A gas suspension-based stacked satellite separation simulation test system and method

Abstract

The application provides a gas suspension-based stacked satellite separation simulation test system and method, which comprises an air floating platform, a gas suspension assembly, a stacked satellite, a locking connection device and a final stage rocket body simulation platform; the stacked satellite is locked and connected with the final stage rocket body simulation platform through the locking connection device; the stacked satellite and the final stage rocket body simulation platform are both suspended in the space above the air floating platform through the gas suspension assembly; after the locking connection device is unlocked, the stacked satellite is separated from the final stage rocket body simulation platform. The application realizes zero-friction and zero-gravity simulation of ground test through gas suspension technology, and can realize on-orbit movement of the rocket final stage and the stacked satellite combination, accurately simulate on-orbit separation movement and improve test accuracy by being equipped with an attitude control system.

Description

TECHNICAL FIELD

[0001] The application relates to the field of separation test technology, in particular to a stacked satellite separation simulation test system and method based on air suspension. BACKGROUND

[0002] The separation technology of stacked flat plate satellites is a key technology for the successful launch of stacked satellites to the predetermined orbit, and the most critical is the near-field safety problem of stacked flat plate satellites. The stacked flat plate satellites are prone to near-field collision during the separation process, resulting in satellite damage. Therefore, during the development process, it is essential to carry out separation tests of stacked satellites to verify the correctness of the separation test method. The main difficulty in carrying out multi-satellite separation tests of stacked satellites on the ground is zero-gravity simulation. Because of the existence of the gravity field on the ground, the motion behavior of stacked satellites in space is completely different. Therefore, a test system that can overcome the influence of gravity is needed to complete the principle technology verification of stacked flat plate satellite separation on the ground.

[0003] The separation test process of stacked satellites is a typical multi-body motion process, and the separation test system is relatively complex, which needs to realize zero-gravity simulation and correctly apply the separation rotation speed. In the past, the suspension and other ways were used to simulate zero gravity, which could not completely eliminate the influence of friction. At the same time, the application of the separation speed used the fixed rotation shaft and other application methods, which could not realize the on-orbit motion simulation of stacked satellites.

[0004] Therefore, there is an urgent need to provide a separation test system that can realize zero-friction zero-gravity simulation, accurately simulate on-orbit separation motion, and improve test accuracy. SUMMARY

[0005] The purpose of the present application is to provide a stacked satellite separation simulation test system and method based on air suspension, which realizes zero-friction zero-gravity simulation of ground tests through air suspension technology, and can realize on-orbit motion of the rocket final stage and stacked satellite combination by being equipped with an attitude control system, accurately simulate on-orbit separation motion, and improve test accuracy.

[0006] To achieve the above purpose, the application provides a stacked satellite separation simulation test system based on air suspension, which comprises an air floating platform, an air suspension assembly, a stacked satellite, a locking connection device and a final stage rocket body simulation platform.

[0007] The stacked satellite is locked and connected with the final stage rocket body simulation platform through the locking connection device.

[0008] The stacked satellite and the final stage rocket body simulation platform are both suspended above the air floating platform through the air suspension assembly.

[0009] After the locking connection device is unlocked, the stacked satellite is separated from the final stage rocket body simulation platform.

[0010] The air suspension-based stacked satellite separation simulation test system as claimed in any one of the preceding claims, wherein a camera system is further arranged above the stacked satellite and the final-stage rocket body simulation platform, and the camera system is configured to capture a separation process of the stacked satellite and the final-stage rocket body simulation platform.

[0011] The air suspension-based stacked satellite separation simulation test system as claimed in any one of the preceding claims, wherein the locking connection device comprises a satellite adapter and a stacked satellite locking device.

[0012] The satellite adapter is fixedly connected to the final-stage rocket body simulation platform.

[0013] The stacked satellite is connected to the satellite adapter as a whole through the stacked satellite locking device.

[0014] The air suspension-based stacked satellite separation simulation test system as claimed in any one of the preceding claims, wherein an attitude thruster is fixedly connected to the final-stage rocket body simulation platform.

[0015] The attitude thruster is configured to drive the combination of the stacked satellite and the final-stage rocket body simulation platform to perform a steady-state rotational motion around a yaw direction about a center of mass of the combination.

[0016] The air suspension-based stacked satellite separation simulation test system as claimed in any one of the preceding claims, further comprising a platform control computer, wherein the platform control computer is in communication connection with the attitude thruster and the locking connection device.

[0017] The platform control computer is configured to send a control instruction to the attitude thruster and an unlocking instruction to the locking connection device.

[0018] The air suspension-based stacked satellite separation simulation test system as claimed in any one of the preceding claims, wherein an inertial measurement unit is arranged on the final-stage rocket body simulation platform.

[0019] The inertial measurement unit is configured to measure a motion attitude of the combination of the stacked satellite and the final-stage rocket body simulation platform on the air suspension platform, and feed back the measured motion attitude to the platform control computer.

[0020] The air suspension-based stacked satellite separation simulation test system as claimed in any one of the preceding claims, wherein the air suspension assembly comprises a plurality of air feet, a plurality of air cylinders and a plurality of air suspension control valves.

[0021] The air feet are in communication with the air cylinders through the air suspension control valves.

[0022] The air feet are arranged on the stacked satellite and the final-stage rocket body simulation platform.

[0023] After the air floating control valve is opened, the gas in the gas cylinder continuously flows out through the air foot to maintain the suspension of the stacked satellite and the final stage missile analog platform on the air floating platform.

[0024] The air-suspension-based stacked satellite separation simulation test system as described above, wherein the stacked satellite comprises a plurality of flat plate satellites, and the plurality of flat plate satellites are locked together by the locking connection device.

[0025] The air-suspension-based stacked satellite separation simulation test system as described above, wherein the flat plate satellite comprises a stacked satellite analog shell, a stacked satellite load-bearing column and a stacked satellite control unit.

[0026] The stacked satellite control unit is arranged in the stacked satellite analog shell.

[0027] The stacked satellite load-bearing column is fixedly connected to the outer wall of the stacked satellite analog shell.

[0028] The plurality of flat plate satellites are connected by the stacked satellite load-bearing column and locked together by the locking connection device.

[0029] The application further provides an air-suspension-based stacked satellite separation simulation test method applied to the air-suspension-based stacked satellite separation simulation test system, and the method comprises the following steps.

[0030] The motion attitude of the stacked satellite and the final stage missile analog platform combination on the air floating platform is measured.

[0031] According to the measured motion attitude, a control instruction is sent to the attitude jet pipe to control the jet of the attitude jet pipe, and the attitude jet pipe drives the stacked satellite and the final stage missile analog platform combination on the air floating platform to simulate the steady rotation motion of the combination around the combination mass center in the yaw direction.

[0032] When the speed of the steady rotation motion reaches a preset condition, the stacked satellite locking device is unlocked and the stacked satellite is released.

[0033] The motion image of the separation of the stacked satellite from the final stage missile analog platform under the action of the steady rotation angular velocity is collected in real time.

[0034] The application has the following beneficial effects:

[0035] (1) The test system of the application can effectively simulate the in-orbit separation motion process of the stacked satellite on the ground, and can realize frictionless zero-gravity simulation test, and can be used for analyzing the correctness of the in-orbit separation method of the stacked satellite and the near-field safety problem of the stacked flat plate satellite, thereby providing strong support for the development of the stacked satellite technology.

[0036] (2) The end-stage missile body simulation platform can realize frictionless movement in two-dimensional position and yaw three-plane freedom, and is also equipped with an inertial measurement unit and a platform control computer. The test system can realize two-dimensional position and yaw plane movement of the test system by controlling the attitude jet pipe, effectively simulate the on-orbit movement process of the stacked satellite, and improve the test accuracy. BRIEF DESCRIPTION OF DRAWINGS

[0037] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or prior art description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments described in the present application, and other drawings can also be obtained by those skilled in the art according to these drawings.

[0038] Figure 1 A structure schematic diagram of a stacked satellite separation simulation test system based on air suspension according to an embodiment of the present application.

[0039] Figure 2 A connection structure schematic diagram of a stacked satellite and an end-stage missile body simulation platform according to an embodiment of the present application.

[0040] Figure 3 A locked connection schematic diagram of a stacked satellite and an end-stage missile body simulation platform according to an embodiment of the present application.

[0041] Figure 4 An unlocked state schematic diagram of a locked connection device according to an embodiment of the present application.

[0042] Figure 5 A separation state schematic diagram of a stacked satellite and an end-stage missile body simulation platform according to an embodiment of the present application Figure 1 .

[0043] Figure 6 A separation state schematic diagram of a stacked satellite and an end-stage missile body simulation platform according to an embodiment of the present application Figure 2 .

[0044] Figure 7 A structure schematic diagram of a flat plate satellite according to an embodiment of the present application.

[0045] Figure 8 A plane three-freedom zero-gravity simulation equivalent platform schematic diagram used in the simulation test system of the present application.

[0046] Figure 9 A flow chart of a stacked satellite separation simulation test method based on air suspension according to an embodiment of the present application.

[0047] Reference numerals: 1-Air-float platform; 2-Air suspension component; 3-Stacked satellites; 4-Locking connection device; 5-Final stage rocket body simulation platform; 6-Platform control computer; 7-Attitude nozzle; 8-Camera system; 9-Inertial measurement unit; 10-Center of mass; 11-Planar moving platform; 12-Payload; 21-Air foot; 22-Air cylinder; 23-Air-float control valve; 31-Stacked satellite simulation shell; 32-Stacked satellite control unit; 33-Stacked satellite support column; 41-Satellite adapter; 42-Stacked satellite locking device; 421-Locking rod; 422-Connecting plate. Detailed Implementation

[0048] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0049] Example 1

[0050] like Figures 1-2 As shown, this application provides a stacked satellite separation simulation test system based on air suspension, including an air suspension platform 1, an air suspension component 2, stacked satellites 3, a locking connection device 4, and a final stage rocket body simulation platform 5; the stacked satellites 3 are locked to the final stage rocket body simulation platform 5 through the locking connection device 4; the stacked satellites 3 are stacked flat-panel satellites. Both the stacked satellite 3 and the final stage rocket body simulation platform 5 are suspended in the space above the air-bearing platform 1 by the air suspension component 2. The air suspension component 2 makes the stacked satellite 3 and the final stage rocket body simulation platform 5 float as a whole. The air suspension component 2 blows air towards the air-bearing platform 1, and an air film is formed between the air suspension component 2 and the air-bearing platform 1 to provide support for the combination of the stacked satellite 3 and the final stage rocket body simulation platform 5, thereby compensating for the gravity of the combination of the stacked satellite 3 and the final stage rocket body simulation platform 5. This enables frictionless motion and zero-gravity simulation tests of the two-dimensional position and yaw three-plane degrees of freedom of the stacked satellite 3 and the final stage rocket body simulation platform 5, improving the test accuracy of the test system for simulating the on-orbit separation motion of the stacked satellite 3. After the locking connection device 4 is unlocked, the stacked satellite 3 separates from the final stage rocket body simulation platform 5, thereby realizing the separation simulation test of the stacked satellite 3.

[0051] like Figure 1As shown, the air suspension-based stacked satellite separation simulation test system also comprises a camera system 8 arranged above the stacked satellite 3 and the final stage rocket body simulation platform 5, and the camera system 8 is used to shoot the separation process of the stacked satellite 3 and the final stage rocket body simulation platform 5, so as to collect the motion image of the separation of the stacked satellite 3 from the final stage rocket body simulation platform 5 under the action of the steady-state rotation angular velocity, and record the test data of the separation motion of the stacked satellite 3 in orbit.

[0052] As shown in Figure 2 The locking connection device 4 comprises a satellite adapter 41 and a stacked satellite locking device 42. The satellite adapter 41 is fixedly connected with the final stage rocket body simulation platform 5, and is fixedly connected to the side wall of the final stage rocket body simulation platform 5. The end of the stacked satellite locking device 42 is fixedly connected to the end of the satellite adapter 41 away from the final stage rocket body simulation platform 5, and the stacked satellite 3 is connected as a whole with the satellite adapter 41 through the stacked satellite locking device 42.

[0053] As shown in Figure 4 The stacked satellite locking device 42 comprises a connecting plate 422 and a locking pull rod 421. The connecting plate 422 is fixedly connected to the end of the satellite adapter 41 away from the final stage rocket body simulation platform 5, and the plane on which the connecting plate 422 is arranged is perpendicular to the air floating platform 1. The end of the locking pull rod 421 is rotatably connected to the connecting plate 422, and the locking pull rod 421 is locked to the outer wall of the stacked satellite 3. The end of the locking pull rod 421 away from the connecting plate 422 is locked by a locking device to realize the locking of the stacked satellite 3 and to ensure the overall rigidity of the stacked satellite locking device 42. The locking device can comprise an explosive bolt and a locking nut, and the locking nut is locked to the explosive bolt to realize the locking. When it is necessary to release the stacked satellite 3, the explosive bolt is broken, the one end of the locking pull rod 421 is separated from the stacked satellite 3, and the other end swings around the connecting plate 422, so as to release the stacked satellite 3 and to carry out the in-orbit separation test of the stacked satellite 3.

[0054] As shown in Figures 1-6 The attitude jet pipe 7 is fixedly connected to the final stage rocket body simulation platform 5. The attitude jet pipe 7 is used to drive the combination of the stacked satellite 3 and the final stage rocket body simulation platform 5 to perform a steady-state rotation motion around the combination center of mass 10 in the yaw direction. Preferably, the attitude jet pipe 7 comprises a plurality of attitude jet pipes 7 distributed on the side wall of the final stage rocket body simulation platform 5. The attitude jet pipe 7 is communicated with a gas source device, and the gas source device and the attitude jet pipe 7 are communicated through a control valve. The gas source device is used to provide a gas source to the attitude jet pipe 7. When the attitude jet pipe 7 receives the control instruction of the platform control computer 6, the control valve is opened, the gas source device delivers the gas source to the attitude jet pipe 7, and the attitude jet pipe 7 sprays the gas.

[0055] As shown in Figure 3The diagram shows the structure of the locking connection device 4 locking the stacked satellite 3 to the final stage rocket body simulation platform 5. The stacked satellite 3 is locked to the side of the final stage rocket body simulation platform 5.

[0056] like Figure 4 The diagram shows the unlocked state of the locking connection device 4, with the end of the locking connection device 4 separated from the stacked satellite 3.

[0057] like Figure 5 The diagram shows the locking connection device 4 in the swing-open state, with the stacked satellite 3 separated from the final stage rocket body simulation platform 5.

[0058] like Figure 6 The diagram shows the fully open locking connection device 4, with the individual flat satellites of the stacked satellites 3 separated from each other. It can be understood that before the locking connection device 4 is unlocked, a pre-tightening force is applied to press down the stacking satellite support columns 33 of the stacked satellites 3. After the locking connection device 4 is unlocked, the stacking satellite support columns 33 of the individual flat satellites naturally separate. During the separation of the stacked flat satellites, each flat satellite rotates around the center of mass 10 of the combined stacked satellites 3 and the final stage rocket body simulation platform 5 at the moment of separation. The tangential velocity of the circular motion of the flat satellites at different distances from the center of mass 10 is different. This achieves the simulation of the on-orbit motion of the stacked satellites 3.

[0059] like Figure 1 and 2 As shown, the stacked satellite separation simulation test system based on air suspension also includes a platform control computer 6, which is communicatively connected to the attitude nozzle 7 and the locking connection device 4. The platform control computer 6 is used to send control commands to the attitude nozzle 7 and unlocking commands to the locking connection device 4.

[0060] like Figure 1 and 2As shown, the last-stage rocket body simulation platform 5 is provided with an inertial measurement unit 9, which is used to measure the motion attitude of the combination of the stacked satellite 3 and the last-stage rocket body simulation platform 5 on the air floating platform 1, and feed back the measured motion attitude to the platform control computer 6. After the platform control computer 6 obtains the motion attitude of the combination of the stacked satellite 3 and the last-stage rocket body simulation platform 5 on the air floating platform 1, according to the motion attitude of the combination of the stacked satellite 3 and the last-stage rocket body simulation platform 5 on the air floating platform 1, the platform control computer 6 sends a control instruction to the attitude jet pipe 7 according to a pre-designed control program, and controls the attitude jet pipe 7 to drive the combination of the stacked satellite 3 and the last-stage rocket body simulation platform 5 on the air floating platform 1 to simulate the steady-state rotational motion of the combination around the center of mass 10 of the combination in the yaw direction. When the steady-state rotational motion speed meets the condition, i.e., reaches the preset value, the platform control computer 6 sends an unlocking instruction to the stacked satellite locking device 42, the stacked satellite locking device 42 is unlocked, and the stacked satellite 3 is released. Under the action of the steady-state rotational angular velocity, the stacked flat plate satellites gradually move away from the satellite adapter 41 combination and separate from each other by using the speed difference formed by the inertial difference of the stacked satellite 3. It can be understood that under the action of the steady-state rotational angular velocity, the stacked flat plate satellites gradually move away from the last-stage rocket body simulation platform 5, and separate from each other by using the speed difference formed by the inertial difference of the stacked flat plate satellites. When the stacked flat plate satellites separate, they rotate around the center of mass 10 of the combination of the stacked satellite 3 and the last-stage rocket body simulation platform 5 at the separation time. The flat plate satellites with different distances from the center of mass 10 have different tangential velocities of the circular motion around the center of mass 10, and thus generate a speed difference.

[0061] As shown in Figure 1 and 7 As shown, the air suspension assembly 2 includes a plurality of air feet 21, a plurality of air cylinders 22 and a plurality of air floating control valves 23; the air feet 21 are communicated with the air cylinders 22 through the air floating control valves 23; the air feet 21 are arranged on the stacked satellite 3 and the last-stage rocket body simulation platform 5; after the air floating control valves 23 are opened, the gas in the air cylinders 22 continuously flows out through the air feet 21, so as to maintain the suspension of the stacked satellite 3 and the last-stage rocket body simulation platform 5 on the air floating platform 1.

[0062] As a specific embodiment of the present application, the stacked satellite 3 includes a plurality of flat plate satellites, the plurality of flat plate satellites are stacked and locked together through the locking connection device 4.

[0063] As shown in Figure 7As shown, the flat plate satellite comprises: a stacked satellite simulation shell 31, a stacked satellite support column 33 and a stacked satellite control unit 32; the stacked satellite control unit 32 is arranged in the stacked satellite simulation shell 31; the stacked satellite support column 33 is fixedly connected to the outer wall of the stacked satellite simulation shell 31; a plurality of flat plate satellites are connected through the stacked satellite support column 33 and are locked together by the locking connection device 4. Specifically, the stacked satellite support columns 33 of two adjacent flat plate satellites are nested and connected along the length direction of the stacked satellite support column 33, the stacked satellite support columns 33 of a plurality of flat plate satellites are nested and connected at the head and tail, the nested stacked satellite support columns 33 are on a straight line, and the locking pull rod 421 of the locking connection device 4 is locked and connected to the nested stacked satellite support columns 33 of the stacked flat plate satellites, so as to lock and connect the plurality of stacked flat plate satellites together. The locking pull rod 421 is limited on the outer side of the stacked satellite support columns 33 of the plurality of flat plate satellites, and the end of the locking pull rod 421 is locked and connected to the stacked flat plate satellites through locking components such as locking bolts or latches. When the locking connection device 4 is unlocked, the stacked satellite 3 is released, and the stacked satellite support columns 33 of two adjacent flat plate satellites are separated to realize the separation of the flat plate satellites. The nesting stroke of the stacked satellite support columns 33 of two adjacent flat plate satellites realizes that the flat plate satellites do not collide with each other during the separation process, greatly improves the near-field separation safety of the stacked satellite 3, and protects the safety of the flat plate satellite.

[0064] As a specific embodiment of the present application, the stacked satellite control unit 32 comprises an attitude measurement unit and an air floating control algorithm. In the test process, the stacked satellite control unit 32 and the air floating control valve 23 are used to ensure that the gas in the gas cylinder 22 continuously maintains the suspension of the stacked satellite 3 on the air floating platform 1 through the air foot 21, so as to realize zero-gravity simulation.

[0065] As shown, Figure 8 As shown, it is a flat three-degree-of-freedom zero-gravity simulation equivalent platform schematic diagram used in the simulation test system of the present application. It can be understood that the main principle of the test system of the present application is that the air film is formed by the cooperation of the air foot 21 and the air floating platform 1, the supporting force is generated to compensate the gravity of the flat moving platform 11, the frictionless motion of the flat moving platform 11 in two-dimensional position and yaw three plane degrees of freedom is realized, and the combination of the stacked satellite 3 and the final stage missile simulation platform 5 is equivalent to the flat moving platform 11; the gravity of the combination of the stacked satellite 3 and the final stage missile simulation platform 5 is equivalent to the effective load 12. The stacked satellite separation simulation test platform based on the air suspension technology of the present application can realize frictionless zero-gravity simulation. The final stage missile simulation platform 5 can realize frictionless motion in two-dimensional position and yaw three plane degrees of freedom, and is provided with an inertial measurement unit 9 and a platform control computer 6. The arbitrary two-dimensional position and yaw plane motion of the test system can be realized through the control of the attitude jet pipe 7, and the in-orbit motion process of the stacked satellite 3 is effectively simulated.

[0066] Embodiment Two

[0067] As Figure 9 shown, the application also provides a gas suspension-based stacked satellite separation simulation test method, applied to a gas suspension-based stacked satellite separation simulation test system, the method comprising the following steps:

[0068] Step S1, measure the motion attitude of the stacked satellite and the final stage rocket body simulation platform combination on the air floating platform.

[0069] Specifically, the motion attitude of the stacked satellite and the final stage rocket body simulation platform combination on the air floating platform is measured by an inertial measurement unit, and the measured motion attitude of the stacked satellite and the final stage rocket body simulation platform combination on the air floating platform is fed back to the platform control computer.

[0070] Step S2, according to the measured motion attitude, send control instructions to the attitude jet pipe to control the jet of the attitude jet pipe.

[0071] Specifically, the platform control computer sends control instructions to the attitude jet pipe according to the measured motion attitude according to the pre-designed control program, to control the jet of the attitude jet pipe, so that the attitude jet pipe drives the combination of the stacked satellite and the final stage rocket body simulation platform to simulate the steady-state rotational motion of the combination around the mass center of the combination around the yaw direction on the air floating platform.

[0072] Step S3, the attitude jet pipe drives the combination of the stacked satellite and the final stage rocket body simulation platform to simulate the steady-state rotational motion of the combination around the mass center of the combination around the yaw direction on the air floating platform.

[0073] Step S4, when the speed of the steady-state rotational motion reaches the preset condition, the stacked satellite locking device is unlocked and releases the stacked satellite.

[0074] Specifically, when the speed of the steady-state rotational motion reaches the preset condition, the platform control computer sends an unlocking instruction to the stacked satellite locking device, the stacked satellite locking device is unlocked and releases the stacked satellite.

[0075] Step S5, real-time acquisition of the motion image of the stacked satellite separating from the final stage rocket body simulation platform under the action of the steady-state rotational angular velocity.

[0076] Specifically, the motion image of the stacked satellite separating from the final stage rocket body simulation platform under the action of the steady-state rotational angular velocity is acquired in real time by the camera system 8, which can be used to analyze the correctness of the on-orbit separation method of the stacked satellite and the near-field safety problem of the stacked satellite, and provide strong support for the development of the stacked satellite technology.

[0077] The beneficial effects achieved by the application are as follows:

[0078] (1) The test system of the application can effectively simulate the on-orbit separation movement process of the stacked satellite on the ground, and can realize frictionless zero-gravity simulation test, and can be used for analyzing the correctness of the on-orbit separation method of the stacked satellite and the near-field safety problem of the stacked flat plate satellite, thereby providing strong support for the development of the stacked satellite technology.

[0079] (2) The terminal rocket body simulation platform of the application can realize frictionless movement in two-dimensional position and yaw three planes, and the terminal rocket body simulation platform is also provided with an inertial measurement unit and a platform control computer, so that the arbitrary two-dimensional position and yaw plane movement of the test system can be realized by controlling the attitude jet pipe, the on-orbit movement process of the stacked satellite can be effectively simulated, and the test accuracy is improved.

[0080] In the description of the application, the terms "first", "second" are only used for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more features. In the description of the application, the meaning of "a plurality of" is two or more, unless otherwise specifically limited.

[0081] In the description of the application, the word "for example" is used to mean "serving as an example, instance, or illustration". Any embodiment described as "for example" in this application is not necessarily to be construed as preferred or advantageous over other embodiments. The following description is presented to enable any person skilled in the art to make and use the application. In the following description, details are set forth for the purpose of explanation. It will be appreciated that one of ordinary skill in the art can realize and implement the application without using these specific details. In other instances, well-known structures and processes are not described in detail in order to avoid obscuring the description of the application. Therefore, the present application is not intended to be limited to the embodiments shown, but is to be consistent with the widest scope consistent with the principles and features disclosed herein.

[0082] The above only describes the embodiments of the application and is not intended to limit the application. The application can have various changes and modifications for those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the application shall be included in the scope of the claims of the application.

Claims

1. A simulated experimental system for the separation of stacked satellites based on air suspension, characterized in that, This includes an air-bearing platform, air-suspended components, stacked satellites, locking and connecting devices, and a final stage rocket body simulation platform; The stacked satellites are locked to the final stage rocket body simulation platform via the locking connection device. Both the stacked satellite and the final stage rocket body simulation platform are suspended in the space above the air-bearing platform by the air-bearing component. After the locking connection device is unlocked, the stacked satellites separate from the final stage rocket body simulation platform; An attitude nozzle is fixedly connected to the final stage rocket body simulation platform; The attitude nozzle is used to drive the combination of the stacked satellite and the final stage rocket body simulation platform to perform steady-state rotation around the center of mass of the combination in the yaw direction.

2. The stacked satellite separation simulation test system based on air suspension according to claim 1, characterized in that, It also includes a camera system, which is positioned above the stacked satellites and the final stage rocket body simulation platform, and is used to capture the separation process of the stacked satellites from the final stage rocket body simulation platform.

3. The stacked satellite separation simulation test system based on air suspension according to claim 1, characterized in that, The locking connection device includes: a satellite adapter and a stacked satellite locking device; The satellite adapter is fixedly connected to the final stage rocket body simulation platform; The stacked satellites are connected to the satellite adapter as a whole via the stacked satellite locking device.

4. The stacked satellite separation simulation test system based on air suspension as described in claim 1, characterized in that, It also includes a platform control computer, which is communicatively connected to the attitude nozzle and the locking connection device; The platform control computer is used to send control commands to the attitude nozzle and unlock commands to the locking connection device.

5. The stacked satellite separation simulation test system based on air suspension according to claim 4, characterized in that, An inertial measurement unit is installed on the final stage rocket body simulation platform. The inertial measurement unit is used to measure the motion attitude of the combination of the stacked satellite and the final stage rocket body simulation platform on the air-bearing platform, and to feed back the measured motion attitude to the platform control computer.

6. The stacked satellite separation simulation test system based on air suspension according to claim 1, characterized in that, The air suspension assembly includes multiple air feet, multiple air cylinders, and multiple air suspension control valves; The air supply is connected to the air cylinder through the air flotation control valve; The air supply is installed on the stacked satellite and the final stage rocket body simulation platform; After the air-float control valve is opened, the gas in the gas cylinder flows out continuously through the air foot to maintain the stacked satellite and the final stage rocket body simulation platform suspended on the air-float platform.

7. The stacked satellite separation simulation test system based on air suspension according to claim 1, characterized in that, The stacked satellites include multiple flat-panel satellites, which are locked together by the locking connection device.

8. The stacked satellite separation simulation test system based on air suspension according to claim 7, characterized in that, The flat-panel satellite includes: a stacked satellite simulation shell, stacked satellite support columns, and a stacked satellite control unit; The stacked satellite control unit is housed within the stacked satellite simulation shell; The stacked satellite support columns are fixedly connected to the outer wall of the stacked satellite simulation shell; Multiple flat-panel satellites are connected by stacked satellite support columns and locked together by the locking connection device.

9. A simulation test method for the separation of stacked satellites based on air suspension, characterized in that, The method applied to the air-suspended stacked satellite separation simulation test system according to any one of claims 1-8 includes the following steps: The motion attitude of the stacked satellite and final stage rocket body simulation platform assembly on the air-bearing platform was measured. Based on the measured motion attitude, control commands are sent to the attitude nozzle to control the jetting of the attitude nozzle. The attitude nozzle drives the stacked satellite and the final stage rocket body simulation platform assembly on the air-bearing platform to simulate the steady-state rotational motion of the assembly around the center of mass of the assembly in orbit around the yaw direction. When the speed of steady-state rotational motion reaches a preset condition, the satellite stacking locking device unlocks and releases the stacked satellites; Real-time acquisition of motion images of stacked satellites separating from the final stage rocket body simulation platform under steady-state rotational angular velocity.

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