamping module is located above the solution pool and is used to press the stamped part into the solution pool;

[0010] The solution pool can be retracted and expanded reciprocatingly, has a heating function, and is filled with protective liquid;

[0011] The first pressure device and the second pressure device are flat pressure structures, respectively arranged on both sides of the solution pool;

[0012] The first buffer device and the second buffer device are respectively located between the first pressure device and the solution pool, and between the second buffer device and the solution pool.

[0013] Furthermore, the stamping module is made of silicone rubber material, and its Shore A hardness is 40-50.

[0014] Furthermore, the heating temperature of the solution pool is controlled at 35°C to 70°C.

[0015] Furthermore, the first buffer device and the second buffer device are pneumatic buffer or liquid buffer structures, which cooperate with the first pressure device and the second pressure device to uniformly apply pressure of 0 to 15 kPa.

[0016] Furthermore, the protective liquid is a silicone rubber material, which is coated on the material surface at a set temperature and pressure, has a temperature resistance range of better than ±100°C, and has atomic oxygen and ultraviolet radiation protection properties.

[0017] A method for forming a space-use repeatable expandable and retractable structure, comprising:

[0018] Place the workpiece to be stamped on the solution pool, and place the stamping module on the workpiece to be stamped;

[0019] Control the stamping module to move from top to bottom, drive the parts to be stamped to move into the solution pool, so that the protective liquid in the solution pool completely covers the parts to be stamped;

[0020] Control the first pressure device and the second pressure device to move toward the middle, drive the first buffer device and the second buffer device to apply pressure to the outer wall of the solution pool, and maintain the pressure for 1min to 5min, so that the protective liquid further infiltrates the inner and outer surfaces of the part to be stamped;

[0021] The first pressure device and the second pressure device are controlled to move to both sides, and the stamping module is controlled to move upward to take out the sample and complete the forming of the part to be stamped.

[0022] Furthermore, the stamping module is made of silicone rubber material, and its Shore A hardness is 40-50.

[0023] Furthermore, the solution pool controls the temperature of the protection solution at 35°C to 70°C.

[0024] Furthermore, the first buffer device and the second buffer device are pneumatic buffer or liquid buffer structures, which cooperate with the first pressure device and the second pressure device to uniformly apply pressure of 0 to 15 kPa.

[0025] Furthermore, the protective liquid is a silicone rubber material, which is coated on the material surface at a set temperature and pressure, has a temperature resistance range of -100°C to 100°C, and has atomic oxygen and ultraviolet radiation protection properties.

[0026] The advantages of the present invention compared with the prior art are:

[0027] The present invention is to effectively solve the problem that the power transmission part of a space solar cell array has the function of being repeatedly expandable and retractable and realize highly reliable connection, and provides a method for forming a repeatable expandable and retractable structure for space. The existing deficiencies are solved through the design of a new structure forming process, which is beneficial to the development of high-power, lightweight and flexible solar cell array technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0029] Figure 1 A composition diagram of a repeatable unfoldable structure forming device provided by the present invention;

[0030] Figure 2 A schematic diagram of the pressure forming principle of the method for forming a repeatable expandable and retractable structure provided in an embodiment of the present invention;

[0031] Figure 3 A state after forming of a repeatable expandable and retractable structure is provided in an embodiment of the invention. DETAILED DESCRIPTION

[0032] The present method will be described in more detail below with reference to the accompanying drawings showing embodiments of the invention. However, the present invention may be implemented in many different forms and should not be construed as being limited to the embodiments set forth herein. Rather, these embodiments are set forth in order to achieve a full and complete disclosure and to enable those skilled in the art to fully understand the scope of the present invention. In these drawings, the sizes and relative sizes of layers and regions may be exaggerated for clarity.

[0033] The invention will now be further described by describing in detail the preferred embodiments of the present invention.

[0034] like Figure 1 As shown, the repeatable expandable and retractable structure forming device includes a stamping module 1, a solution pool 3, a first buffer device 4-1, a second buffer device 4-2, a first pressure device 5-1, a second pressure device 5-2 and a protective liquid 6; the stamping module 1 is located above the solution pool 3, and is used to press the stamped part 2 into the solution pool 3; the solution pool 3 can be retracted and expanded reciprocatingly, and has a heating function, and is filled with a protective liquid 6; the first pressure device 5-1 and the second pressure device 5-2 are flat pressure structures, which are respectively arranged on both sides of the solution pool 3; the first buffer device 4-1 and the second buffer device 4-2 are respectively located between the first pressure device 5-1 and the solution pool 3, and between the second buffer device 4-2 and the solution pool 3.

[0035] The stamping module 1 is an elastic material with a certain elasticity; the part to be stamped 2 is a flexible material with a flat structure; the solution pool 3 has greater elasticity, can be reciprocated and expanded, and has a heating function; the first buffer device 4-1 and the second buffer device 4-2 are pneumatic buffer or liquid buffer structures; the first pressure device 5-1 and the second pressure device 5-2 are flat pressure structures; the protective liquid 6 has good adaptability to the space environment, a temperature resistance range wider than -100°C to 100°C, and has protection properties such as atomic oxygen and ultraviolet radiation.

[0036] This method of repeatedly expanding and contracting a structure has a simple structure, an easily controllable forming process, and good protection performance, thereby improving the reliability of solar cell array power supply transmission products.

[0037] like Figure 2 As shown, a method for forming a space-use repeatable expandable and retractable structure, the specific working steps of the method are as follows:

[0038] Step 1: Place the workpiece 2 to be stamped on the solution pool 3, and place the stamping module 1 on the workpiece 2 to be stamped; the stamping module 1 is made of silicone rubber material, has a certain elasticity, and its Shore A hardness is 40-50;

[0039] Step 2: The stamping module 1 moves from top to bottom, driving the workpiece 2 to be stamped to move into the solution pool 3, and the protective liquid 6 in the solution pool 3 completely covers the workpiece 2 to be stamped; the solution pool 3 has a heating function, which can realize the temperature control of the protective liquid 6 at 35°C to 70°C; the protective liquid 6 is a silicone rubber material, which can be coated on the material surface under a certain temperature and pressure;

[0040] Step 3: The first pressure device 5-1 and the second pressure device 5-2 move toward the middle, driving the first buffer device 4-1 and the second buffer device 4-2 to apply pressure to the outer wall of the solution pool, maintaining the pressure for 1min to 5min, and the protective liquid 6 further infiltrates the inner and outer surfaces of the punched part 2; the first buffer device 4-1 and the second buffer device 4-2 are pneumatic buffer or liquid buffer structures, which can achieve uniform pressure of 0 to 15kPa together with the first pressure device 5-1 and the second pressure device 5-2;

[0041] Step 4: The first pressure device 5-1 and the second pressure device 5-2 move to both sides, and then the stamping module 1 moves upward to take out the sample, and wait for the stamping part 2 to complete the unfolding of the "herringbone" structure. Figure 3 As shown, the "herringbone" structure has good fatigue performance, and the protective liquid 6 coated on its surface has good adaptability to space environment.

[0042] Experiments have proved that the present invention realizes the pressing and forming of the part to be stamped 2 by the up and down movement of the stamping module 1 and the reciprocating movement of the first pressure device 5-1 and the second pressure device 5-2, and at the same time, the protective liquid 6 is applied to the inner and outer surfaces of the part to be stamped 2 to realize the surface protection of the part to be stamped 2 and the repeated expansion and contraction structure forming. This structure effectively solves the problem of the deployment structure connection of the space solar wing power supply transmission component and its space environment adaptability protection design. It has been verified that the "herringbone" expandable structure can withstand 100,000 times of ±10mm structural fatigue, meet 100,000 times of ±100℃ thermal cycle life assessment, and meet 10 years of atomic oxygen, ultraviolet radiation, ionizing radiation and other space environment adaptability requirements, which promotes the engineering application progress of solar cell array power supply transmission products.

[0043] The device and method for repeatedly expanding and contracting a structure provided by the present invention will provide a guarantee for the engineering application of solar cell array power supply transmission products and improve the application level of my country's space solar cell arrays.

[0044] The contents not described in detail in this specification belong to the prior art known to those skilled in the art. It is obvious 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 present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-restrictive, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention. Any figure mark in the claims should not be regarded as limiting the claims involved.

Claims

1. A space-use retractable structure forming device, characterized in that: It comprises a stamping module (1), a solution pool (3), a first buffer device (4-1), a second buffer device (4-2), a first pressure device (5-1), a second pressure device (5-2) and a protective liquid (6); The punching module (1) is located above the solution pool (3) and is used to press the punched part (2) into the solution pool (3); The solution pool (3) can be retracted and expanded reciprocatingly and has a heating function, and is filled with a protective liquid (6); The first pressure device (5-1) and the second pressure device (5-2) are flat pressure structures, which are respectively arranged on both sides of the solution pool (3); The first buffer device (4-1) and the second buffer device (4-2) are respectively located between the first pressure device (5-1) and the solution pool (3), and between the second buffer device (4-2) and the solution pool (3).

2. A space-use retractable structure forming device according to claim 1, characterized in that: The punching module (1) is made of silicone rubber material, and its Shore A hardness is 40-50.

3. The space-use retractable structure forming device according to claim 1, characterized in that: The heating temperature of the solution pool (3) is controlled at 35°C to 70°C.

4. The space-use retractable structure forming device according to claim 1, characterized in that: The first buffer device (4-1) and the second buffer device (4-2) are pneumatic buffer or liquid buffer structures, and cooperate with the first pressure device (5-1) and the second pressure device (5-2) to uniformly apply pressure of 0 to 15 kPa.

5. The space-use retractable structure forming device according to claim 1, characterized in that: The protective liquid (6) is a silicone rubber material, which is coated on the material surface at a set temperature and pressure, has a temperature resistance range of -100°C to 100°C, and has atomic oxygen and ultraviolet radiation protection properties.

6. A method for forming a space-use retractable structure, characterized in that: include: Placing the workpiece to be stamped (2) above the solution pool (3), and placing the stamping module (1) on the workpiece to be stamped (2); Controlling the stamping module (1) to move from top to bottom, driving the workpiece to be stamped (2) to move into the solution pool (3), so that the protective liquid (6) in the solution pool (3) completely covers the workpiece to be stamped (2); Controlling the first pressure-applying device (5-1) and the second pressure-applying device (5-2) to move toward the middle, driving the first buffer device (4-1) and the second buffer device (4-2) to apply pressure to the outer wall of the solution pool (3), maintaining the pressure for 1 to 5 minutes, so that the protective liquid (6) further infiltrates the inner and outer surfaces of the part to be stamped (2); The first pressure device (5-1) and the second pressure device (5-2) are controlled to move to both sides, and the stamping module (1) is controlled to move upward to take out the sample and complete the forming of the part to be stamped (2).

7. A method for forming a space-use retractable structure according to claim 6, characterized in that: The punching module (1) is made of silicone rubber material, and its Shore A hardness is 40-50.

8. The method for forming a space-use retractable structure according to claim 6, characterized in that: The solution pool (3) controls the temperature of the protective solution (6) at 35°C to 70°C.

9. The method for forming a space-use retractable structure according to claim 6, characterized in that: The first buffer device (4-1) and the second buffer device (4-2) are pneumatic buffer or liquid buffer structures, and cooperate with the first pressure device (5-1) and the second pressure device (5-2) to uniformly apply pressure of 0 to 15 kPa.

10. The method for forming a space-use retractable structure according to claim 6, characterized in that: The protective liquid (6) is a silicone rubber material, which is coated on the material surface at a set temperature and pressure, has a temperature resistance range of -100°C to 100°C, and has atomic oxygen and ultraviolet radiation protection properties.

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