Space attitude adjusting device, system and method for satellite testing

Abstract

The invention relates to the technical field of satellite product testing, in particular to a space attitude adjusting device, system and method for satellite testing. The device comprises a rotary connecting seat, wherein the rotary connecting seat comprises an upper connecting plate, a lower connecting plate and a connecting column; the top surface of the upper connecting plate is rotatably connected with a rotating mechanism, and the upper surface of the lower connecting plate is fixedly connected with a hanging mechanism; the system further comprises a tilt angle sensor and a servo driving system. The method comprises the following steps: respectively connecting the free ends of the slings with different end parts of a test satellite; adjusting the length of each sling, and adjusting the pitch angle and the roll angle of the tested satellite; the rotation driving device is started to drive the rotation connecting seat to rotate integrally, and the azimuth angle of the test satellite is adjusted to the test azimuth angle; after the satellite to be tested is static, space attitude adjustment is completed. The problems that in the prior art, the attitude adjustment range is small, the testing efficiency is low, and the testing result error is large are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite product testing, and in particular to a space attitude adjustment device, system and method for satellite testing. Background Art

[0002] Satellite surface scattering test is an important test specially used to evaluate and study the reflection and scattering characteristics of satellite surface materials to electromagnetic waves. This test is crucial to ensure the communication performance, radar stealth, thermal control effect, etc. of the satellite during its in-orbit operation. When performing scattering test, the product needs to be fixed in a specific position or adjusted in attitude. The fixing or attitude adjustment of the test product requires the cooperation of a support body. In order to reduce the impact on the scattering test results, the support body needs to be made of a low-scattering material structure.

[0003] There are currently two main commonly used support methods: one is a low-scatter foam bracket system, and the other is a low-scatter metal bracket system. The low-scatter foam bracket system places a low-scatter foam bracket on a one-dimensional turntable table. It is only used for one-dimensional testing and does not have two-dimensional or three-dimensional testing functions. The low-scatter metal bracket system embeds the top low-scatter metal rotating top into the test product. The rotating top has azimuth rotation and small-angle pitch functions, and can perform one-dimensional and two-dimensional tests; however, since the metal rotating top needs to be embedded in the test product, the test product needs to be provided with a groove that matches the rotating top, and therefore cannot be used for testing actual satellite products; since the rotation angle of the rotating top is limited, the attitude adjustment range of the test product is small, resulting in low test efficiency. Since neither of the two existing technologies can simulate the actual attitude of the satellite in space for three-dimensional testing, the test results often have large errors.

[0004] CN114740443A discloses a low-scattering foam bracket for testing target radar scattering characteristics, belonging to the field of RCS test technology, including a foam support platform, a foam support seat, a first foam support body, a second foam support body and a third foam support body, the first foam support body including a first large support body and a first small support body detachably connected to the first large support body, the second foam support body including two detachably connected second support blocks, the two second support blocks are symmetrically arranged along a horizontal line, the third foam support body including two detachably connected third support blocks, the two third support blocks are symmetrically arranged along a horizontal line, the first large support body is located above the foam support seat and is connected to the foam support seat with mortise and tenon joints.

[0005] However, the prior art uses a low-scattering foam support system and can only be used for one-dimensional testing, and does not have two-dimensional or three-dimensional testing capabilities. Summary of the invention

[0006] The purpose of the present invention is to provide a space attitude adjustment device, system and method for satellite testing, which can realize three-dimensional, large-angle attitude adjustment of satellite products in space, and at the same time have good low-scattering characteristics to provide a good test environment for testing; it solves the problem that the attitude adjustment range of the prior art is small, resulting in low test efficiency and large errors in test results.

[0007] The present invention provides the following solution

[0008] A space attitude adjustment device for satellite testing comprises a rotating connection seat, wherein the rotating connection seat comprises an upper connection plate and a lower connection plate, wherein a connection column is fixedly connected between the upper connection plate and the lower connection plate; a rotating mechanism is rotatably connected to the top surface of the upper connection plate, and a hanging mechanism is fixedly connected to the upper surface of the lower connection plate.

[0009] Furthermore, the rotating mechanism includes a rotating bearing and a rotating driving device, the rotating bearing is rotatably connected to the top surface of the upper connecting plate of the rotating connecting seat; the lower end of the rotating driving device is fixedly connected to the upper surface of the lower connecting plate, and the upper end of the rotating driving device is meshingly connected to the rotating bearing; the hanging mechanism includes at least four winches, each of the winches is fixedly connected to the upper surface of the lower connecting plate, and each of the winches is driven and connected to a sling, and the free end of the sling is located below the lower connecting plate.

[0010] The rotating drive device can drive the rotating bearing to rotate relatively or remain stationary, driving the entire rotating connecting seat to rotate to adjust the azimuth angle of the satellite; the winch can roll the sling up and down to extend or shorten it. Setting up at least four winches and slings can ensure that the test satellite has at least one sling connected in the four directions of front, back, left and right, so that it can rotate in two axes. Adding more winches and slings to connect more suspension points can make the rotation angle range wider and more precise.

[0011] Furthermore, the upper connecting plate and the lower connecting plate are both circular structures, the cross-section of the connecting column is also circular, and the centers of the upper connecting plate, the lower connecting plate and the cross-section of the connecting column are coaxial; the edge of the upper connecting plate is provided with a motor connecting part protruding outward, and the motor connecting part is provided with a through hole; the lower connecting plate is provided with a limiting hole for the sling to pass through.

[0012] Setting it as a circular structure can make the overall center of gravity and rotation center of the device more stable; the rotation drive device drives the entire rotating connection seat to rotate through the motor connection part; setting the limit hole can make the sling move within a certain range to avoid mutual entanglement.

[0013] Furthermore, the rotation drive device includes a motor and a driving gear, the lower end of the motor is fixedly connected to the upper surface of the lower connecting plate, the upper part of the motor is fixedly connected to the motor connecting part of the upper connecting plate, the output shaft at the upper end of the motor passes through the through hole on the motor connecting part and is connected to the driving gear, and the driving gear is meshingly connected to the rotating bearing.

[0014] The upper and lower ends of the motor are fixedly connected to the rotating connecting seat, making the connection more firm and avoiding falling off or damage when the drive rotates.

[0015] Furthermore, the center of the rotating bearing coincides with the center of the upper connecting plate; the rotating bearing comprises an outer gear ring and an inner ring, the outer wall of the outer gear ring is evenly provided with transmission teeth along the circumferential direction, and the transmission teeth are meshed with the driving gear of the rotating drive device; the inner side of the outer gear ring is rotatably connected with the inner ring, the lower surface of the inner ring protrudes from the lower surface of the outer gear ring and is fixedly connected to the top surface of the upper connecting plate; balls and retaining frames are provided between the outer gear ring and the inner ring; the top surface of the outer gear ring is fixedly connected with a connecting piece for connecting to an external fixing facility.

[0016] The rotating bearing can be driven to rotate relative to the outer gear ring through the rotating driving device; since the outer gear ring of the rotating bearing is fixed and the inner ring is fixedly connected to the rotating connecting seat, the rotating connecting seat as a whole rotates relative to the outer gear ring under the drive of the rotating driving device, thereby adjusting the azimuth angle of the test satellite; balls and retaining frames are provided between the outer gear ring and the inner ring to reduce friction resistance and make the rotation of the inner ring relative to the outer gear ring smoother; a connecting piece is fixedly connected to the top surface of the outer gear ring for connecting to external fixing facilities such as laboratory beams.

[0017] Furthermore, the hanging mechanism includes four winches evenly arranged along the circumference of the lower connecting plate, each of the winches is fixedly connected to the upper surface of the lower connecting plate, each of the winches is driven and connected to a sling, and the lower connecting plate is evenly provided with limiting holes corresponding to the four winches along the circumference, and the free end of each of the slings passes through the corresponding limiting hole to the bottom of the lower connecting plate.

[0018] The lower connecting plate is evenly provided with four winches and corresponding limiting holes along the circumference. The free end of each sling passes through the corresponding limiting hole to the bottom of the lower connecting plate and is connected to one end of the test satellite. The four slings are respectively connected to the front, back, left and right ends of the test satellite to adjust the pitch and roll angles.

[0019] Furthermore, circular weight-reducing holes are provided in the centers of the upper connecting plate, the connecting column and the lower connecting plate; and stiffening plates are fixedly connected between the connecting column and the upper connecting plate and between the connecting column and the lower connecting plate.

[0020] Weight-reducing holes are provided to reduce the overall weight of the rotating connection seat and save materials; stiffening plates are fixedly connected between the connection column and the upper and lower connection plates to make the connection between the connection column and the upper and lower connection plates more secure and withstand greater loads.

[0021] Furthermore, it also includes an anti-sway mechanism, which includes a turntable and an elastic rope. The turntable includes a base, which is fixedly connected to the ground. The top of the base is rotatably connected to a turntable, and the rotation center of the turntable and the rotation center of the rotating bearing are located on the same axis. The outer edge of the turntable is evenly provided with four elastic rope connecting parts along the circumferential direction, and an elastic rope connecting hole is provided in the middle of each elastic rope connecting part. The elastic rope is detachably connected to the elastic rope connecting hole.

[0022] During the process of adjusting the test satellite's spatial attitude, the elastic rope has tension, which can effectively reduce the shaking amplitude of the test satellite, allowing the satellite to return to a stationary state more quickly; when adjusting the azimuth angle, the turntable of the turntable can rotate with the test satellite, so it will not affect the azimuth angle adjustment process.

[0023] A space attitude adjustment system for satellite testing includes a tilt sensor and a servo drive system, and also includes the above-mentioned space attitude adjustment device for satellite testing; the tilt sensor is detachably connected to the test satellite, and the tilt sensor, winch and rotation drive device are all electrically connected to the servo drive system.

[0024] The inclination sensor can be detachably connected to the test satellite, and can measure the spatial angle of the test satellite more quickly and accurately; the system also includes a servo drive system for automatically controlling the space attitude adjustment device to perform various angle adjustments; setting up the inclination sensor and connecting the device to the servo drive system can effectively improve the test efficiency and positioning accuracy.

[0025] A space attitude adjustment method for satellite testing, based on the space attitude adjustment device for satellite testing, comprises the following steps:

[0026] Connecting the free ends of the slings to different ends of the test satellite;

[0027] Adjust the length of each sling, and adjust the pitch angle and roll angle of the test satellite to the test pitch angle and test roll angle;

[0028] Start the rotation drive device to drive the rotating connector to rotate as a whole, and adjust the azimuth angle of the test satellite to the test azimuth angle;

[0029] After the test satellite is stationary, the space attitude adjustment is completed.

[0030] Compared with the prior art, the present invention has the following advantages:

[0031] The space attitude adjustment device, system and method for satellite testing provided by the present invention can realize three-dimensional and large-angle attitude adjustment of satellite products in space by setting a rotating mechanism and a hanging mechanism, and at the same time use a sling made of low-scattering material, which has good low-scattering characteristics and provides a good test environment for testing; in addition, the anti-sway mechanism and the top hanging are coordinated with each other to reduce the shaking amplitude of the test satellite, so that the satellite can return to a stationary state more quickly, thereby improving the test efficiency; setting an inclination sensor and connecting the device to a servo drive system can effectively improve the test efficiency and positioning accuracy; thereby meeting the test requirements of large angle, low scattering, high accuracy and high efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0033] Attached Figure 1 This is a schematic diagram of the overall structure of the space attitude adjustment device for satellite testing according to the present invention;

[0034] Attached Figure 2 It is a schematic diagram of the structure explosion of the space attitude adjustment device for satellite testing according to the present invention;

[0035] Attached Figure 3 It is a structural schematic diagram of the rotating connecting seat of the present invention;

[0036] Attached Figure 4 It is a partial structural schematic diagram of the rotating mechanism of the present invention;

[0037] Attached Figure 5 It is a partial structural schematic diagram of the rotary bearing of the present invention;

[0038] Attached Figure 6 It is a schematic cross-sectional view of a local structure of the rotary bearing of the present invention;

[0039] Attached Figure 7 This is a schematic diagram of the overall structure of the space attitude adjustment device for satellite testing according to Embodiment 2 of the present invention;

[0040] Attached Figure 8 This is a schematic diagram of the structure of the turntable described in Example 2 of the present invention;

[0041] Attached Fig. 9This is a schematic diagram of the space attitude adjustment method for satellite testing according to the present invention;

[0042] Attached Fig.10 A schematic diagram of a test principle of the space attitude adjustment method for satellite testing according to the present invention;

[0043] Attached Fig.11 This is another schematic diagram of the testing principle of the space attitude adjustment method for satellite testing described in the present invention.

[0044] In the figure:

[0045] 1-rotating connecting seat, 11-upper connecting plate, 111-motor connecting part, 12-lower connecting plate, 121-limiting hole, 13-connecting column, 131-stiffening plate, 2-rotating mechanism, 21-rotating bearing, 211-outer gear ring, 212-inner ring, 213-connecting piece, 214-ball, 215-retaining frame, 22-rotating driving device, 221-motor, 222-driving gear, 3-hanging mechanism, 31-winch, 32-sling, 4-anti-sway mechanism, 41-turntable, 411-base, 412-turntable, 4121-elastic rope connecting part, 42-elastic rope. DETAILED DESCRIPTION

[0046] In order to make the purpose, technical solutions and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0047] The terms used in the embodiments of the present application are only for the purpose of describing specific embodiments, and are not intended to limit the present application. The singular forms "a", "said" and "the" used in the embodiments of the present application and the appended claims are also intended to include plural forms, unless the context clearly indicates other meanings, and "multiple" generally includes at least two.

[0048] It should be understood that the term "and / or" used in this article is only a description of the association relationship of associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, the character " / " in this article generally indicates that the associated objects before and after are in an "or" relationship.

[0049] It should be understood that although the terms first, second, third, etc. may be used to describe in the embodiments of the present application, these descriptions should not be limited to these terms. These terms are only used to distinguish the descriptions. For example, without departing from the scope of the embodiments of the present application, the first may also be referred to as the second, and similarly, the second may also be referred to as the first.

[0050] As used herein, the words "if" and "if" may be interpreted as "at the time of" or "when" or "in response to determining" or "in response to detecting", depending on the context. Similarly, the phrases "if it is determined" or "if (stated condition or event) is detected" may be interpreted as "when it is determined" or "in response to determining" or "when detecting (stated condition or event)" or "in response to detecting (stated condition or event)", depending on the context.

[0051] It should also be noted that the term "includes", "comprising" or any other variation thereof is intended to cover non-exclusive inclusion, so that a commodity or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such commodity or device. In the absence of more restrictions, the elements defined by the sentence "comprising a ..." do not exclude the existence of other identical elements in the commodity or device including the elements.

[0052] It should be particularly noted that any symbols and / or numbers in the specification that are not marked in the accompanying drawings are not drawing marks.

[0053] Example 1, please refer to Figure 1 As shown, this embodiment provides a space attitude adjustment device for satellite testing, including a rotating connection seat 1, the top of the rotating connection seat 1 is rotatably connected to a rotating mechanism 2, and the lower part of the rotating connection seat 1 is fixedly connected to a hanging mechanism 3.

[0054] Specifically, see Figure 2 and Figure 3As shown, the rotating connecting seat 1 includes an upper connecting plate 11 and a lower connecting plate 12, and a connecting column 13 is fixedly connected between the upper connecting plate 11 and the lower connecting plate 12; preferably, the upper connecting plate 11 and the lower connecting plate 12 are both circular structures, and the cross section of the connecting column 13 is also circular, and the centers of the three are on the same straight line; the cross sections of the upper connecting plate 11, the lower connecting plate 12 and the connecting column 13 can also be square or other shapes; the edge of the upper connecting plate 11 is protruding outwardly with a motor connecting portion 111, and the motor connecting portion 111 is provided with a through hole; preferably, the upper Circular weight-reducing holes are provided in the centers of the connecting plate 11, the connecting column 13 and the lower connecting plate 12 to reduce the overall weight of the rotating connecting seat 1 and save materials; a stiffening plate 131 is fixedly connected between the upper end of the connecting column 13 and the lower surface of the upper connecting plate 11 and between the lower end of the connecting column 13 and the upper surface of the lower connecting plate 12 to make the connection between the connecting column 13 and the upper and lower connecting plates 12 more secure and withstand greater loads; the top surface of the upper connecting plate 11 is rotatably connected to the rotating mechanism 2, and the upper surface of the lower connecting plate 12 is fixedly connected to the hanging mechanism 3.

[0055] See also Figure 2 and Figure 4 As shown, the rotating mechanism 2 includes a rotating bearing 21 and a rotating driving device 22. The rotating bearing 21 is rotatably connected to the top surface of the upper connecting plate 11 of the rotating connecting seat 1, and the center of the rotating bearing 21 coincides with the center of the upper connecting plate 11; the rotating driving device 22 includes a motor 221 and a driving gear 222. The lower end of the motor 221 is fixedly connected to the upper surface of the lower connecting plate 12, and the upper part of the motor 221 is fixedly connected to the motor connecting part 111 of the upper connecting plate 11. The output shaft at the upper end of the motor 221 passes through the through hole on the motor connecting part 111 and is connected to the driving gear 222, and the driving gear 222 is meshed and connected with the rotating bearing 21.

[0056] Specifically, see Figure 2 , Figure 5 and Figure 6 As shown, the rotating bearing 21 includes an outer ring gear 211 and an inner ring 212. The outer wall of the outer ring gear 211 is evenly provided with transmission teeth along the circumferential direction and meshes with the driving gear 222 of the rotating driving device 22. The inner side of the outer ring gear 211 is rotatably connected with the inner ring 212. The lower surface of the inner ring 212 protrudes from the lower surface of the outer ring gear 211 and is fixedly connected to the top surface of the upper connecting plate 11; balls 214 and a retaining frame 215 are provided between the outer ring gear 211 and the inner ring gear 212 to reduce friction resistance and make the rotation of the inner ring 212 relative to the outer ring gear 211 smoother; the top surface of the outer ring gear 211 is fixedly connected with a connecting piece 213 to connect with external fixing facilities such as laboratory beams.

[0057] See also Figure 2 and Figure 3As shown, the suspension mechanism 3 includes at least four winches 31 evenly arranged along the circumference of the lower connecting plate 12, each winch 31 is fixedly connected to the upper surface of the lower connecting plate 12, each winch 31 is driven and connected to a sling 32, and the lower connecting plate 12 is evenly provided with limiting holes 121 corresponding to the four winches 31 along the circumference, and the free end of each sling 32 passes through the corresponding limiting hole 121 to the bottom of the lower connecting plate 12 and is connected to one end of the test satellite, and the four slings 32 are respectively connected to the front, back, left and right ends of the test satellite to adjust the pitch and roll angles. Considering the test requirements, the sling 32 needs to have low RCS reflection characteristics, so the sling 32 uses a low-reflection cable; a low-reflection cable is a cable specially designed to reduce electromagnetic wave reflection, and is widely used in applications that require minimizing electromagnetic interference or radar cross section (RCS). Such cables are usually used in aerospace, military equipment, communication antenna support, stealth technology and other fields.

[0058] See also Fig. 9 As shown, this embodiment also provides a space attitude adjustment method for satellite testing, based on the above-mentioned space attitude adjustment device for satellite testing, including the following steps:

[0059] Connecting the free ends of the slings 32 to different ends of the test satellite respectively;

[0060] Adjust the length of each sling 32 to adjust the pitch angle and roll angle of the test satellite to the test pitch angle and the test roll angle;

[0061] The rotation driving device 22 is started to drive the rotating connecting seat 1 to rotate as a whole, and the azimuth angle of the test satellite is adjusted to the test azimuth angle;

[0062] After the test satellite is stationary, the space attitude adjustment is completed.

[0063] Specifically, first, the free ends of the four cables 32 are connected to the front, rear, left and right ends of the test satellite respectively; the test pitch angle, test roll angle and test azimuth angle are target angles pre-set to meet the test needs, and the length of each cable 32 can be adjusted by winding the cable 32 with the winch 31 to adjust the pitch angle and roll angle of the test satellite.

[0064] See also Fig.10 As shown, in a certain test, the test pitch angle is set to 45° and the test roll angle is set to 0°, then the front and rear slings 32 are adjusted to be the same length and tightened so that the roll angle is 0°, and then the left sling 32 is extended and relaxed, and the right sling 32 is shortened and tightened so that the pitch angle is 45°.

[0065] See also Fig.11As shown, in a certain test, the test pitch angle is set to 0° and the test roll angle is set to 90°, and the rear sling 32 is adjusted to be shortened and tightened, and the other three slings 32 are extended and relaxed, so that the pitch angle is 0° and the roll angle is 90°.

[0066] The rotating bearing 21 can be driven to rotate relative to the rotating bearing 21 by the rotating driving device 22; since the outer ring gear 211 of the rotating bearing 21 is fixed and the inner ring 212 is fixedly connected to the rotating connecting seat 1, the rotating connecting seat 1 is driven by the rotating driving device 22, and the rotating connecting seat 1 is rotated as a whole relative to the outer ring gear 211, thereby adjusting the azimuth angle of the test satellite.

[0067] Through the cooperation of the four suspension ropes 32 of the suspension mechanism 3, various combinations of pitch angles and roll angles can be realized to meet the testing requirements of various space postures; on top of this, the azimuth angle of the test satellite can be adjusted through the rotating mechanism 2 to realize the three-dimensional testing function.

[0068] Example 2, please refer to Figure 7 As shown, this embodiment provides a space attitude adjustment device for satellite testing. On the basis of Embodiment 1, an anti-sway mechanism 4 is added to prevent the test satellite from shaking significantly during the attitude adjustment process.

[0069] Specifically, see Figure 7 and Figure 8 As shown, the anti-sway mechanism 4 includes a turntable 41 and an elastic rope 42. The turntable 41 includes a base 411, which is fixedly connected to the ground. The top of the base 411 is rotatably connected to a turntable 412. The rotation center of the turntable 412 and the rotation center of the rotating bearing 21 are located on the same axis. The outer edge of the turntable 412 is evenly provided with four elastic rope connecting parts 4121 along the circumferential direction. An elastic rope connecting hole is provided in the middle of each elastic rope connecting part 4121. The elastic rope 42 is detachably connected to the elastic rope connecting hole. The upper ends of the four elastic ropes 42 are respectively connected to the front, back, left and right four ends of the test satellite.

[0070] During the process of adjusting the test satellite's spatial attitude, since the elastic rope 42 has tension, the shaking amplitude of the test satellite can be effectively reduced, allowing the satellite to return to a stationary state more quickly; when adjusting the azimuth angle, the turntable 412 of the turntable 41 can rotate with the test satellite, so it will not affect the azimuth angle adjustment process.

[0071] Embodiment 3, this embodiment provides a space attitude adjustment system for satellite testing, including a space attitude adjustment device for satellite testing as in embodiment 1 or embodiment 2, and also including an inclination sensor, which is detachably connected to the test satellite and can measure the space angle of the test satellite more quickly and accurately. The system also includes a servo drive system for automatically controlling the space attitude adjustment device to make various angle adjustments; the servo drive system is a high-precision motion control system widely used in industrial automation, robotics, CNC machine tools, precision positioning equipment and other fields; it can accurately control the speed, position and torque of the motor 221 and the winch 31 through a closed-loop control method, ensuring that the movement of the mechanical system has high precision, high responsiveness and high stability; the inclination sensor, the winch 31 and the rotation drive device 22 are all electrically connected to the servo drive system.

[0072] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A space attitude adjustment device for satellite testing, characterized in that: The invention comprises a rotating connection seat (1), wherein the rotating connection seat (1) comprises an upper connecting plate (11) and a lower connecting plate (12), wherein a connecting column (13) is fixedly connected between the upper connecting plate (11) and the lower connecting plate (12); the top surface of the upper connecting plate (11) is rotatably connected to a rotating mechanism (2), and the upper surface of the lower connecting plate (12) is fixedly connected to a hanging mechanism (3).

2. The space attitude adjustment device for satellite testing according to claim 1, characterized in that: The rotating mechanism (2) comprises a rotating bearing (21) and a rotating driving device (22), wherein the rotating bearing (21) is rotatably connected to the top surface of the upper connecting plate (11) of the rotating connecting seat (1); the lower end of the rotating driving device (22) is fixedly connected to the upper surface of the lower connecting plate (12), and the upper end of the rotating driving device (22) is meshingly connected to the rotating bearing (21); the hanging mechanism (3) comprises at least four winches (31), each of the winches (31) is fixedly connected to the upper surface of the lower connecting plate (12), and each of the winches (31) is drivingly connected to a sling (32), and the free end of the sling (32) is located below the lower connecting plate (12).

3. The space attitude adjustment device for satellite testing according to claim 2, characterized in that: The upper connecting plate (11) and the lower connecting plate (12) are both circular structures, the cross section of the connecting column (13) is also circular, and the centers of the cross sections of the upper connecting plate (11), the lower connecting plate (12) and the connecting column (13) are coaxial; a motor connecting portion (111) is protruding outward from the edge of the upper connecting plate (11), and a through hole is provided on the motor connecting portion (111); and a limiting hole (121) is provided on the lower connecting plate (12) for the sling (32) to pass through.

4. The space attitude adjustment device for satellite testing according to claim 3, characterized in that: The rotation driving device (22) comprises a motor (221) and a driving gear (222); the lower end of the motor (221) is fixedly connected to the upper surface of the lower connecting plate (12); the upper part of the motor (221) is fixedly connected to the motor connecting portion (111) of the upper connecting plate (11); the output shaft at the upper end of the motor (221) passes through a through hole on the motor connecting portion (111) and is connected to the driving gear (222); and the driving gear (222) is meshedly connected to the rotating bearing (21).

5. The space attitude adjustment device for satellite testing according to claim 4, characterized in that: The center of the rotating bearing (21) coincides with the center of the upper connecting plate (11); the rotating bearing (21) comprises an outer gear ring (211) and an inner ring (212); the outer wall of the outer gear ring (211) is evenly provided with transmission teeth along the circumferential direction, and the transmission teeth are meshed with the driving gear (222) of the rotating driving device (22); the inner side of the outer gear ring (211) is rotatably connected with the inner ring (212), the lower surface of the inner ring (212) protrudes from the lower surface of the outer gear ring (211) and is fixedly connected to the top surface of the upper connecting plate (11); balls (214) and a retaining frame (215) are provided between the outer gear ring (211) and the inner ring (212); the top surface of the outer gear ring (211) is fixedly connected with a connecting piece (213) for connecting to an external fixing facility.

6. The space attitude adjustment device for satellite testing according to claim 3, characterized in that: The hanging mechanism (3) comprises four hoists (31) uniformly arranged along the circumference of the lower connecting plate (12), each of the hoists (31) is fixedly connected to the upper surface of the lower connecting plate (12), each of the hoists (31) is drivingly connected to a sling (32), and the lower connecting plate (12) is uniformly provided with limiting holes (121) corresponding to the four hoists (31) along the circumference, and the free end of each sling (32) passes through the corresponding limiting hole (121) to the bottom of the lower connecting plate (12).

7. The space attitude adjustment device for satellite testing according to claim 3, characterized in that: Circular weight-reducing holes are provided at the centers of the upper connecting plate (11), the connecting column (13) and the lower connecting plate (12); and stiffening plates (131) are fixedly connected between the connecting column (13) and the upper connecting plate (11) and between the connecting column (13) and the lower connecting plate (12).

8. The space attitude adjustment device for satellite testing according to any one of claims 2 to 7, characterized in that: The invention also comprises an anti-sway mechanism (4), wherein the anti-sway mechanism (4) comprises a turntable (41) and an elastic rope (42), wherein the turntable (41) comprises a base (411), wherein the base (411) is fixedly connected to the ground, wherein a turntable (412) is rotatably connected to the top of the base (411), wherein the rotation center of the turntable (412) and the rotation center of the rotation bearing (21) are located on the same axis, and the outer edge of the turntable (412) is evenly provided with four elastic rope connection parts (4121) along the circumferential direction, wherein an elastic rope connection hole is provided in the middle of each elastic rope connection part (4121), and the elastic rope (42) is detachably connected to the elastic rope connection hole.

9. A space attitude adjustment system for satellite testing, comprising an inclination sensor and a servo drive system, characterized in that: It also includes the space attitude adjustment device for satellite testing as described in claim 8; the inclination sensor is detachably connected to the test satellite, and the inclination sensor, winch (31) and rotation drive device (22) are all electrically connected to the servo drive system.

10. A space attitude adjustment method for satellite testing, based on the space attitude adjustment device for satellite testing according to any one of claims 2 to 7, comprising the following steps: The free ends of the slings (32) are respectively connected to different ends of the test satellite; Adjusting the length of each sling (32) to adjust the pitch angle and roll angle of the test satellite to a test pitch angle and a test roll angle; Starting the rotation driving device (22) to drive the rotating connecting seat (1) to rotate as a whole, and adjusting the azimuth angle of the test satellite to the test azimuth angle; After the test satellite is stationary, the space attitude adjustment is completed.

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