Spacecraft thermal test power supply switching interconnection structure and method

Abstract

The invention provides a spacecraft thermal test power supply switching interconnection structure and method. The structure comprises a thermal test switching cable; the thermal test adapter cable comprises a first thermal test adapter cable socket, a second thermal test adapter cable socket and a third thermal test adapter cable socket, and the driving mechanism is connected with the first thermal test adapter cable socket through a first on-satellite cable; the second thermal test adapter cable socket is connected with an on-satellite power supply input end electric connector socket of the power supply controller, the third thermal test adapter cable socket is sequentially connected with a second on-satellite cable and a first ground cable, the first ground cable is connected with a second ground cable through a vacuum tank wall flange, and the second ground cable is connected to the ground simulation array. According to the invention, the original on-satellite cable is utilized, the ground cable is placed in the vacuum tank, and the three power interface connectors of the in-satellite end power supply output end of the driving mechanism, the ground power supply input end of the power supply controller and the on-satellite power supply input end are switched over, so that the length of a new switching cable can be shortened, and the cost is saved.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft power supply and distribution technology, and in particular to a spacecraft thermal test power supply transfer interconnection structure and method, especially a satellite thermal test ground verification power supply and distribution interconnection structure and transfer method. Background Art

[0002] Before launch, the satellite needs to undergo thermal testing to verify the ability of the thermal control subsystem to maintain the onboard instruments and equipment within the specified temperature index range, to assess the adaptability of the single unit working in the active phase of the satellite launch to the low-pressure environment, to verify the working performance of the entire satellite in a vacuum thermal cycle environment, as well as the matching and coordination between the various systems, and to further expose potential defects in the process, assembly, and manufacturing of onboard equipment, materials, and components.

[0003] For the sake of convenience and safety, satellites are generally not powered directly by solar arrays during ground testing. Instead, they are powered by a ground simulation array and the connection between ground test equipment and satellites is completed via ground splitter cables.

[0004] Due to the limitation of thermal test conditions, the satellite is in a vacuum tank during the thermal test, and the ground simulation array and other ground equipment are outside the vacuum tank. The connection between the satellite and the ground simulation array needs to be achieved through the flange of the vacuum tube wall. At the same time, in order to evaluate the electrical performance of the drive mechanism slip ring, the power path needs to be led from the vacuum tube wall flange to the drive mechanism through the thermal test adapter cable, and then led back to the satellite electrical connector through the short-circuit plug at the satellite end of the drive mechanism, and then the power path is led to the power controller through the thermal test adapter cable to supply power to each unit on the satellite.

[0005] The patent document with publication number CN105375603A discloses a ground power supply system for satellite thermal vacuum test, including a solar simulation array, a control console, an external transfer cable network, an internal transfer cable network and a flange. Its transfer cable can connect the ordinary slip ring power supply to the vacuum tank flange without changing the single-machine design scheme on the satellite, while retaining the shunt connected to the vacuum tank flange through plugging and unplugging. By setting two power supply channels inside and outside the tank, it is ensured that the on-board power supply system can work normally after the single-point failure of the slip ring power supply during the thermal vacuum test. However, this solution cannot maximize the use of the original cables on the satellite, the length of the newly invested transfer cable is long, and the transfer cost is high. Summary of the invention

[0006] In view of the defects in the prior art, the purpose of the present invention is to provide a spacecraft thermal test power supply transfer interconnection structure and method.

[0007] The spacecraft thermal test power supply transfer interconnection structure provided by the present invention comprises a first on-board cable, a drive mechanism, a power controller, a thermal test transfer cable, a second on-board cable, a first ground cable, a second ground cable and a ground simulation array;

[0008] The thermal test transfer cable comprises a first thermal test transfer cable socket, a second thermal test transfer cable socket and a third thermal test transfer cable socket, and the driving mechanism is connected to the first thermal test transfer cable socket via a first on-board cable;

[0009] The second thermal test adapter cable socket is connected to the onboard power supply input electrical connector socket of the power controller, the third thermal test adapter cable socket is connected in sequence to the second onboard cable and the first ground cable, the first ground cable is connected to the second ground cable through the vacuum tank wall flange, and the second ground cable is connected to the ground simulation array.

[0010] Preferably, the first on-satellite cable is an original on-satellite cable, and one end of the first on-satellite cable is provided with a first on-satellite cable power supply output plug, which is connected to the on-satellite end electrical connector socket of the driving mechanism;

[0011] The other end of the first on-satellite cable is provided with a first on-satellite cable power supply input plug, the specification of the first on-satellite cable power supply input plug corresponds to the on-satellite power supply input end electrical connector socket, and the first on-satellite cable power supply input plug is connected to the first thermal test adapter cable socket.

[0012] Preferably, the second ground cable is a ground universal cable, and one end of the second ground cable is provided with a second ground cable ground analog array plug, which is connected to the ground analog array socket on the chassis of the ground analog array;

[0013] The other end of the second ground cable is provided with a second ground cable flange socket, which is connected to the side of the vacuum tube wall flange located outside the vacuum tank and is electrically connected to the first ground cable.

[0014] Preferably, the first ground cable is an original ground test cable on the satellite, one end of the first ground cable is provided with a first ground cable flange plug, connected to a side of the vacuum tube wall flange located in the vacuum tank, and electrically connected to the second ground cable;

[0015] The other end of the first ground cable is a detachable electrical connector of the satellite-to-ground interface, which is connected to the second satellite cable through the first ground cable detachable plug.

[0016] Preferably, the second on-satellite cable is an existing on-satellite cable, one end of which is a detachable electrical connector of a satellite-to-ground interface, and is connected to the first ground cable through a second on-satellite cable detachable socket;

[0017] The other end of the second on-satellite cable is provided with a second on-satellite cable power controller ground power supply input plug, the specification of the second on-satellite cable power controller ground power supply input plug corresponds to the ground power supply input electrical connector socket of the power controller, and the second on-satellite cable power controller ground power supply input plug is connected to the third thermal test adapter cable socket.

[0018] Preferably, the drive mechanism external star end electrical connector socket of the drive mechanism is connected with a drive mechanism external star end short-circuit plug, and the drive mechanism external star end short-circuit plug is used to test the drive mechanism slip ring power supply and signal transmission channel performance.

[0019] Preferably, the driving mechanism off-star end shorting plug comprises a driving mechanism off-star end power connector shorting plug;

[0020] The short-circuiting plug of the power connector at the outer end of the driving mechanism star leads the positive power line of the ground simulation array from the negative ring of the driving mechanism slip ring to the positive ring, so that the positive ring and the negative ring of the driving structure slip ring are short-circuited, which is used to test the performance of the power supply transmission channel of the driving mechanism slip ring.

[0021] Preferably, the driving mechanism external star end short-circuit plug comprises a driving mechanism external star end signal connector short-circuit plug;

[0022] The short-circuit plug of the signal connector at the outer end of the driving mechanism is connected in series with a resistor between the solar array deployment in place signal and the deployment in place signal ground on the left side plate of the driving mechanism slip ring, between the solar array deployment in place signal and the deployment in place signal ground on the right side plate, and between the solar array temperature measurement signal and the temperature measurement ground, so as to test the performance of the signal transmission channel of the driving mechanism slip ring.

[0023] Preferably, the driving mechanism external star end short-circuit plug comprises a driving mechanism external star end power connector short-circuit plug and a driving mechanism external star end signal connector short-circuit plug;

[0024] The specification of the short-circuit plug of the power connector at the outer star end of the driving mechanism is J6W-50D01KNMB, and the specification of the short-circuit plug of the signal connector at the outer star end of the driving mechanism is J6W-50D01JNMB.

[0025] A spacecraft thermal test power supply transfer interconnection method provided by the present invention is used to transfer the structure during the ground electrical test of the spacecraft to form the spacecraft thermal test power supply transfer interconnection structure;

[0026] During the ground electrical test of the spacecraft, the ground simulation array inputs energy into the ground power supply input end electrical connector socket of the power controller through the first ground cable and the second on-board cable in sequence, and the driving mechanism leads the power and signal to the on-board power supply input end electrical connector socket of the power controller through the first on-board cable;

[0027] The spacecraft thermal test power supply transfer interconnection method comprises the following steps:

[0028] Unplug the first on-board cable power supply input plug of the first on-board cable from the on-board power supply input end electrical connector socket, and connect it to the first thermal test adapter cable socket of the thermal test adapter cable;

[0029] Unplug the ground power supply input end plug of the second on-board cable power supply controller of the second on-board cable from the ground power supply input end electrical connector socket, and connect it to the third thermal test transfer cable socket of the thermal test transfer cable;

[0030] Connect the second thermal test adapter cable socket of the thermal test adapter cable to the electrical connector socket at the power supply input end on the satellite;

[0031] Unplug the first ground cable flange plug of the first ground cable from the ground simulation array and connect it to the inner side of the vacuum tank wall flange. Meanwhile, connect the outer side of the vacuum tube wall flange to the ground simulation array through the second ground cable.

[0032] Insert the short-circuit plug at the outer star end of the driving mechanism into the electrical connector socket at the outer star end of the driving mechanism.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] 1. The present invention has a simple structure, utilizes the original cable on the satellite, places the ground cable in the vacuum tank, and transfers the three power interface connectors of the driving mechanism satellite power output electrical connector, the power controller ground power input electrical connector, and the power controller satellite power input electrical connector, so that the length of the newly invested transfer cable can be reduced from 10 meters to 0.5 meters, saving costs;

[0035] 2. The coupling degree of the thermal test adapter cable in the present invention is low, and the three electrical connectors have a one-to-one correspondence. If there are several electrical connectors for transmitting simulated array power on a spacecraft, several adapter cables are used accordingly, and the cable has good versatility;

[0036] 3. The present invention short-circuits the positive and negative of the power ring through the short-circuit plug of the electric connector at the outer end of the driving mechanism star, and connects a resistor in series between the signal rings, so that the electrical transmission performance of the power ring and the signal ring of the driving mechanism can be evaluated during the whole star thermal test. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] 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:

[0038] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0039] Figure 2 It is a schematic diagram of the structure of the short-circuit plug of the power connector at the outer end of the driving mechanism in the present invention;

[0040] Figure 3 It is a schematic diagram of the structure of the short-circuit plug of the signal connector at the outer end of the driving mechanism in the present invention;

[0041] Figure 4 Cable connection diagram for ground test power supply of satellite equipment.

[0042] The figure shows:

[0043] Driving mechanism star external end short-circuit plug 1 Third thermal test adapter cable socket 10

[0044] Drive mechanism star external end electrical connector socket 2 Second satellite cable power controller ground power supply Drive mechanism star internal end electrical connector socket 3 Input end plug 11

[0045] The first satellite cable power supply output plug 4 The second satellite cable outlet socket 12

[0046] First satellite cable power supply input plug 5 First ground cable disconnect plug 13

[0047] First thermal test transfer cable socket 6 First ground cable flange plug 14

[0048] Second thermal test transfer cable socket 7 Second ground cable flange socket 15

[0049] On-board power supply input terminal electrical connector socket 8 Second ground cable ground simulation array plug 16

[0050] Ground power supply input terminal electrical connector socket 9 Ground analog array socket 17 DETAILED DESCRIPTION

[0051] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0052] The present invention discloses a spacecraft thermal test power supply transfer interconnection structure and method, which utilizes the original on-board cables, places the ground cables in a vacuum tank, and transfers three power interface connectors, namely, the on-board power supply output electrical connector of the driving mechanism, the ground power supply input electrical connector of the power supply controller, and the on-board power supply input electrical connector of the power supply controller, thereby greatly shortening the length of the new transfer cables and saving costs.

[0053] Example 1

[0054] This embodiment provides a spacecraft thermal test power supply transfer interconnection structure, such as Figure 1 As shown, it includes a first satellite cable, a driving mechanism, a power controller, a thermal test transfer cable, a second satellite cable, a first ground cable, a second ground cable and a ground simulation array; the thermal test transfer cable includes a first thermal test transfer cable socket 6, a second thermal test transfer cable socket 7 and a third thermal test transfer cable socket 10, the driving mechanism is connected to the first thermal test transfer cable socket 6 through the first satellite cable; the second thermal test transfer cable socket 7 is connected to the satellite power input end electrical connector socket 8 of the power controller, the third thermal test transfer cable socket 10 is connected to the second satellite cable and the first ground cable in sequence, the first ground cable is connected to the second ground cable through the vacuum tank wall flange, and the second ground cable is connected to the ground simulation array. By using the first satellite cable, the second satellite cable and the first ground cable, three original satellite cables, and using the thermal test transfer cable to realize the transfer of the three power interface connectors of the driving mechanism satellite end power output electrical connector, the power controller ground power input end electrical connector, and the power controller satellite power input end electrical connector, the length of the newly invested transfer cable can be greatly shortened.

[0055] Specifically, the first on-satellite cable is an original on-satellite cable, and one end of the first on-satellite cable is provided with a first on-satellite cable power output plug 4, which is connected to the on-satellite end electrical connector socket 3 of the driving mechanism; the other end of the first on-satellite cable is provided with a first on-satellite cable power input plug 5, and the specification of the first on-satellite cable power input plug 5 corresponds to the on-satellite power input end electrical connector socket 8, and the first on-satellite cable power input plug 5 is connected to the first thermal test adapter cable socket 6.

[0056] The second ground cable is a universal ground cable. One end of the second ground cable is provided with a second ground cable ground simulation array plug 16, which is connected to the ground simulation array socket 17 on the chassis of the ground simulation array; the other end of the second ground cable is provided with a second ground cable flange socket 15, which is connected to the side of the vacuum tube wall flange outside the vacuum tank and is electrically connected to the first ground cable.

[0057] The first ground cable is the original ground test cable on the satellite. One end of the first ground cable is provided with a first ground cable flange plug 14, which is connected to the side of the vacuum tube wall flange located in the vacuum tank and is electrically connected to the second ground cable; the other end of the first ground cable is a detachable electrical connector of the satellite-to-ground interface, which is connected to the second on-satellite cable through the first ground cable detachable plug 13.

[0058] The second on-satellite cable is the original on-satellite cable, one end of the second on-satellite cable is the detachable electrical connector of the satellite-to-ground interface, and is connected to the first ground cable through the second on-satellite cable detaching socket 12; the other end of the second on-satellite cable is provided with a second on-satellite cable power controller ground power supply input terminal plug 11, the specification of the second on-satellite cable power controller ground power supply input terminal plug 11 corresponds to the ground power supply input terminal electrical connector socket 9 of the power controller, and the second on-satellite cable power controller ground power supply input terminal plug 11 is connected to the third thermal test adapter cable socket 10.

[0059] Preferably, the low-frequency cables of the thermal test adapter cables all use FF40J-2Q / 19 / 0.20 conductors, and the cables are covered with nylon silk sheaths.

[0060] Example 2

[0061] Based on Example 1, this embodiment improves the test of the electrical transmission performance of the power ring and signal ring of the driving mechanism during the whole star thermal test. Specifically, the driving mechanism star-outside electrical connector socket 2 of the driving mechanism is connected to the driving mechanism star-outside short-circuit plug 1, and the driving mechanism star-outside short-circuit plug 1 is used to test the power supply and signal transmission channel performance of the driving mechanism slip ring.

[0062] like Figure 2 As shown, the drive mechanism external star short-circuit plug 1 includes a drive mechanism external star power connector short-circuit plug; the drive mechanism external star power connector short-circuit plug leads the power positive line of the ground simulation array from the negative ring of the drive mechanism slip ring to the positive ring, so that the positive ring and the negative ring of the drive structure slip ring are short-circuited, which is used to test the performance of the drive mechanism slip ring power supply transmission channel. Preferably, the drive mechanism external star power connector short-circuit plug specification is J6W-50D01KNMB;

[0063] like Figure 3 As shown, the drive mechanism external star end short-circuit plug 1 includes a drive mechanism external star end signal connector short-circuit plug; the drive mechanism external star end signal connector short-circuit plug is connected in series with a resistor between the left side panel solar array deployment in place signal and the deployment in place signal ground, between the right side panel solar array deployment in place signal and the deployment in place signal ground, and between the solar array temperature measurement signal and the temperature measurement ground, respectively, for testing the drive mechanism slip ring signal transmission channel performance. Preferably, the drive mechanism external star end signal connector short-circuit plug specification is J6W-50D01JNMB, and the series resistor is a 10Ω resistor.

[0064] Example 3

[0065] This embodiment provides a spacecraft thermal test power supply transfer interconnection method for transferring the structure during the ground electrical test of the spacecraft to form the spacecraft thermal test power supply transfer interconnection structure in Embodiment 1 or Embodiment 2;

[0066] like Figure 4 The figure shows the connection structure during the ground electrical test of the spacecraft. The ground simulation array inputs energy into the ground power supply input end electrical connector socket 9 of the power controller through the first ground cable and the second on-board cable in turn, and the driving mechanism leads the power and signal to the on-board power supply input end electrical connector socket 8 of the power controller through the first on-board cable;

[0067] The spacecraft thermal test power supply transfer interconnection method comprises the following steps:

[0068] Before the spacecraft thermal test, the first on-board cable power input plug 5 of the first on-board cable is unplugged from the on-board power input end electrical connector socket 8 and connected to the first thermal test adapter cable socket 6 of the thermal test adapter cable;

[0069] Unplug the ground power supply input end plug 11 of the second on-board cable power controller of the second on-board cable from the ground power supply input end electrical connector socket 9, and connect it to the third thermal test transfer cable socket 10 of the thermal test transfer cable;

[0070] Connect the second thermal test adapter cable socket 7 of the thermal test adapter cable to the electrical connector socket 8 at the power supply input end on the satellite;

[0071] Unplug the first ground cable flange plug 14 of the first ground cable from the ground simulation array and connect it to the inner side of the vacuum tank wall flange. Meanwhile, connect the outer side of the vacuum tube wall flange to the ground simulation array through the second ground cable.

[0072] Insert the short-circuit plug 1 at the external end of the drive mechanism into the electrical connector socket 2 at the external end of the drive mechanism. This completes the power supply cable modification before the spacecraft thermal test. Figure 1 The spacecraft thermal test power supply transfer interconnection structure is shown.

[0073] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0074] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A spacecraft thermal test power supply transfer interconnection structure, characterized in that: It includes a first on-board cable, a driving mechanism, a power supply controller, a thermal test adapter cable, a second on-board cable, a first ground cable, a second ground cable and a ground simulation array; The thermal test transfer cable comprises a first thermal test transfer cable socket (6), a second thermal test transfer cable socket (7) and a third thermal test transfer cable socket (10), and the driving mechanism is connected to the first thermal test transfer cable socket (6) via a first on-board cable; The second thermal test adapter cable socket (7) is connected to the onboard power supply input terminal electrical connector socket (8) of the power controller, the third thermal test adapter cable socket (10) is connected in sequence to the second onboard cable and the first ground cable, the first ground cable is connected to the second ground cable via the vacuum tank wall flange, and the second ground cable is connected to the ground simulation array.

2. The spacecraft thermal test power supply transfer interconnection structure according to claim 1, characterized in that: The first on-satellite cable is an original on-satellite cable, and one end of the first on-satellite cable is provided with a first on-satellite cable power supply output plug (4), which is connected to the on-satellite end electrical connector socket (3) of the driving mechanism; The other end of the first on-satellite cable is provided with a first on-satellite cable power input plug (5), the specification of the first on-satellite cable power input plug (5) corresponds to the on-satellite power input end electrical connector socket (8), and the first on-satellite cable power input plug (5) is connected to the first thermal test adapter cable socket (6).

3. The spacecraft thermal test power supply transfer interconnection structure according to claim 1, characterized in that: The second ground cable is a general ground cable, and one end of the second ground cable is provided with a second ground cable ground simulation array plug (16) which is connected to a ground simulation array socket (17) on a chassis of the ground simulation array; The other end of the second ground cable is provided with a second ground cable flange socket (15), which is connected to the side of the vacuum tube wall flange located outside the vacuum tank and is electrically connected to the first ground cable.

4. The spacecraft thermal test power supply transfer interconnection structure according to claim 1, characterized in that: The first ground cable is an existing ground test cable on the satellite, one end of which is provided with a first ground cable flange plug (14), which is connected to a side of the vacuum tube wall flange located in the vacuum tank and is electrically connected to the second ground cable; The other end of the first ground cable is a detachable electrical connector of the satellite-to-ground interface, which is connected to the second satellite cable through a first ground cable detachable plug (13).

5. The spacecraft thermal test power supply transfer interconnection structure according to claim 1, characterized in that: The second on-satellite cable is an original on-satellite cable, one end of which is a detachable electrical connector of a satellite-to-ground interface, and is connected to the first ground cable via a second on-satellite cable detachable socket (12); The other end of the second on-satellite cable is provided with a second on-satellite cable power controller ground power input plug (11), the specification of the second on-satellite cable power controller ground power input plug (11) corresponds to the ground power input electrical connector socket (9) of the power controller, and the second on-satellite cable power controller ground power input plug (11) is connected to the third thermal test adapter cable socket (10).

6. The spacecraft thermal test power supply transfer interconnection structure according to claim 1, characterized in that: The drive mechanism external star end electrical connector socket (2) of the drive mechanism is connected to a drive mechanism external star end short-circuit plug (1), and the drive mechanism external star end short-circuit plug (1) is used to test the drive mechanism slip ring power supply and signal transmission channel performance.

7. The spacecraft thermal test power supply transfer interconnection structure according to claim 6, characterized in that: The driving mechanism external star end short-circuit plug (1) comprises a driving mechanism external star end power connector short-circuit plug; The short-circuiting plug of the power connector at the outer end of the driving mechanism star leads the positive power line of the ground simulation array from the negative ring of the driving mechanism slip ring to the positive ring, so that the positive ring and the negative ring of the driving structure slip ring are short-circuited, which is used to test the performance of the power supply transmission channel of the driving mechanism slip ring.

8. The spacecraft thermal test power supply transfer interconnection structure according to claim 1, characterized in that: The driving mechanism external star end short-circuit plug (1) comprises a driving mechanism external star end signal connector short-circuit plug; The short-circuit plug of the signal connector at the outer end of the driving mechanism is connected in series with a resistor between the solar array deployment in place signal and the deployment in place signal ground on the left side plate of the driving mechanism slip ring, between the solar array deployment in place signal and the deployment in place signal ground on the right side plate, and between the solar array temperature measurement signal and the temperature measurement ground, so as to test the performance of the signal transmission channel of the driving mechanism slip ring.

9. The spacecraft thermal test power supply transfer interconnection structure according to claim 1, characterized in that: The driving mechanism external star end short-circuit plug (1) comprises a driving mechanism external star end power connector short-circuit plug and a driving mechanism external star end signal connector short-circuit plug; The specification of the short-circuit plug of the power connector at the outer star end of the driving mechanism is J6W-50D01KNMB, and the specification of the short-circuit plug of the signal connector at the outer star end of the driving mechanism is J6W-50D01JNMB.

10. A method for power supply transfer and interconnection of spacecraft thermal test, characterized in that: Used to convert the structure during the ground electrical test of the spacecraft to form the spacecraft thermal test power supply transfer interconnection structure as described in any one of claims 1 to 9; During the ground electrical test of the spacecraft, the ground simulation array sequentially inputs energy into the ground power supply input end electrical connector socket (9) of the power controller through the first ground cable and the second on-board cable, and the driving mechanism leads the power and signal to the on-board power supply input end electrical connector socket (8) of the power controller through the first on-board cable; The spacecraft thermal test power supply transfer interconnection method comprises the following steps: Unplug the first on-board cable power input plug (5) of the first on-board cable from the on-board power input end electrical connector socket (8), and connect it to the first thermal test adapter cable socket (6) of the thermal test adapter cable; Unplug the ground power input end plug (11) of the second on-board cable power controller of the second on-board cable from the ground power input end electrical connector socket (9), and connect it to the third thermal test transfer cable socket (10) of the thermal test transfer cable; Connecting the second thermal test adapter cable socket (7) of the thermal test adapter cable to the onboard power supply input terminal electrical connector socket (8); The first ground cable flange plug (14) of the first ground cable is unplugged from the ground simulation array and connected to the inner side of the vacuum tank wall flange, and at the same time, the outer side of the vacuum tube wall flange is connected to the ground simulation array through the second ground cable; Insert the short-circuit plug (1) at the outer end of the driving mechanism star into the electrical connector socket (2) at the outer end of the driving mechanism star.

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