Ground test verification device suitable for separation of two satellites and detection method

Abstract

The invention belongs to the field of self-stacking satellite inter-satellite separation tests, and particularly relates to a ground test verification device suitable for two-satellite separation of satellites and a detection method, the ground test verification device comprises an upper satellite separation motion supporting frame, a suspension assembly, a counterweight adjusting system, a force monitoring unit and a buffer protection mechanism; the upper satellite separation movement supporting frame is formed by welding profile steel, a satellite two-axis rotary table is arranged under the upper satellite separation movement supporting frame, a gravity unloading device is fixedly installed at the top of the upper satellite separation movement supporting frame, and pulley pairs are fixedly installed at the four corners of the bottom of the gravity unloading device through pulley installation bases. The suspension assembly comprises four groups of independent steel wire ropes, and each group of steel wire ropes is correspondingly wound on one group of pulley pair. The suspension tool system is flexibly designed according to the mass and the boundary dimension of the two satellites, the four-point suspension mode and the adjustable balancing weight combination are combined, the two-satellite separation test requirements of the large satellite and the small satellite can be met at the same time, and the problem that in the prior art, the adaptability to the satellite scale is limited is solved.

Description

Technical Field

[0001] This invention belongs to the field of inter-satellite separation experiments for self-stacked satellites, specifically relating to a ground-based test verification device and detection method suitable for the separation of two satellites. Background Technology

[0002] With increasing demands for cost-effectiveness and efficiency in space launch missions, multiple satellite launches have become the mainstream method for building satellite constellations. In the traditional multiple satellite launch mode, multiple satellites are connected to the launch vehicle through independent satellite-rocket interfaces. This requires the launch vehicle to be equipped with multiple support and adaptation structures, which not only increases the complexity of the rocket design but also reduces the effective payload capacity due to the space and weight occupied by the interfaces, thus restricting launch economy.

[0003] To address these issues, self-stacking satellites have emerged. These satellites achieve direct stacking through inter-satellite connection and separation interfaces, connecting to the launch vehicle via a single satellite-rocket interface, significantly simplifying rocket design and improving launch efficiency. The inter-satellite unlocking and separation capability of this type of satellite is crucial for successful deployment after entering orbit, and its reliability needs to be verified through ground tests.

[0004] In the prior art, patent CN108001713A discloses a ground test method for the separation of two self-stacking satellites. This method uses a suspension system to achieve gravity unloading, adjusts the counterweight block to simulate a weightless environment, and monitors the separation process. While this method addresses the adaptation problem of traditional tests for stacked satellites to some extent, it still has limitations: First, the counterweight design and stroke control of the suspension system have limited adaptability to satellites of different masses and sizes, especially for large satellites or satellites with special shapes, where the gravity unloading accuracy is insufficient. Second, the center of mass adjustment process lacks real-time monitoring and dynamic calibration mechanisms, making it difficult to ensure the consistency of the lateral center of mass of the separated body with its on-orbit state. Third, the safety limiting measures for the separation motion are not refined enough, and the calculation standard for the safe distance between the counterweight block and the buffer pad is not clearly defined, posing a collision risk.

[0005] Therefore, given the diversity of self-stacking satellites (including large and small satellites), there is an urgent need for a ground-based experimental verification method that is more adaptable, has higher simulation accuracy, and is more reliable in order to accurately verify the effectiveness of the inter-satellite separation function. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the purpose of this invention is to provide a ground-based test verification device and testing method suitable for the separation of two satellites.

[0007] According to the present invention, a ground test and verification device suitable for the separation of two satellites is provided, comprising an upper satellite separation motion support frame, a suspension assembly, a counterweight adjustment system, a force monitoring unit, and a buffer protection mechanism; The satellite separation motion support frame is made of welded steel, with a satellite two-axis turntable set directly below it and a gravity unloading device fixedly installed on top. At the four corners of the bottom of the gravity unloading device, pulley pairs are fixedly installed through pulley mounting seats. The suspension assembly includes four independent steel wire ropes, each set of steel wire ropes being wound around a set of pulley pairs. The pulley pairs include an inner pulley and an outer pulley. The inner pulley is located near the center of the gravity unloading device, and the outer pulley is located at the edge of the gravity unloading device. Turnbuckles are connected in series on the steel wire ropes. One end of the steel wire rope is connected to the lifting point of the external interface tooling of the upper star, and the other end is connected to the counterweight adjustment system after passing through the outer pulley and the inner pulley in sequence. The counterweight adjustment system includes four independently set counterweight blocks, each counterweight block being connected to the end of the wire rope away from the external interface tooling of the upper satellite; it also includes the external interface tooling of the upper satellite, which includes the lifting device connector of the upper satellite and its local counterweight. The lifting device connector is installed on the surface of the upper satellite, and the lifting device connector is provided with a turnbuckle connection interface and an interface for the local counterweight of the transverse center of gravity of the upper satellite separator. The force monitoring unit includes four force gauges, each of which is connected in series with the corresponding wire rope. The buffer protection mechanism includes a buffer pad set on the ground, which is located directly below the counterweight.

[0008] Furthermore, the turnbuckle is used to adjust the length of the wire rope to achieve the level adjustment of the upper star separator, and the level adjustment accuracy is better than 1mm.

[0009] Furthermore, the steel profile has sufficient rigidity to avoid deformation affecting the test accuracy, and the upper satellite separation motion support frame is used to provide spatial guidance for the upper satellite separation body during the separation motion.

[0010] Furthermore, the satellite two-axis turntable is used to set the relative position of the upper and lower satellite assembly relative to the ground separation test verification device, and to adjust the levelness of the upper and lower satellite separation surfaces.

[0011] This invention also provides a ground-based test method for detecting the separation of two satellites, comprising the following steps: Step S1: Construct a ground-based test and verification device; Step S2: Perform mass and lateral center of gravity tests on the satellite separation body with the lifting device connector. Adjust the lateral center of gravity by adding local counterweights to the lifting device connector so that the lateral center of gravity of the satellite separation body with the local counterweights of the lifting device connector is consistent with that of the satellite when it separated in orbit. Step S3: Calculate the target mass of the counterweight based on the mass and lateral centroid data of the satellite separation body, assemble the counterweight and connect it to the suspension system; Step S4: Perform a trial lift of the upper satellite separation body, adjust the turnbuckle to ensure that the horizontality of the upper satellite separation body is better than 1mm, record the initial tension values ​​of the four force gauges, and mark the relative positions of the upper satellite and the upper satellite separation motion support frame. Step S5: Disassemble the upper satellite separator, complete the docking of the upper and lower satellites, and fix the two satellite assemblies by a two-axis turntable or other positioning fixtures, so that the upper satellite returns to the position marked in step S4 and the horizontality of the separation surface is better than 1mm. Step S6: Reconnect the satellite separator to the suspension system and confirm that the tension values ​​of the four force gauges deviate from the initial values ​​in step S4 by less than 5%. Step S7: Start the camera recording equipment, power on the satellite to unlock the inter-satellite connection device, and record the motion process of the satellite separation body until it hovers stably. Step S8: After the test is completed, the satellite is powered off, the suspension connection is removed, and the test equipment is retrieved.

[0012] Furthermore, in step S2, during the lateral center of gravity test, the distribution position and mass of the local counterweights on the lifting device connector can be adjusted to achieve the lateral center of gravity adjustment of the satellite separator with the lifting device connector.

[0013] Furthermore, in step S3, the mass calculation of the four counterweights satisfies: FA+FB+FC+FD=M1; Where M1 is the sum of the mass of the satellite separation body and the contribution of pulley friction, and M1 must be greater than the total mass of the satellite separation body with the lifting device and the lateral counterweight in step S2, but not exceed 1.05 times the total mass; FA is the suspension force of the suspension point under the suspension mode at point A in the satellite suspension separation system; FB is the suspension force of the suspension point under the suspension mode at point B in the satellite suspension separation system; FC is the suspension force of the suspension point under the suspension mode at point C in the satellite suspension separation system; FD is the suspension force of the suspension point under the suspension mode at point D in the satellite suspension separation system. (FA+FB)×X1=(FC+FD)×X2; (FA+FD)×Y1=(FB+FC)×Y2; Where X1 is the distance from the point of application of the resultant force of the suspension force combination (FA+FB) to the lateral center of mass of the upper satellite separation body; X2 is the distance from the point of application of the resultant force of the suspension force combination (FC+FD) to the lateral center of mass of the upper satellite separation body; Y1 is the distance from the point of application of the resultant force of the suspension force combination (FA+FD) to the lateral center of mass of the upper satellite separation body; Y2 is the distance from the point of application of the resultant force of the suspension force combination (FB+FC) to the lateral center of mass of the upper satellite separation body.

[0014] Furthermore, in step S3, the suspension force FA = (X ± ΔX) kg is controlled, where X is 0.25 × M1, to determine the mass of the four counterweights.

[0015] Furthermore, in step S4, the initial distance between the counterweight and the buffer pad is adjusted to satisfy: minimum safe distance < initial distance < rising limit height, where the minimum safe distance is the safe distance between the upper and lower stars after the two stars separate, and the rising limit height is the safe distance between the upper star and the top of the upper star separation motion support frame (1).

[0016] Furthermore, in step S6, if the force value of the force gauge deviates from the initial value in step S4 by more than or equal to 5%, the mass of the turnbuckle and / or the counterweight needs to be readjusted until the deviation is less than 5%.

[0017] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention flexibly designs a suspension fixture system based on the mass and dimensions of the two satellites, and combines a four-point suspension method with adjustable counterweights to simultaneously meet the separation test requirements of both large and small satellites, thus solving the problem of limited adaptability of existing technologies to satellite scale.

[0018] 2. This invention monitors the lifting force in real time using force gauges at four suspension points. Combined with center of mass testing and counterweight adjustment, it ensures that the resultant force of the four suspension points accurately passes through the transverse center of mass of the satellite separation body. Furthermore, the total weight of the counterweight is slightly greater than the sum of the weight of the satellite separation body and the friction of the pulleys. This can more realistically simulate the separation motion state under weightlessness in orbit and improve the reliability of the test data.

[0019] 3. This invention avoids the risk of collision during the separation process by limiting the safe distance between the counterweight and the ground buffer pad to simultaneously meet the requirements of "greater than the minimum safe distance after the two stars separate" and "not exceeding the limit height of the top of the suspension fixture". This double limiting measure makes the safety control more refined than the existing technology. Attached Figure Description

[0020] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a diagram showing the ground test status of the two satellites before separation according to the present invention. Figure 2 This is a diagram showing the ground test status after the separation of the two satellites according to the present invention; Figure 3 This is a schematic diagram of the four-point suspension force transmission path of the present invention; Figure 4 This is a diagram showing the relationship between the centroid of the separated body and the suspension point in this invention. The following are the labeling elements in the figure: 1. Satellite separation motion support frame; 2. Satellite two-axis turntable; 3. Gravity unloading device; 4. Steel wire rope; 5. Turnbuckle; 6. Force gauge; 7. Inner pulley; 8. Outer pulley; 9. Counterweight; 10. Buffer pad; 11. Satellite external interface tooling. Detailed Implementation

[0021] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0022] like Figure 1-2 As shown, the present invention provides a ground test verification device suitable for the separation of two satellites, including an upper satellite separation motion support frame 1, a suspension assembly, a counterweight adjustment system, a force monitoring unit, and a buffer protection mechanism.

[0023] The upper satellite separation motion support frame 1 is welded from structural steel. The structural steel has sufficient rigidity to avoid deformation affecting the test accuracy. The upper satellite separation motion support frame 1 serves as the load-bearing foundation of the device. The upper satellite separation motion support frame 1 provides spatial guidance for the upper satellite separation body during separation motion. The satellite two-axis turntable 2 is set directly below the upper satellite separation motion support frame 1. The lower satellite separation body is set on the top of the satellite two-axis turntable 2. The gravity unloading device 3 is fixedly installed on the top of the upper satellite separation motion support frame 1. The four corners of the bottom of the gravity unloading device 3 are all fixedly installed with pulley pairs through pulley mounting seats.

[0024] The suspension assembly includes four independent sets of steel wire ropes 4 and pulley pairs. Each pulley pair includes an inner pulley 7 and an outer pulley 8. The inner pulley 7 is located near the center of the gravity unloading device 3, and the outer pulley 8 is located at the edge of the gravity unloading device 3. Steel wire ropes 4 are wound around the inner pulley 7 and the outer pulley 8. Turnbuckles 5 are also connected in series on the steel wire ropes 4. The turnbuckles 5 are used to adjust the length of the steel wire ropes 4 to achieve the horizontal adjustment of the upper satellite separation body. The horizontal adjustment accuracy is better than 1mm. One end of the steel wire rope 4 is connected to the lifting point of the upper satellite's external interface tooling. The other end of the steel wire rope 4 is wound around the outer pulley 8 and the inner pulley 7 in sequence and then fixedly connected to the counterweight block 9 to form a force-saving transmission structure. The suspension assembly adopts a four-point suspension layout, and the four suspension points are distributed in a rectangle.

[0025] The counterweight adjustment system includes four independently set counterweight blocks 9, which are connected to the upper satellite separator via steel wire ropes 4. The counterweight blocks 9 are used to provide the balancing force for gravity unloading. It also includes an upper satellite external interface fixture 11, which includes the upper satellite's lifting device connector and its local counterweight. The lifting device connector is installed on the surface of the upper satellite, and the lifting device connector is provided with a connection interface of turnbuckle 5 and an interface for the local counterweight of the transverse center of gravity of the upper satellite separator.

[0026] The force monitoring unit includes four force gauges 6, each of which is connected in series with the corresponding steel wire rope 4. The force gauges 6 are used to monitor the tension at each suspension point in real time and to verify the accuracy of the counterweight adjustment.

[0027] The buffer protection mechanism includes a buffer pad 10 set on the ground, which is directly below the counterweight 9 and is used to absorb the impact force of the counterweight 9 falling.

[0028] like Figure 3-4 As shown, the present invention provides a test method for a ground-based experimental verification device suitable for the separation of two satellites, comprising the following steps: Step S1: Construct a ground test and verification device, including an upper satellite separation motion support frame 1, a suspension assembly, a counterweight adjustment system, a force monitoring unit, and a buffer protection mechanism; Step S2: First, perform a mass test on the spacecraft separating body without the lifting harness connector and a lateral center of gravity test parallel to the separation surface. Based on the mass and lateral center of gravity test results without the lifting harness connector, further composite calculations are needed to include the mass of the unloaded propellant and other components, and to exclude the tooling mass, so that the composite calculation state is consistent with the state before on-orbit separation. According to the calculation results, add local counterweights to the lifting harness connector of the spacecraft separating body, and perform mass and lateral center of gravity tests again on the spacecraft separating body with the lifting harness connector, and adjust the local counterweights on the lifting harness connector so that the lateral center of gravity of the spacecraft separating body with the lifting harness connector is consistent with the lateral center of gravity during on-orbit separation. When testing the lateral center of gravity, the distribution position and mass of the local counterweights on the lifting harness connector can be adjusted to achieve the adjustment of the lateral center of gravity of the spacecraft separating body with the lifting harness connector.

[0029] Step S3: Calculate the target mass of counterweight 9 based on the mass and lateral center of gravity data of the upper star separation body with local counterweight lifting device connector, assemble counterweight 9 and connect it to the suspension system; The mass calculation of the four counterweights 9 satisfies: FA+FB+FC+FD=M1; Where M1 is the sum of the mass of the satellite separation body and the contribution of pulley friction, and M1 must be greater than the total mass of the satellite separation body with the lifting device and the lateral counterweight in step S2, but not exceed 1.05 times the total mass; FA is the suspension force of the suspension point under the suspension mode at point A in the satellite suspension separation system; FB is the suspension force of the suspension point under the suspension mode at point B in the satellite suspension separation system; FC is the suspension force of the suspension point under the suspension mode at point C in the satellite suspension separation system; FD is the suspension force of the suspension point under the suspension mode at point D in the satellite suspension separation system. (FA+FB)×X1=(FC+FD)×X2; (FA+FD)×Y1=(FB+FC)×Y2; Where X1 is the distance from the point of application of the resultant force of the suspension force combination (FA+FB) to the lateral center of mass of the upper satellite separation body; X2 is the distance from the point of application of the resultant force of the suspension force combination (FC+FD) to the lateral center of mass of the upper satellite separation body; Y1 is the distance from the point of application of the resultant force of the suspension force combination (FA+FD) to the lateral center of mass of the upper satellite separation body; Y2 is the distance from the point of application of the resultant force of the suspension force combination (FB+FC) to the lateral center of mass of the upper satellite separation body. Since the solution for the four-point suspension has infinitely many elements, in order to facilitate the adjustment of the level of the four suspension force components, the suspension force FA = (X ± △X) kg is controlled, where X can be 0.25 × M1. According to the calculation formula, the four matching suspension components can be obtained, and thus the mass of the four counterweights 9 should be determined. Step S4: Perform a trial lift of the satellite separation body, adjust the turnbuckle to make the horizontality of the satellite separation body better than 1mm, record the initial tension values ​​of the four force gauges 6, and mark the relative position of the satellite and the support frame. During the trial lift, the initial distance between the counterweight 9 and the buffer pad 10 needs to be adjusted to meet the following requirements: Minimum safe distance < initial distance < maximum ascent height Among them, the minimum safe distance is the safe distance between the upper and lower satellites after the two satellites separate, and the maximum ascent height is the safe distance between the upper satellite and the top of the support frame. Step S5: Disassemble the upper satellite separator, complete the docking of the upper and lower satellites, and fix the two satellite assemblies by a two-axis turntable or other positioning fixtures, so that the upper satellite returns to the position marked in step S4 and the horizontality of the separation surface is better than 1mm. Step S6: Reconnect the satellite separator to the suspension system and confirm that the tension values ​​of the four force gauges 6 deviate from the initial values ​​in step S4 by less than 5%. Step S7: Start the camera recording equipment, power on the satellite to unlock the inter-satellite connection device, and record the motion process of the satellite separation body until it hovers stably. Step S8: After the test is completed, the satellite is powered off, the suspension connection is removed, and the test equipment is retrieved.

[0030] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0031] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A ground-based test and verification device suitable for the separation of two satellites, characterized in that, Includes a satellite separation motion support frame (1), a suspension assembly, a counterweight adjustment system, a force monitoring unit, and a buffer protection mechanism; The satellite separation motion support frame (1) is made of welded steel. A satellite two-axis turntable (2) is set directly below it, and a gravity unloading device (3) is fixedly installed on the top. At the four corners of the bottom of the gravity unloading device (3), pulley pairs are fixedly installed through pulley mounting seats. The suspension assembly includes four independent steel wire ropes (4), each set of steel wire ropes (4) is wound around a set of pulley pairs, the pulley pairs include an inner pulley (7) and an outer pulley (8), the inner pulley (7) is set close to the center of the gravity unloading device (3), the outer pulley (8) is located at the edge of the gravity unloading device (3), turnbuckles (5) are connected in series on the steel wire ropes (4), one end of the steel wire rope (4) is connected to the lifting point of the external interface tooling of the upper star, and the other end is connected to the counterweight adjustment system after passing through the outer pulley (8) and the inner pulley (7) in sequence; The counterweight adjustment system includes four independently set counterweight blocks (9), and the counterweight blocks (9) are connected to the end of the wire rope (4) away from the external interface tooling of the upper satellite; it also includes the external interface tooling of the upper satellite (11), which includes the lifting device connector of the upper satellite and its local counterweight. The lifting device connector is installed on the surface of the upper satellite, and the lifting device connector is provided with a connection interface of turnbuckle (5) and an interface of the local counterweight of the transverse center of mass of the upper satellite separator. The force monitoring unit includes four force gauges (6), each of which is connected in series in the corresponding wire rope (4); The buffer protection mechanism includes a buffer pad (10) set on the ground, which is located directly below the counterweight (9).

2. The ground-based test and verification device for satellite separation according to claim 1, characterized in that, The turnbuckle (5) is used to adjust the length of the wire rope (4) to achieve the horizontal adjustment of the upper star separator, and the horizontal adjustment accuracy is better than 1mm.

3. The ground-based test and verification device for satellite separation according to claim 1, characterized in that, The steel profile has sufficient rigidity to avoid deformation affecting the test accuracy. The upper satellite separation motion support frame (1) is used to provide spatial guidance for the upper satellite separation body during the separation motion.

4. The ground-based test and verification device for satellite separation according to claim 1, characterized in that, The satellite two-axis turntable (2) is used to set the relative position of the upper and lower satellite assembly relative to the ground separation test verification device, and to adjust the levelness of the upper and lower satellite separation surface.

5. The ground-based test and detection method for the separation of two satellites according to any one of claims 1-4, characterized in that, Includes the following steps: Step S1: Construct a ground-based test and verification device; Step S2: Perform mass and lateral center of gravity tests on the satellite separation body with the lifting device connector. Adjust the lateral center of gravity of the satellite separation body by adding local counterweights to the lifting device connector so that the lateral center of gravity of the satellite separation body with the lifting device connector is consistent with that of the satellite when it separated in orbit. Step S3: Calculate the target mass of the counterweight (9) based on the mass and lateral centroid data of the satellite separator, assemble the counterweight (9) and connect it to the suspension system; Step S4: Perform a trial lift of the upper satellite separation body, adjust the turnbuckle (5) to make the horizontality of the upper satellite separation body better than 1mm, record the initial tension values ​​of the four force gauges (6), and mark the relative positions of the upper satellite and the upper satellite separation motion support frame (1). Step S5: Disassemble the upper satellite separator, complete the docking of the upper and lower satellites, and fix the two satellite assemblies by a two-axis turntable or other positioning fixtures, so that the upper satellite returns to the position marked in step S4 and the horizontality of the separation surface is better than 1mm. Step S6: Reconnect the satellite separator to the suspension system and confirm that the tension values ​​of the four force gauges (6) deviate from the initial values ​​in step S4 by less than 5%; Step S7: Start the camera recording equipment, power on the satellite to unlock the inter-satellite connection device, and record the motion process of the satellite separation body until it hovers stably. Step S8: After the test is completed, the satellite is powered off, the suspension connection is removed, and the test equipment is retrieved.

6. The ground-based test and detection method for satellite separation according to claim 5, characterized in that, In step S2, during the lateral center of gravity test, the lateral center of gravity of the satellite separator with the lifting device can be adjusted by adjusting the distribution position and mass of the local counterweights on the lifting device connector.

7. The ground-based test and detection method for satellite separation according to claim 5, characterized in that, In step S3, the mass calculation of the four counterweights (9) satisfies: FA+FB+FC+FD=M1; Where M1 is the sum of the mass of the satellite separation body and the contribution of pulley friction, and M1 must be greater than the total mass of the satellite separation body with the lifting device and the lateral counterweight in step S2, but not exceed 1.05 times the total mass; FA is the suspension force of the suspension point under the suspension mode at point A in the satellite suspension separation system; FB is the suspension force of the suspension point under the suspension mode at point B in the satellite suspension separation system; FC is the suspension force of the suspension point under the suspension mode at point C in the satellite suspension separation system; FD is the suspension force of the suspension point under the suspension mode at point D in the satellite suspension separation system. (FA+FB)×X1=(FC+FD)×X2; (FA+FD)×Y1=(FB+FC)×Y2; Where X1 is the distance from the point of application of the resultant force of the suspension force combination (FA+FB) to the lateral center of mass of the upper satellite separation body; X2 is the distance from the point of application of the resultant force of the suspension force combination (FC+FD) to the lateral center of mass of the upper satellite separation body; Y1 is the distance from the point of application of the resultant force of the suspension force combination (FA+FD) to the lateral center of mass of the upper satellite separation body; Y2 is the distance from the point of application of the resultant force of the suspension force combination (FB+FC) to the lateral center of mass of the upper satellite separation body.

8. The ground-based test and detection method for satellite separation according to claim 5, characterized in that, In step S3, the suspension force FA = (X ± △X) kg is controlled, where X is 0.25 × M1, to determine the mass of the four counterweights (9).

9. The ground-based test and detection method for satellite separation according to claim 5, characterized in that, In step S4, the initial distance between the counterweight (9) and the buffer pad (10) is adjusted to satisfy the following: minimum safe distance < initial distance < maximum height, where the minimum safe distance is the safe distance between the upper and lower stars after the two stars separate, and the maximum height is the safe distance between the upper star and the top of the upper star separation motion support frame (1).

10. The ground-based test and detection method for satellite separation according to claim 5, characterized in that, In step S6, if the force value of the force gauge deviates from the initial value in step S4 by more than or equal to 5%, the mass of the turnbuckle and / or counterweight needs to be readjusted until the deviation is less than 5%.

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