Solar wing quick-mounting method suitable for flexible hinge connection of micro-satellite and solar wing

Abstract

The application provides a solar wing quick mounting method and a solar wing suitable for flexible hinge connection of a micro-satellite, and the solar wing quick mounting method comprises the following steps: step 1, the hinge is pre-formed to the required angle through a hinge forming tool, and a hinge positioning tool is installed on the formed hinge joint through fasteners; step 2, the plate sleeve of the solar wing base plate is respectively installed on the upper and lower surfaces of the through hole of the locking device of the inner solar wing base plate, the middle solar wing base plate and the outer solar wing base plate, and the fastener of the locking plate sleeve is measured after being positioned through a pin; step 3, the outer solar wing base plate and the middle solar wing base plate are installed above the solar wing simulation wall through a positioning pin and a limiting column, and then the inner solar wing base plate with the SADA connecting frame installed in advance is installed above the middle solar wing base plate through the positioning pin. The beneficial effects of the application are that the flexible hinge is pre-formed, the hinge embedded part of the solar wing base plate is installed, and the line marking positioning ensures the installation position precision of the hinge.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace, in particular to a solar wing quick mounting method suitable for flexible hinge connection of microsatellites and a solar wing. BACKGROUND

[0002] Under the traditional satellite scientific research and production mode, the microsatellite adopts a spring hinge or a leaf spring as a driving component for solar wing unfolding. Neither the spring hinge nor the leaf spring can bear longitudinal shear force. Therefore, in order to protect the solar wing driving component from damage during unfolding test, light test, solar wing installation and solar wing compression, the assembly and test work need to be carried out under the condition that the solar wing is hung on the solar wing unfolding frame. This assembly method can ensure sufficient assembly accuracy and safety of the solar wing, but at the same time, it has the shortcomings of long time-consuming processes such as frequent satellite attitude adjustment, frequent distance adjustment of the whole solar wing assembly, simulation wall attitude adjustment, position adjustment of the simulation wall and the satellite, satellite reverse rotation, etc. The solar wing assembly process has the shortcomings of complexity and long time consumption. SUMMARY

[0003] The present application provides a solar wing quick mounting method suitable for flexible hinge connection of microsatellites, which solves the problems of frequent satellite attitude adjustment and long time consumption in the installation of the existing microsatellite solar wing. The present application provides a solar wing quick mounting method suitable for flexible hinge connection of microsatellites, which comprises the following steps:

[0004] Step 1, the hinge is pre-formed to the required angle by a hinge forming tool, and a hinge positioning tool is installed on the hinge joint of the formed hinge with a fastener to ensure the bending angle of the hinge.

[0005] Step 2, the plate sleeve of the solar wing base plate is installed on the upper and lower surfaces of the through hole of the locking device of the inner solar wing base plate, the middle solar wing base plate and the outer solar wing base plate, respectively, and the fastener of the locking plate sleeve is measured after positioning by the pin.

[0006] Step 3, the outer solar wing base plate and the middle solar wing base plate are installed above the solar wing simulation wall through the positioning pin and the limiting column, the middle solar wing base plate is located above the outer solar wing base plate, then the inner solar wing base plate with the SADA connecting frame installed in advance is installed above the middle solar wing base plate through the positioning pin, and the inner solar wing base plate, the middle solar wing base plate and the outer solar wing base plate are connected by the wires of the electrical connector.

[0007] Step 4, the locking nut and the washer are installed on the positioning pin and the limiting column, and the force of the positioning pin and the limiting column of the three solar wing base plates is measured through the washer and the locking nut.

[0008] Step 5, install the first solar wing pressing tool and handle on the side edges of the outer solar wing substrate and the intermediate solar wing substrate, and install the second solar wing pressing tool on the side edges of the intermediate solar wing substrate and the inner solar wing substrate.

[0009] Step 6, install the preformed hinge treated in step 1 on the side edges of the installed outer solar wing substrate and intermediate solar wing substrate and the intermediate solar wing substrate and inner solar wing substrate respectively.

[0010] Step 7, remove the locking nuts and washers, and take out the fixed solar wing from the solar wing simulation wall and install it as a whole to the whole satellite structure.

[0011] As a further improvement of the present application, in step 3, the electrical connector wires led out from the outer solar wing substrate and the intermediate solar wing substrate are tied and fixed at the cable support of the intermediate solar wing substrate.

[0012] As a further improvement of the present application, the preformed hinge includes a first preformed hinge and a second preformed hinge, in step 6, one end of the first preformed hinge is installed at the hinge installation mark position of the outer solar wing substrate, the other end of the first preformed hinge is installed at one of the hinge installation mark positions of the intermediate solar wing substrate, one end of the second preformed hinge is installed at the other hinge installation mark position of the intermediate solar wing substrate, and the other end of the second preformed hinge is installed at the hinge installation mark position of the inner solar wing substrate.

[0013] The present application also discloses a solar wing suitable for flexible hinge connection of a micro-satellite, which comprises an outer solar wing substrate, an intermediate solar wing substrate installed above the outer solar wing substrate and movably connected with the outer solar wing substrate, and an inner solar wing substrate installed above the intermediate solar wing substrate and movably connected with the intermediate solar wing substrate.

[0014] As a further improvement of the present application, the solar wing comprises a preformed hinge, the preformed hinge includes a first preformed hinge and a second preformed hinge, the outer solar wing substrate and the intermediate solar wing substrate are connected through the first preformed hinge, and the intermediate solar wing substrate and the inner solar wing substrate are connected through the second preformed hinge.

[0015] As a further improvement of the present application, the preformed hinge includes a first fastener, a second fastener, and a connecting assembly, one end of the connecting assembly is connected with the first fastener, the other end of the connecting assembly is connected with the second fastener, and a hinge positioning tool is installed between the first fastener and the second fastener.

[0016] As a further improvement of the present application, the solar wing further comprises a SADA connecting frame installed on the inner solar wing base plate, which is used to connect the inner solar wing base plate with the whole satellite structure.

[0017] As a further improvement of the present application, the solar wing further comprises a cable support installed on the middle solar wing base plate, which is used to install the electrical connectors led out by the adjacent two solar wing base plates and to plug the electrical connectors on the cable support.

[0018] As a further improvement of the present application, the solar wing further comprises a first solar wing pressing tool and a second solar wing pressing tool, the first solar wing pressing tool is installed on the side edge of the outer solar wing base plate and the middle solar wing base plate, and the second solar wing pressing tool is installed on the side edge of the middle solar wing base plate and the inner solar wing base plate.

[0019] As a further improvement of the present application, the solar wing further comprises a handle, which connects the outer solar wing base plate and the middle solar wing base plate.

[0020] As a further improvement of the present application, the solar wing further comprises a plate sleeve, which is installed on the upper and lower surfaces of the through hole of the locking device of the inner solar wing base plate, the middle solar wing base plate and the outer solar wing base plate.

[0021] As a further improvement of the present application, a plurality of mounting holes for placing the positioning device are arranged on the inner solar wing base plate, the middle solar wing base plate and the outer solar wing base plate respectively.

[0022] The present application has the following advantages: 1. The present application adopts flexible hinge pre-forming, solar wing base plate installation hinge embedded part and line marking positioning to ensure the installation position accuracy of the hinge; 2. The assembly method of connecting the solar wing base plate as an auxiliary process to assemble into a component in advance shortens the time of solar wing hanging and satellite frequent attitude adjustment, and improves the assembly efficiency; 3. The present application solves the problems of long time consumption of solar wing assembly in batch production of microsatellites, long-term occupation of solar wing unfolding frame, two-axis turntable and other equipment, and waiting for solar wing unfolding frame in solar wing unfolding test. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 is the axial view of the solar wing of the present application;

[0024] Figure 2 is the front view of the solar wing of the present application;

[0025] Figure 3 is the pre-formed hinge structure diagram of the solar wing of the present application;

[0026] Figure 4is a side view of a solar wing of the present application;

[0027] Figure 5 is a flow chart of a solar wing mounting process of the present application. DETAILED DESCRIPTION

[0028] The solar wing quick mounting method of the present application considers that a series of solar wing components such as solar wings, SADA connecting frames 5, compression release devices, plate sleeves 23, leaf spring / spring hinges, etc. are efficiently and quickly assembled at a certain work station, and then the assembly is rigidly fixed to a satellite body through screwing, so as to achieve the effect of quick mounting of the solar wing and help the goal of mass production of satellites.

[0029] The solar wing quick mounting method of the present application replaces the solar wing mounting from the main line process to the auxiliary line process, and saves in the form of components, so as to solve the problem that the satellite solar wing mounting needs to occupy the solar wing unfolding frame and the two-axis turntable device for a long time, and other models of solar wing mounting and unfolding need to wait in line. The production bottleneck of solar wing mounting is eliminated, and the production efficiency of satellites is greatly improved.

[0030] The device and product involved in the solar wing quick mounting method of the present application are hinge forming tooling 8, hinge positioning tooling 10, flexible hinge (leaf spring / spring hinge), three solar wing base plates (inner solar wing base plate 1, middle solar wing base plate 2 and outer solar wing base plate 3), plate sleeve 23, solar wing simulation wall 4 (two positioning pins 11 and two limiting columns 12 are respectively installed on the upper surface), cable support 14, SADA connecting frame 5, solar wing compression tooling 15, handle 7, through the pre-forming of the flexible hinge and the assembly of the solar wing simulation wall 4 and the solar wing base plate, the assembly of the solar wing is finally realized.

[0031] As shown in Figure 5 The solar wing quick mounting method suitable for flexible hinge connection of a micro-satellite is disclosed, which comprises the following steps:

[0032] Step 1, the flexible hinge is pre-formed to the required angle through the hinge forming tooling 8, and the hinge positioning tooling 10 is installed at the hinge joint of the pre-formed hinge to ensure the bending angle of the hinge.

[0033] Step 2, the solar wing base plate is erected on the anti-static table top, the plate sleeve 23 of the upper solar wing base plate is respectively installed on the upper surface and the lower surface of the through hole of the locking device of the single solar wing base plate (inner solar wing base plate 1 or middle solar wing base plate 2 or outer solar wing base plate 3), and the fastener of the locking plate sleeve is measured after positioning by the pin (fastener force measurement: the torque wrench is used to measure the fastener torque).

[0034] Step 3, the solar wing simulation wall 4 is horizontally placed on the anti-static table, the outer solar wing base plate 3 and the middle solar wing base plate 2 are installed above the solar wing simulation wall 4 through the positioning pin 11 and the limiting column 12, the middle solar wing base plate 2 is located above the outer solar wing base plate 3, the electric connector wire led out of the outer solar wing base plate 3 is fixed by binding on the cable support 14 and the back of the middle solar wing base plate 2, and the wire is led out from the hinge installation side of the middle solar wing base plate 2 and the inner solar wing base plate 1; then the inner solar wing base plate 1 with the SADA connecting frame 5 installed in advance is installed horizontally on the left side of the middle solar wing base plate 2 through the positioning pin 11, and the wire led out of the middle solar wing base plate 2 is fixed by binding on the middle solar wing and the cable support 14 and the back of the inner solar wing base plate 1, and the electric connector wires of the inner solar wing base plate 1, the middle solar wing base plate 2 and the outer solar wing base plate 3 are uniformly led out from the direction of the SADA connecting frame 5.

[0035] Step 4, the locking nut and the gasket are installed on the positioning pin 11 and the limiting column 12, the force of the positioning pin 11 and the limiting column 12 of the three solar wing base plates is measured through the gasket and the locking nut (the force of the positioning pin 11 and the limiting column 12 is measured by tightening the locking nut), so as to ensure the same compression allowance between the solar wing base plates. The same compression allowance refers to measuring the same torque of each nut, and the spacing between the base plates is the same after locking.

[0036] Step 5, the first solar wing pressing tool 6 and the handle 7 are installed on the side edges of the outer solar wing base plate 3 and the middle solar wing base plate 2, and the second solar wing pressing tool 15 is installed on the side edges of the middle solar wing base plate 2 and the inner solar wing base plate 1. The solar wing pressing tool is installed to prevent the position between the upper and lower solar wing base plates from moving.

[0037] Step 6, the preformed hinge treated in the step 1 is respectively installed on the side edges of the outer solar wing base plate 3 and the middle solar wing base plate 2 and the middle solar wing base plate 2 and the inner solar wing base plate 1.

[0038] The preformed hinge includes a first preformed hinge 9 and a second preformed hinge 13.

[0039] In the step 6, one end of the first preformed hinge 9 is installed at the hinge installation marking position of the outer solar wing base plate 3, the force of the fastener is measured, the hinge positioning tool 10 on the first preformed hinge is slightly loosened, the other end of the first preformed hinge 9 is aligned with the hinge installation marking position of the middle solar wing base plate 2, and the force of the fastener is measured; the second preformed hinge 13 between the middle solar wing base plate and the inner solar wing base plate is installed in the same way, that is, one end of the second preformed hinge 13 is installed at the other hinge installation marking position of the middle solar wing base plate 2, the force of the fastener is measured, the hinge positioning tool 10 on the second preformed hinge 13 is slightly loosened, the other end of the second preformed hinge 13 is aligned with the hinge installation marking position of the inner solar wing base plate 1, and the force of the fastener is measured. The force of the fastener is measured: the fastener (screw) is coated with thread glue, and the torque is hit.

[0040] After the preformed hinge is installed, the hinge positioning tool 10 is not needed; the hinge positioning tool 10 is slightly loosened during installation to align the screw holes when the preformed hinge is installed on the four fasteners of the side locking hinge of the solar wing base plate, so that there is no forced installation when the preformed hinge is installed.

[0041] In step 7, the locking nuts 19 and washers of the positioning pins and limiting columns for fixing the solar wing base plate are removed, the fixed solar wing is taken out from the solar wing simulation wall 4, and then the fixed solar wing is installed as a whole to the whole satellite structure.

[0042] As shown in Figure 1 The application also discloses a solar wing suitable for flexible hinge connection of a microsatellite, which comprises an outer solar wing base plate 3, a middle solar wing base plate 2 installed above the outer solar wing base plate 3 and movably connected with the outer solar wing base plate 3, and an inner solar wing base plate 1 installed above the middle solar wing base plate 2 and movably connected with the middle solar wing base plate 2.

[0043] The solar wing comprises a preformed hinge, that is, the flexible hinge is preformed to a required angle by a hinge forming tool 8, and a hinge positioning tool 10 is installed on the hinge joint by a fastener to ensure the bending angle of the hinge. The side edges of the outer solar wing base plate 3, the middle solar wing base plate 2 and the inner solar wing base plate 1 are respectively provided with a plurality of hinge embedded parts 19, which are marked with hinge installation marking positions 22 for ensuring the installation position precision of the preformed hinge. One hinge embedded part 19 (the hinge embedded part 19 is an aluminum alloy block with an installation hole, which is glued to the solar wing base plate) is provided for each solar wing base plate corresponding to one hinge, and the hinge embedded part is embedded in advance when the solar wing base plate is manufactured.

[0044] The preformed hinge includes a first preformed hinge 9, a second preformed hinge 13, the outer solar wing base plate 3 is connected with the intermediate solar wing base plate 2 through the first preformed hinge 9, and the intermediate solar wing base plate 2 is connected with the inner solar wing base plate 1 through the second preformed hinge 13.

[0045] As shown in Figure 4 , the first preformed hinge 9 is two in number, one end of one first preformed hinge 9 is installed at one hinge installation marking line position on the side edge of the outer solar wing base plate 3, and the other end is installed at one hinge installation marking line position on the side edge of the intermediate solar wing base plate 2, one end of the other first preformed hinge 9 is installed at another hinge installation marking line position on the side edge of the outer solar wing base plate 3, and the other end is installed at another hinge installation marking line position on the intermediate solar wing base plate 2. The second preformed hinge 13 is two in number, one end of one second preformed hinge 13 is installed at one hinge installation marking line position on the other side of the intermediate solar wing base plate 2, and the other end is installed at one hinge installation marking line position on one side of the inner solar wing base plate 1, one end of the other second preformed hinge 13 is installed at another hinge installation marking line position on the other side of the intermediate solar wing base plate 2, and the other end is installed at another hinge installation marking line position on one side of the inner solar wing base plate 1.

[0046] As shown in Figure 3 , the preformed hinge includes a first fastener 16, a second fastener 17, and a connecting assembly 18, one end of the connecting assembly 18 is connected with the first fastener 16, the other end of the connecting assembly 18 is connected with the second fastener 17, and a hinge positioning tool 10 is installed between the first fastener 16 and the second fastener 17.

[0047] The first fastener 16 and the second fastener 17 are provided with mounting holes 21 at the upper and lower ends for fixing the hinge positioning tool 10, and a plurality of through holes are respectively provided on the first fastener 16 and the second fastener 17.

[0048] The solar wing further includes an SADA connecting frame 5 installed on the side edge of the inner solar wing base plate 1, which is used to connect the inner solar wing base plate 1 with the whole satellite structure.

[0049] The solar wing further includes a cable support 14 installed on the side edge of the intermediate solar wing base plate 2, which is used to install two adjacent solar wing base plate leading electrical connectors and perform electrical connector plugging on the cable support 14. The intermediate solar wing base plate 2 cable support can plug the electrical connector connected between the outer solar wing base plate 3 and the intermediate solar wing base plate 2, and the inner solar wing base plate 1 cable support can plug the electrical connector leading from the satellite.

[0050] The solar wing further comprises a first solar wing pressing tool 6 and a second solar wing pressing tool 15, the first solar wing pressing tool 6 is installed on the side edge of the outer solar wing substrate 3 and the intermediate solar wing substrate 2, and the second solar wing pressing tool 15 is installed on the side edge of the intermediate solar wing substrate 2 and the inner solar wing substrate 1, so as to prevent displacement of the outer solar wing substrate 3 and the intermediate solar wing substrate 2.

[0051] The first solar wing pressing tool 6 and the second solar wing pressing tool 15 are collectively referred to as pressing tools, the pressing tools are used for temporarily fixing the solar wing substrates during assembly of the solar wing assembly, so as to prevent the solar wing from moving and ensure the relative position relationship between the solar wing substrates, and the pressing tools are removed after the solar wing assembly is installed as a whole on the satellite structure.

[0052] The first solar wing pressing tool 6 is four in number, and two of the first solar wing pressing tools 6 are respectively installed on the upper end and the lower end of the outer solar wing substrate 3 and the intermediate solar wing substrate 2, the second solar wing pressing tool 15 is two in number, and the two second solar wing pressing tools 15 are respectively installed on the intermediate solar wing substrate 2 and the inner solar wing substrate 1 on the side of the second preformed hinge 13.

[0053] The solar wing further comprises two handles 7, one of the handles 7 is respectively installed on the upper end and the lower end of the outer solar wing substrate 3 and the intermediate solar wing substrate 2.

[0054] The solar wing further comprises a plate sleeve 23, the plate sleeve 23 is respectively installed on the upper surface and the lower surface of the through hole of the locking device of the inner solar wing substrate 1, the intermediate solar wing substrate 2 and the outer solar wing substrate 3, and one of the plate sleeves 23 is installed on the front surface and the back surface of each solar wing substrate, so as to limit and position.

[0055] The inner solar wing substrate 1, the intermediate solar wing substrate 2 and the outer solar wing substrate 3 are respectively provided with a plurality of mounting holes for placing a positioning device, and the positioning device comprises a positioning pin 11 and a limiting column 12.

[0056] The solar wing assembly method has the following beneficial effects: 1. The flexible hinge preform is adopted, the hinge embedded part 19 of the solar wing substrate is installed, and the line positioning is used to ensure the installation position accuracy of the hinge; 2. The solar wing substrate connection is taken as an auxiliary process and is assembled into an assembly in advance, so that the time for hanging and adjusting the attitude of the satellite is shortened, and the assembly efficiency is improved; 3. The method solves the problems that the solar wing assembly method for batch production of microsatellites is time-consuming, the solar wing deployment test needs to wait for the solar wing deployment frame, and the solar wing deployment frame and a two-axis turntable are long-term occupied.

[0057] The above is further detailed description of the present application in combination with specific preferred embodiments, and cannot be deemed as limitation of the specific implementation of the present application to these descriptions. For those skilled in the art to which the present application belongs, without departing from the concept of the present application, a number of simple deductions or substitutions can be made, and all of them shall be deemed as falling within the protection scope of the present application.

Claims

1. A quick-assembly method for solar arrays with flexible hinge connections suitable for microsatellites, characterized in that, Includes the following steps: Step 1: The flexible hinge is pre-formed to the required angle using the hinge forming fixture (8), and the hinge positioning fixture (10) is installed at the formed hinge joint using fasteners to ensure the bending angle of the hinge. Step 2: Install the solar panel sleeves (23) on the upper and lower surfaces of the through holes of the locking device on the inner solar panel substrate (1), the middle solar panel substrate (2) and the outer solar panel substrate (3). After positioning with pins, measure the force of the fasteners of the locking sleeves. Step 3: Install the outer solar panel substrate (3) and the middle solar panel substrate (2) above the solar panel simulation wall (4) using positioning pins (11) and limiting posts (12). The middle solar panel substrate (2) is located above the outer solar panel substrate (3). Then, install the inner solar panel substrate (1) with the pre-installed SADA connector (5) above the middle solar panel substrate (2) using positioning pins (11). And lead out the electrical connector wires of the inner solar panel substrate (1), the middle solar panel substrate (2) and the outer solar panel substrate (3) from the direction of the SADA connector (5). Step 4: Install locking nuts and washers on the positioning pins (11) and limiting posts (12), and measure the force on the positioning pins (11) and limiting posts (12) of the three solar panel substrates through the washers and locking nuts; Step 5: Install the first solar wing clamping fixture (6) and handle (7) on the sides of the outer solar wing substrate (3) and the middle solar wing substrate (2), and install the second solar wing clamping fixture (15) on the sides of the middle solar wing substrate (2) and the inner solar wing substrate (1). Step 6: Install the pre-formed hinges processed in Step 1 on the sides of the outer solar panel substrate (3) and the middle solar panel substrate (2), as well as on the sides of the middle solar panel substrate (2) and the inner solar panel substrate (1). Step 7: Remove the locking nut and washer, and take the fixed solar array off the solar array simulation wall (4) and install it as a whole onto the satellite structure.

2. The method for quick installation of solar panels according to claim 1, characterized in that: In step 3, the electrical connector wires leading out from the outer solar panel substrate (3) and the middle solar panel substrate (2) are tied and fixed to the cable bracket (14) of the middle solar panel substrate (2).

3. The method for quick installation of solar panels according to claim 1, characterized in that, The preformed hinge includes a first preformed hinge (9) and a second preformed hinge (13). In step 6, one end of the first preformed hinge (9) is installed at the hinge mounting line position on the outer solar panel substrate (3), and the other end of the first preformed hinge (9) is installed at one of the hinge mounting line positions on the middle solar panel substrate (2). Then, one end of the second preformed hinge (13) is installed at the other hinge mounting line position on the middle solar panel substrate (2), and the other end of the second preformed hinge (13) is installed at the hinge mounting line position on the inner solar panel substrate (1).

4. A solar array suitable for flexible hinge connection of microsatellites, employing the solar array quick-installation method according to any one of claims 1-3, characterized in that: It includes an outer solar panel substrate (3), an intermediate solar panel substrate (2) mounted above the outer solar panel substrate (3) and movably connected to the outer solar panel substrate (3), and an inner solar panel substrate (1) mounted above the intermediate solar panel substrate (2) and movably connected to the intermediate solar panel substrate (2).

5. The solar array according to claim 4, characterized in that: The solar array includes a preformed hinge, which includes a first preformed hinge (9) and a second preformed hinge (13). The outer solar array substrate (3) and the middle solar array substrate (2) are connected by the first preformed hinge (9), and the middle solar array substrate (2) and the inner solar array substrate (1) are connected by the second preformed hinge (13).

6. The solar array according to claim 5, characterized in that: The preformed hinge includes a first fastener (16), a second fastener (17), and a connecting component (18). One end of the connecting component (18) is connected to the first fastener (16), and the other end of the connecting component (18) is connected to the second fastener (17). A hinge positioning fixture (10) is installed between the first fastener (16) and the second fastener (17).

7. The solar array according to claim 4, characterized in that: The solar array also includes a SADA connector (5) mounted on the inner solar array substrate (1), the SADA connector (5) being used to connect the inner solar array substrate (1) to the entire satellite structure.

8. The solar array according to claim 4, characterized in that: The solar array also includes a cable bracket (14) mounted on the intermediate solar array substrate (2), the cable bracket (14) being used to mount electrical connectors leading out from two adjacent solar array substrates and to insert the electrical connectors on the cable bracket (14).

9. The solar array according to claim 4, characterized in that: The solar array also includes a first solar array clamping fixture (6) and a second solar array clamping fixture (15). The first solar array clamping fixture (6) is installed on the side of the outer solar array substrate (3) and the middle solar array substrate (2), and the second solar array clamping fixture (15) is installed on the side of the middle solar array substrate (2) and the inner solar array substrate (1).

10. The solar array according to claim 4, characterized in that: The solar array also includes a handle (7), through which the outer solar array substrate (3) and the middle solar array substrate (2) are connected.

11. The solar array according to claim 4, characterized in that: The solar array also includes a sleeve (23), and the sleeve (23) is installed on the upper and lower surfaces of the through holes for mounting locking devices on the inner solar array substrate (1), the middle solar array substrate (2) and the outer solar array substrate (3).

12. The solar array according to claim 4, characterized in that: The inner solar panel substrate (1), the middle solar panel substrate (2), and the outer solar panel substrate (3) are each provided with a plurality of mounting holes for placing positioning devices.

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