Ground simulation satellite and three-axis mass center fine adjustment mechanism thereof

Abstract

The invention discloses a ground simulation satellite and a triaxial centroid fine tuning mechanism thereof, comprising a satellite integral frame, the top of the satellite integral frame is provided with a tungsten filament clamping member housing, the interior of the satellite integral frame is provided with a centroid fine tuning mechanism, the top of the centroid fine tuning mechanism is provided with a horizontal centroid adjusting mass block, and the horizontal centroid adjusting mass block is provided with a tungsten filament clamping member housing. A horizontal mass center adjusting mass block base is mounted on the lower surface of the horizontal mass center adjusting mass block; the three-axis adjusting structure is arranged, the adjusting direction of the horizontal mass center adjusting mechanism is arranged along the X-axis and the Y-axis of the satellite, the horizontal direction position of the mass block can be adjusted, then the mass center of the satellite in the X-axis and the Y-axis is adjusted, the adjusting direction of the vertical mass center adjusting mechanism is arranged along the Z-axis of the satellite, and the vertical direction position of the mass block can be adjusted. And the horizontal mass center adjusting mechanism and the vertical mass center adjusting mechanism are matched with each other, so that three-axis adjustment is realized.

Description

Technical Field

[0001] The invention relates to the field of a satellite center of mass adjustment mechanism, in particular to a ground simulation satellite and a three-axis center of mass fine-tuning mechanism thereof. Background Art

[0002] As a cutting-edge, innovative, leading and challenging scientific and technological field, space science plays a vital role in the process of the national innovation-driven development strategy. In recent years, with the development and launch of space science satellites such as the dark matter detection satellite "Wukong", the drag-free technology test satellite "Taiji No. 1", "Tianqin No. 1" and the solar exploration science and technology test satellite "Xihe", my country's space science has greatly enhanced its international influence. Drag-free satellites are key platforms for implementing tasks such as gravitational wave detection and gravity field measurement. However, satellites are high-value products with high scientific and technological content. They use low-quality and high-strength materials, have high production costs, and carry high-precision instruments. It is often impossible to provide a real satellite for testing, so it is necessary to design a simulated satellite for testing. However, simulated satellites usually use ordinary materials, which leads to the problem of center of mass deviation in simulated satellites. Therefore, it is necessary to first build a simulation system on the ground to verify the effectiveness of its control system.

[0003] In order to eliminate the centroid displacement deviation of the ground simulation satellite caused by the installation as much as possible, it is necessary to design a centroid fine-tuning mechanism. In order to ensure that the ground simulation satellite remains horizontal as much as possible, it is necessary to design a horizontal centroid adjustment mechanism. If the satellite centroid and the thrust generated by the micro-thruster are not on the same horizontal plane, it will cause the tilt horizontal coupling effect, that is, the satellite structure not only swings around the suspension point under the action of the micro-thruster, but also produces a rotational motion with its own centroid as the center, thereby affecting the detection accuracy of the grating displacement sensor for the displacement between the satellite and the inspection mass, so it is necessary to design a vertical centroid adjustment mechanism. The current satellite centroid adjustment mechanism mainly has the following problems: 1. Most satellite centroid adjustment mechanisms disclosed in the prior art are mainly applicable to in-orbit satellites. The high-precision centroid adjustment system of the in-orbit satellite is to achieve high-precision centroid adjustment of the in-orbit satellite, but the system is too complicated and is not suitable for the centroid adjustment task requirements of ground satellites; 2. The satellite centroid adjustment mechanism disclosed in the prior art adopts a screw slide rail structure, which can only adjust the centroid of one axis, so three sets of screw slide rail structures are required on the three axes respectively, and this centroid adjustment mechanism greatly occupies the internal space of the satellite.

[0004] In summary, by innovating the existing satellite centroid adjustment mechanism and designing the centroid fine-tuning mechanism based on the mechanism of the ground-simulated satellite, a ground-simulated satellite and its three-axis centroid fine-tuning mechanism are proposed. The centroid adjustment in three axial directions is realized simultaneously, which can facilitate the fine-tuning of the satellite centroid, greatly reduce the occupied space volume of the satellite, facilitate the assembly with the satellite, and avoid the interference problem relative to the simulated satellite. Summary of the Invention

[0005] The purpose of the present invention is to provide a ground-simulated satellite and its three-axis centroid fine-tuning mechanism to solve the problems raised in the above background technology.

[0006] To achieve the above purpose, the present invention provides the following technical solutions: A three-axis centroid fine-tuning mechanism for a ground-simulated satellite includes a satellite overall frame. Inside the satellite overall frame, a centroid fine-tuning mechanism is installed. On the top of the centroid fine-tuning mechanism, a horizontal centroid adjustment mass block is installed, and on the lower surface of the horizontal centroid adjustment mass block, a horizontal centroid adjustment mass block base is installed. At the bottom of the horizontal centroid adjustment mass block base, a horizontal centroid adjustment mass block fixed base is fixedly installed. Below the horizontal centroid adjustment mass block fixed base, a vertical centroid adjustment mechanism housing is installed. On the left and right sides of the vertical centroid adjustment mechanism housing, vertical centroid adjustment mechanism knobs are connected. At the bottom of the vertical centroid adjustment mechanism housing, a vertical centroid adjustment mechanism base is fixedly installed. On the left side of the horizontal centroid adjustment mass block base, a horizontal X-axis centroid adjustment knob is installed. On the surface center line of the vertical centroid adjustment mechanism base, a vertical centroid adjustment mechanism lifting screw is vertically arranged. At the top of the vertical centroid adjustment mechanism lifting screw, a vertical centroid adjustment mass block is installed.

[0007] As an implementation manner of the present invention, wall boxes are installed on the outer walls around the centroid fine-tuning mechanism. Inside the wall boxes, oil bags are installed. On one side of the wall box, a sealed interface is integrally provided, and at the port of the sealed interface, a first oil pipe is connected. At the end of the first oil pipe away from the sealed interface, an oil pump is installed. The inlet end of the oil pump is connected to a second oil pipe. The oil bag is interconnected with the first oil pipe through the sealed interface. The first oil pipe is interconnected with the second oil pipe through the oil pump. At the lower end of the second oil pipe, an oil pipe box is installed. On the top of the oil pipe box, a connection port is integrally provided. The oil pipe box is interconnected with the second oil pipe through the connection port. A bottom cylinder is installed on the outside of the oil pipe box.

[0008] As an implementation manner of the present invention, the vertical centroid adjustment mechanism lifting screw and the vertical centroid adjustment mechanism knob are in a meshing structure.

[0009] As an embodiment of the present invention, a horizontal Y-axis centroid adjustment knob is provided on the back of the horizontal centroid adjustment mass block base, and a fixed base connecting member is installed outside the horizontal Y-axis centroid adjustment knob.

[0010] As an embodiment of the present invention, horizontal Y-axis centroid adjustment fixing bolts for fixed installation are provided on both the left and right sides of the horizontal centroid adjustment mass block base, and a horizontal X-axis centroid adjustment fixing bolt is provided above the horizontal centroid adjustment mass block.

[0011] As an embodiment of the present invention, a horizontal X-axis centroid adjustment knob and a mass block base connecting member are provided outside the horizontal X-axis centroid adjustment knob.

[0012] A ground-simulated satellite includes a satellite overall frame, and a tungsten wire clamping member housing is installed on the top of the satellite overall frame; A controller is installed on the left side inside the satellite overall frame, micro thrusters are installed on the outside of the satellite overall frame, a nitrogen gas storage tank is installed in the middle inside the satellite overall frame, a power supply is installed on the right side of the nitrogen gas storage tank, laser displacement sensors are installed on both the left and right sides of the bottom of the satellite overall frame, and a six-degree-of-freedom displacement table is installed at the bottom of the satellite overall frame. A wedge-shaped block is installed inside the tungsten wire clamping member housing, a tungsten wire is inserted through the wedge-shaped block, and a fastening bolt for suspension connection is provided at the bottom of the tungsten wire clamping member housing.

[0013] As an embodiment of the present invention, the micro thrusters are distributed in a cross shape with respect to the symmetry center line of the satellite overall frame.

[0014] As an embodiment of the present invention, the tungsten wire clamping member housing is connected to the satellite overall frame through a fastening bolt, and the lower end of the tungsten wire is fixedly connected to the inside of the wedge-shaped block.

[0015] As an embodiment of the present invention, the six-degree-of-freedom displacement table is movably connected to the bottom of the satellite overall frame.

[0016] Compared with the prior art, the beneficial effects of the present invention are: By setting up a three-axis adjustment structure, where the three-axis adjustment includes a vertical centroid adjustment mechanism and a horizontal centroid adjustment mechanism. The adjustment direction of the horizontal centroid adjustment mechanism is arranged along the X and Y axes of the satellite, which can adjust the horizontal position of the mass block, thereby adjusting the centroid of the satellite in the X and Y directions. The adjustment direction of the vertical centroid adjustment mechanism is arranged along the Z axis of the satellite, which can adjust the vertical position of the mass block, thereby adjusting the centroid of the satellite in the Z direction. The horizontal centroid adjustment mechanism and the vertical centroid adjustment mechanism cooperate with each other to achieve three-axis adjustment. The vertical centroid adjustment mechanism is mainly that the vertical centroid adjustment mechanism knob is connected to the vertical centroid adjustment mechanism lifting screw through a bevel gear set, so that when the vertical centroid adjustment mechanism knob is rotated, the vertical centroid adjustment mechanism lifting screw can be driven to rotate simultaneously. The horizontal centroid adjustment mass block fixed base is fixedly connected to the vertical centroid adjustment mechanism housing through bolts. The vertical centroid adjustment mechanism knob is connected through a reserved hole on the vertical centroid adjustment mechanism housing. The vertical centroid adjustment mechanism housing is fixedly connected to the vertical centroid adjustment mechanism base through bolts. The vertical centroid adjustment mechanism base can be fixedly connected to the vertical centroid adjustment mechanism housing through bolts. At the same time, the bolts can fixedly connect the vertical centroid adjustment mechanism base and the overall satellite frame through the through holes reserved on the vertical centroid adjustment mechanism base. In this way, the structural design of the vertical centroid adjustment mechanism and the horizontal centroid adjustment mechanism is more compact, and at the same time, the centroid adjustment in three axes is achieved, which can facilitate the fine adjustment of the satellite centroid, greatly reduce the occupied satellite space volume, facilitate the assembly with the satellite, and avoid the interference problem with respect to the simulated satellite.

[0017] 2. The simulated satellite has a two-layer structure in the shape of a regular hexagon. The overall structure is simple and is used for operation. By setting the overall framework of the satellite with two layers, the upper layer mainly houses devices such as power supplies, controllers, micro-thrusters, and gas storage cylinders, while the lower layer mainly houses hardware such as laser displacement sensors. The simulated satellite is suspended by tungsten wires to simulate the weightless state in space. Its power supply can supply power to the entire system, the controller is used to precisely control the micro-thrusters to generate thrust, the nitrogen gas storage tank can be used to store nitrogen, the micro-thrusters generate thrust to control the position and attitude of the simulated satellite, and the laser displacement sensor can monitor the position state of the simulated satellite in real time. At the same time, tungsten wire suspension is used to achieve the state of the satellite. The tungsten wire suspension is mainly realized by a tungsten wire clamping member, which is mainly composed of a tungsten wire clamping member housing, a wedge-shaped block, and a fastening bolt. The tungsten wire passes through the through hole above the tungsten wire clamping member housing, and the wedge-shaped block applies a clamping force to it. The fastening bolt is bolted to the lower part of the tungsten wire clamping member housing. Tightening the fastening bolt can provide a pressing force for the wedge-shaped block, thereby ensuring that the wedge-shaped block has a large enough clamping force on the tungsten wire. In addition, the surface of the wedge-shaped block in contact with the tungsten wire is made as rough as possible to provide higher friction. A through hole is designed at the center of the top cover above the overall framework of the satellite to allow the tungsten wire to pass through, and the top cover is fixedly connected to the overall framework of the satellite by bolts, thereby ensuring that the ground-simulated satellite can be suspended by tungsten wires, making the overall operating system process simple and facilitating the needs of the centroid adjustment task of the ground satellite. Description of the Drawings

[0018] Figure 1 Schematic diagram of the overall structure of the ground-simulated satellite provided by the present invention; Figure 2 Schematic diagram of the tungsten wire clamping mechanism for the ground-simulated satellite provided by the present invention.

[0019] Figure 3 Schematic diagram of the three-axis centroid fine-tuning mechanism for the ground-simulated satellite provided by the present invention; Figure 4 Schematic diagram of the vertical mass centroid adjustment structure of the three-axis centroid fine-tuning mechanism for the ground-simulated satellite provided by the present invention; Figure 5 Schematic diagram of the horizontal mass centroid adjustment structure of the three-axis centroid fine-tuning mechanism for the ground-simulated satellite provided by the present invention; Figure 6 Schematic diagram of the wall box structure of the three-axis centroid fine-tuning mechanism for the ground-simulated satellite provided by the present invention; Figure 7 Schematic diagram of the bottom cylinder structure of the three-axis centroid fine-tuning mechanism for the ground-simulated satellite provided by the present invention.

[0020] In the figure: 1. Overall satellite framework; 1-1. Bottom cylinder; 1-2. Oil pipe; 1-3. Connection port; 2. Centroid fine-tuning mechanism; 2-1. Horizontal centroid adjustment mass block; 2-2. Horizontal centroid adjustment mass block base; 2-3. Horizontal centroid adjustment mass block fixed base; 2-4. Vertical centroid adjustment mechanism housing; 2-5. Vertical centroid adjustment mechanism knob; 2-6. Vertical centroid adjustment mechanism base; 2-7. Vertical centroid adjustment mechanism lifting screw; 2-8. Vertical centroid adjustment mass block; 2-9. Horizontal Y-axis centroid adjustment knob; 2-10. Fixed base connecting piece; 2-11. Horizontal X-axis centroid adjustment knob; 2-12. Horizontal X-axis centroid adjustment knob and mass block base connecting piece; 2-13. Horizontal Y-axis centroid adjustment fixing bolt; 2-14. Horizontal X-axis centroid adjustment fixing bolt; 2-15. Wall box; 2-16. Oil bladder; 2-17. Sealing interface; 2-18. Oil pipe 1; 2-19. Oil pump; 2-20. Oil pipe 2; 3. Controller; 4. Micro thruster; 5. Nitrogen gas storage tank; 6. Power supply; 7. Laser displacement sensor; 8. Six-degree-of-freedom displacement table; 9-1. Tungsten wire; 9-2. Wedge-shaped block; 9-3. Fastening bolt; 9-4. Tungsten wire clamping piece housing. Specific implementation mode

[0021] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0022] Please refer to Figures 1 to 7 , the embodiments of the present invention provide a ground-simulated satellite and its three-axis centroid fine-tuning mechanism, including an overall satellite framework 1. A centroid fine-tuning mechanism 2 is installed inside the overall satellite framework 1. A horizontal centroid adjustment mass block 2-1 is installed on the top of the centroid fine-tuning mechanism 2. The lower surface of the horizontal centroid adjustment mass block 2-1 is provided with a horizontal centroid adjustment mass block base 2-2. The bottom of the horizontal centroid adjustment mass block base 2-2 is fixedly installed with a horizontal centroid adjustment mass block fixed base 2-3. A vertical centroid adjustment mechanism housing 2-4 is installed below the horizontal centroid adjustment mass block fixed base 2-3. The left and right sides of the vertical centroid adjustment mechanism housing 2-4 are connected with a vertical centroid adjustment mechanism knob 2-5. The bottom of the vertical centroid adjustment mechanism housing 2-4 is fixedly installed with a vertical centroid adjustment mechanism base 2-6. A horizontal X-axis centroid adjustment knob 2-11 is installed on the left side of the horizontal centroid adjustment mass block base 2-2. A vertical centroid adjustment mechanism lifting screw 2-7 is vertically arranged on the surface center line of the vertical centroid adjustment mechanism base 2-6. The top of the vertical centroid adjustment mechanism lifting screw 2-7 is installed with a vertical centroid adjustment mass block 2-8.

[0023] On both the left and right sides of the horizontal centroid adjustment mass block base 2-2, there are horizontal Y-axis centroid adjustment fixing bolts 2-13 for fixed installation. Above the horizontal centroid adjustment mass block 2-1, there is a horizontal X-axis centroid adjustment fixing bolt 2-14. Outside the horizontal X-axis centroid adjustment knob 2-11, there is a connecting part 2-12 between the horizontal X-axis centroid adjustment knob and the mass block base; Specifically, the adjustment direction of the horizontal centroid adjustment mechanism is arranged along the X and Y axes of the satellite. It can adjust the horizontal position of the mass block, thereby adjusting the centroid of the satellite in the X and Y directions. Further, the weight of the horizontal centroid adjustment mass block 2-1 is 5 kg, the moving stroke is not less than 30 mm, and the adjustment accuracy of the horizontal mass block position, that is, the bolt matching accuracy, is better than 0.1 mm. Further, m1 refers to the weight of the horizontal mass block being 5 kg, a1 refers to the bolt matching accuracy being 0.1 mm. L1 is the moving stroke of the horizontal mass block, which is 30 mm, and the total weight of the satellite is M = 100 kg. Then the satellite horizontal centroid adjustment range x1 = (m1·L1) / M, and the centroid adjustment accuracy d1 = (m1·a1) / M. It can be obtained that the satellite horizontal centroid adjustment range is 0 - 1.5 mm, and the centroid adjustment accuracy is 0.005 mm, meeting the high-precision adjustment design requirements; The horizontal centroid adjustment mechanism mainly places the horizontal centroid adjustment mass block 2-1 in the chute of the horizontal centroid adjustment mass block base 2-2, and realizes the fine adjustment function of the centroid in the X-axis direction through the horizontal X-axis centroid adjustment knob. By tightening the horizontal X-axis centroid adjustment fixing bolt 2-14, the position of the horizontal centroid adjustment mass block 2-1 can be fixed, thereby determining the centroid position in the X-axis direction. The horizontal centroid adjustment mass block base 2-2 is placed in the chute of the horizontal centroid adjustment mass block fixed base 2-2 to realize the centroid adjustment in the horizontal Y-axis direction. The horizontal centroid adjustment mass block fixed base 2-2 is fixedly connected to the vertical centroid adjustment mechanism housing 2-4 by bolts. The vertical centroid adjustment mechanism knob 2-5 is connected through the reserved hole on the vertical centroid adjustment mechanism housing 2-4, and the vertical centroid adjustment mechanism housing 2-4 is fixedly connected to the vertical centroid adjustment mechanism base 2-6 by bolts; There is a meshing structure between the lifting screw 2-7 of the vertical centroid adjustment mechanism and the vertical centroid adjustment knob 2-5. On the back of the horizontal centroid adjustment mass block base 2-2, there is a horizontal Y-axis centroid adjustment knob 2-9, and outside the horizontal Y-axis centroid adjustment knob 2-9, there is a fixed base connecting part 2-10 installed; The adjustment direction of the vertical centroid adjustment mechanism is arranged along the Z-axis of the satellite. It can adjust the vertical position of the mass block, thereby adjusting the centroid of the satellite in the Z direction. Further, the weight of the vertical mass block is 8 kg, the moving stroke is not less than 50 mm, and the position adjustment accuracy is determined by the cooperation accuracy of the ordinary bolt and the tapered bolt. At the same time, since the vertical centroid adjustment mass block 2-8 is affected by gravity, the cooperation accuracy of the ordinary bolt does not need to be considered, and only the cooperation accuracy of the tapered bolt needs to be considered. Considering comprehensively, it can be known that the position adjustment accuracy of the vertical mass block is better than 0.05 mm. Further, m2 refers to the weight of the vertical mass block, which is 8 kg, and a2 refers to the position adjustment accuracy of the vertical mass block, which is 0.05 mm. L2 is the movable stroke of the horizontal mass block, which is 50 mm, and the total weight of the satellite is M = 100 kg. Then the vertical centroid adjustment range of the satellite x1 = (m2·L2) / M, and the centroid adjustment accuracy d2 = (m2·a2) / M. It can be obtained that the vertical centroid adjustment range of the satellite is 0-4 mm, and the centroid adjustment accuracy is 0.004 mm, meeting the requirements of high-precision adjustment design. The vertical centroid adjustment mechanism is mainly that the vertical centroid adjustment mechanism knob 2-5 is connected to the vertical centroid adjustment mechanism lifting screw 2-7 through a bevel gear set. When the vertical centroid adjustment mechanism knob 2-5 is rotated, the vertical centroid adjustment mechanism lifting screw 2-7 can be driven to rotate at the same time. Since the vertical centroid adjustment mechanism lifting screw 2-7 and the vertical centroid adjustment mass block 2-8 are connected by threads, and the four sides of the vertical centroid adjustment mass block are fitted with the vertical centroid adjustment mechanism housing 2-4 to ensure that the vertical centroid adjustment mass block does not rotate, so as to realize the rotation of the vertical centroid adjustment mechanism lifting screw 2-7 to drive the vertical centroid adjustment mass block 2-8 to move up and down, thereby meeting the vertical centroid adjustment function. The vertical centroid adjustment mechanism base 2-6 can be fixedly connected to the vertical centroid adjustment mechanism housing 2-4 through bolts, and at the same time, the bolts can fixedly connect the vertical centroid adjustment mechanism base 2-6 and the satellite overall frame 1 through the through holes reserved on the vertical centroid adjustment mechanism base 2-6.

[0024] Wall boxes 2-15 are installed on the outer walls around the centroid fine adjustment mechanism 2. An oil bladder 2-16 is installed inside the wall boxes 2-15. A sealing interface 2-17 is integrally provided on one side of the wall boxes 2-15, and a first oil pipe 2-18 is connected to the port of the sealing interface 2-17. A fuel pump 2-19 is installed at the end of the first oil pipe 2-18 away from the sealing interface 2-17. A second oil pipe 2-20 is connected to the inlet end of the fuel pump 2-19. The oil bladder 2-16 is interconnected with the first oil pipe 2-18 through the sealing interface 2-17. The first oil pipe 2-18 is connected to the second oil pipe 2-20 through the fuel pump 2-19. A lower oil pipe box 1-2 is installed at the lower end of the second oil pipe 2-20. A connection port 1-3 is integrally provided at the top of the lower oil pipe box 1-2. The lower oil pipe box 1-2 is interconnected with the second oil pipe 2-20 through the connection port 1-3. A bottom cylinder 1-1 is installed outside the lower oil pipe box 1-2; Specifically, a wall box 2-15 is installed on the outer wall of the centroid fine-tuning mechanism 2. An oil pump 2-19 is used to connect the second oil pipe 2-20 and the first oil pipe 2-18, and the oil inside the oil pipe box 1-2 is pumped into the oil bladder 2-16 inside the wall box 2-15. When the oil enters the oil bladder 2-16, the weight on the corresponding side of the centroid fine-tuning mechanism 2 increases. Then, in cooperation with the three-axis adjustment structure of the centroid fine-tuning mechanism 2, the mass center is adjusted. According to the actual situation of the three-axis adjustment, oil is filled into the corresponding side of the wall box, and then through the change of weight, the centroid fine-tuning of the centroid fine-tuning mechanism 2 is realized.

[0025] A ground-simulated satellite includes a satellite overall frame 1, and a tungsten wire clamping part housing 9-4 is installed on the top of the satellite overall frame 1; a wedge-shaped block 9-2 is installed inside the tungsten wire clamping part housing 9-4, a tungsten wire 9-1 is inserted through the wedge-shaped block 9-2, and a fastening bolt 9-3 for suspension connection is arranged at the bottom of the tungsten wire clamping part housing 9-4. The tungsten wire clamping part housing 9-4 is connected to the satellite overall frame 1 through the fastening bolt 9-3, and the lower end of the tungsten wire 9-1 is fixedly connected to the inside of the wedge-shaped block 9-2; Specifically, the tungsten wire 9-1 is clamped by the wedge-shaped block through a through hole above the tungsten wire clamping part housing 9-4. The fastening bolt 9-3 and the lower part of the tungsten wire clamping part housing 9-4 are connected by bolts. Tightening the fastening bolt 9-3 can provide a pressing force for the wedge-shaped block 9-2, thereby ensuring that the wedge-shaped block 9-2 has a large enough clamping force on the tungsten wire 9-1. In addition, the surface of the wedge-shaped block 9-2 in contact with the tungsten wire 9-1 is made as rough as possible to provide higher friction. A through hole is designed in the center of the top cover above the satellite overall frame 1 to allow the tungsten wire to pass through, and the top cover and the satellite overall frame 1 are fixedly connected by bolts, thereby ensuring that the ground-simulated satellite can be suspended by the tungsten wire.

[0026] A controller 3 is installed on the left side inside the satellite overall frame 1, micro thrusters 4 are installed on the outer sides of the satellite overall frame 1, a nitrogen gas storage tank 5 is installed in the middle inside the satellite overall frame 1, a power supply 6 is installed on the right side of the nitrogen gas storage tank 5, laser displacement sensors 7 are installed on both the left and right sides at the bottom of the satellite overall frame 1, and a six-degree-of-freedom displacement table 8 is installed at the bottom of the satellite overall frame 1; The micro thrusters 4 are distributed in a cross shape with respect to the symmetry center line of the satellite overall frame 1, and the six-degree-of-freedom displacement table 8 is movably connected to the bottom of the satellite overall frame 1. The satellite overall frame 1 is suspended by the tungsten wire to simulate the weightless state of the satellite in space. Since the tungsten wire has good tensile performance but poor shear resistance, a tungsten wire clamping mechanism is used to connect the tungsten wire and the satellite, and at the same time, the tungsten wire is prevented from bearing shear force; Specifically, the power supply 6 can supply power to the entire system to ensure the operation of the control system. The controller 3 is used to precisely control the micro thruster 4 to generate thrust. The micro thruster 4 is fixedly connected to the overall satellite frame 1 through a connecting member, and 8 are distributed oppositely along the X and Y axes respectively. The position and attitude of the simulated satellite are controlled by generating thrust. The nitrogen gas storage tank 5 can be used to store nitrogen gas, which can ensure the continuous operation of the system for 2 hours. The six-degree-of-freedom displacement stage 8 can provide relative displacement between the test mass and the simulated satellite. The laser displacement sensor 7 can monitor the position state of the simulated satellite in real time and simultaneously feedback signals to the control system.

[0027] Working principle: Devices such as the power supply 6, the controller 3, the micro thruster 4, and the nitrogen gas storage tank 5 are mainly placed in the upper structure of the overall satellite frame 1, and hardware such as the laser displacement sensor 7 is mainly placed in the lower structure, so as to simulate the weightless state in space through the tungsten wire 9-1; During three-axis adjustment, the horizontal centroid adjustment mass block 2-1 is placed in the chute of the horizontal centroid adjustment mass block base 2-2. The fine adjustment function of the centroid in the X-axis direction is realized through the horizontal X-axis centroid adjustment knob 2-11. The position of the horizontal centroid mass block can be fixed by tightening the horizontal X-axis centroid adjustment fixing bolt 2-14, and then the centroid position in the X-axis direction is determined. The horizontal centroid adjustment mass block base 2-2 is placed in the chute of the horizontal centroid adjustment mass block fixed base 2-3 to realize the centroid adjustment in the horizontal Y-axis direction. The horizontal centroid adjustment mass block fixed base 2-3 is fixedly connected to the vertical centroid adjustment mechanism housing 2-4 through bolts. The vertical centroid adjustment mechanism knob 2-5 is connected through the reserved hole on the vertical centroid adjustment mechanism housing 2-4. The vertical centroid adjustment mechanism housing 2-4 is fixedly connected to the vertical centroid adjustment mechanism base 2-6 through bolts. In addition, the horizontal centroid adjustment mass block 2-1 is placed in the chute of the horizontal centroid adjustment mass block base 2-2 and is connected to the horizontal X-axis centroid adjustment knob 2-11 through threads. The horizontal X-axis centroid adjustment knob and the mass block base connecting member 2-12 are fixedly connected to the horizontal centroid adjustment mass block base 2-2 through bolts, which can ensure the relative displacement in the X-axis direction between the horizontal X-axis centroid adjustment knob 2-11 and the horizontal centroid adjustment mass block base 2-2. Then, by rotating the horizontal X-axis centroid adjustment knob 2-11, the fine adjustment function of the centroid in the X-axis direction is realized. The position of the horizontal centroid mass block can be fixed by tightening the horizontal X-axis centroid adjustment fixing bolt 2-14, and then the centroid position in the X-axis direction is determined. The horizontal centroid adjustment mass block base 2-2 is placed in the chute of the horizontal centroid adjustment mass block fixed base 2-3 and is connected to the horizontal Y-axis centroid adjustment knob 2-9 through threads. The horizontal Y-axis centroid adjustment knob and the fixed base connecting member 2-10 are fixedly connected to the horizontal centroid adjustment mass block fixed base 2-3 through bolts, which can ensure the relative displacement in the Y-axis direction between the horizontal Y-axis centroid adjustment knob 2-9 and the horizontal centroid adjustment mass block fixed base 2-3, and then the fine adjustment function of the centroid in the horizontal Y-axis direction is realized; The adjustment direction of the vertical centroid adjustment mechanism is arranged along the Z-axis of the satellite, which can adjust the vertical position of the mass block, and thus adjust the centroid of the satellite in the Z direction. The vertical centroid adjustment mechanism knob 2-5 is connected to the vertical centroid adjustment mechanism lifting screw 2-7 through a bevel gear set. When the vertical centroid adjustment mechanism knob 2-5 is rotated, the vertical centroid adjustment mechanism lifting screw 2-7 can be driven to rotate simultaneously. Since the vertical centroid adjustment mechanism lifting screw 2-7 and the vertical centroid adjustment mass block 2-8 are connected by threads, and the four sides of the vertical centroid adjustment mass block 2-8 are matched with the vertical centroid adjustment mechanism housing 2-4 to ensure that the vertical centroid adjustment mass block 2-8 does not rotate. Thus, the rotation of the vertical centroid adjustment mechanism lifting screw 2-7 drives the vertical centroid adjustment mass block 2-8 to move up and down, thereby meeting the vertical centroid adjustment function. The vertical centroid adjustment mechanism base 2-6 can be fixedly connected to the vertical centroid adjustment mechanism housing 2-4 through bolts, and at the same time, the bolts can fixedly connect the vertical centroid adjustment mechanism base 2-6 and the overall satellite frame 1 through the through holes reserved on the vertical centroid adjustment mechanism base 2-6; By tightening the horizontal Y-axis centroid adjustment fixing bolt 2-13, the position of the horizontal centroid mass block can be fixed, and then the centroid position in the Y-axis direction can be determined. Through the vertical centroid adjustment mechanism and the horizontal centroid adjustment mechanism, the X-axis, Y-axis, and Z-axis of the satellite are respectively determined, and at the same time, the centroid adjustment of the three axes is realized, which can facilitate the fine adjustment of the satellite centroid, greatly reduce the occupied satellite space volume, and facilitate the assembly with the satellite while avoiding the interference problem with respect to the simulated satellite; Wall boxes 2-15 are installed on all four sides of the centroid fine adjustment mechanism 2, and oil bags 2-16 are installed inside the wall boxes 2-15. The structures and weights of the wall boxes 2-15 on the four sides are the same. When no oil is filled into the oil bags 2-16, the centroid fine adjustment mechanism 2 maintains its initial balance, and then the centroid adjustment of the three axes is carried out. The oil pump 2-19 pumps the oil inside the oil pipe box 1-2 through the oil pipe two 2-20 into the oil pipe one 2-18, and the oil is filled into the oil bags 2-16 through the oil pipe one 2-18. When the oil enters the inside of the oil bags 2-16, the weight of one side of the centroid fine adjustment mechanism 2 filled with oil in the oil bags 2-16 increases, and the other three sides are the same. By filling the oil into the oil bags 2-16, the offset adjustment of the center of gravity is realized, and then the adjustment of the mass center of gravity is carried out in cooperation with the three-axis adjustment structure of the centroid fine adjustment mechanism 2.

[0028] As mentioned above, only the specific preferred embodiments of the present invention are described, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, makes equivalent substitutions or changes, and all should be covered within the protection scope of the present invention.

Claims

1. A three-axis centroid fine-tuning mechanism for a ground-based simulation satellite, characterized in that: The invention comprises a satellite overall frame (1), wherein a mass center fine adjustment mechanism (2) is installed inside the satellite overall frame (1), a horizontal mass center adjustment mass block (2-1) is installed on the top of the mass center fine adjustment mechanism (2), and a horizontal mass center adjustment mass block base (2-2) is installed on the lower surface of the horizontal mass center adjustment mass block (2-1), a horizontal mass center adjustment mass block fixed base (2-3) is fixedly installed on the bottom of the horizontal mass center adjustment mass block base (2-2), a vertical mass center adjustment mechanism housing (2-4) is installed below the horizontal mass center adjustment mass block fixed base (2-3), and the vertical mass center adjustment mechanism housing (2-4) is installed below the horizontal mass center adjustment mass block fixed base (2-3). The left and right sides of the vertical center of mass adjustment mechanism housing (2-4) are connected to vertical center of mass adjustment mechanism knobs (2-5); the bottom of the vertical center of mass adjustment mechanism housing (2-4) is fixedly mounted with a vertical center of mass adjustment mechanism base (2-6); the left side of the horizontal center of mass adjustment mass block base is mounted with a horizontal X-axis center of mass adjustment knob (2-11); a vertical center of mass adjustment mechanism lifting screw (2-7) is vertically arranged on the center line of the surface of the vertical center of mass adjustment mechanism base (2-6); and a vertical center of mass adjustment mass block (2-8) is mounted on the top of the vertical center of mass adjustment mechanism lifting screw (2-7).

2. The three-axis centroid fine-tuning mechanism for a ground simulation satellite according to claim 1, characterized in that: The outer walls of the centroid fine-tuning mechanism (2) are provided with a wall box (2-15), an oil bag (2-16) is provided inside the wall box (2-15), a sealing interface (2-17) is provided on one side of the wall box (2-15), and a port of the sealing interface (2-17) is connected to an oil pipe 1 (2-18), an oil pump (2-19) is provided at one end of the oil pipe 1 (2-18) away from the sealing interface (2-17), an inlet end of the oil pump (2-19) is connected to an oil pipe 2 (2-20), and the oil bag (2-16) is provided with a sealing interface (2-17) on one side of the wall box (2-15). 6) is interconnected with oil pipe 1 (2-18) through a sealing interface (2-17); the oil pipe 1 (2-18) is interconnected with oil pipe 2 (2-20) through an oil pump (2-19); an oil pipe box (1-2) is installed at the lower end of the oil pipe 2 (2-20); a connecting port (1-3) is integrally provided at the top of the oil pipe box (1-2); the oil pipe box (1-2) is interconnected with oil pipe 2 (2-20) through the connecting port (1-3); and a bottom cylinder (1-1) is installed on the outer side of the oil pipe box (1-2).

3. The three-axis centroid fine-tuning mechanism for a ground simulation satellite according to claim 1, characterized in that: A meshing structure is formed between the vertical center of mass adjustment mechanism lifting screw rod (2-7) and the vertical center of mass adjustment mechanism knob (2-5).

4. The three-axis centroid fine-tuning mechanism for a ground-based simulation satellite according to claim 1, characterized in that: A horizontal Y-axis mass center adjustment knob (2-9) is provided on the back of the horizontal mass center adjustment mass block base (2-2), and a fixed base connector (2-10) is installed on the outer side of the horizontal Y-axis mass center adjustment knob (2-9).

5. The three-axis centroid fine-tuning mechanism for a ground simulation satellite according to claim 1, characterized in that: Horizontal Y-axis center of mass adjustment fixing bolts (2-13) for fixed installation are arranged on both left and right sides of the horizontal center of mass adjustment mass block base (2-2), and horizontal X-axis center of mass adjustment fixing bolts (2-14) are arranged above the horizontal center of mass adjustment mass block (2-1).

6. The three-axis centroid fine-tuning mechanism for a ground simulation satellite according to claim 1, characterized in that: A horizontal X-axis center of mass adjustment knob and mass block base connecting piece (2-12) is arranged on the outer side of the horizontal X-axis center of mass adjustment knob (2-11).

7. A ground simulation satellite, characterized in that: It comprises a satellite integral frame (1), wherein a tungsten wire clamping piece housing (9-4) is installed on the top of the satellite integral frame (1); A controller (3) is installed on the left side of the interior of the satellite integral frame (1), micro-thrusters (4) are installed on the outside of the satellite integral frame (1), a nitrogen gas storage tank (5) is installed in the middle of the interior of the satellite integral frame (1), a power supply (6) is installed on the right side of the nitrogen gas storage tank (5), laser displacement sensors (7) are installed on the left and right sides of the bottom of the satellite integral frame (1), and a six-degree-of-freedom displacement platform (8) is installed on the bottom of the satellite integral frame (1); A wedge-shaped block (9-2) is installed inside the tungsten wire clamping piece housing (9-4), a tungsten wire (9-1) is inserted into the wedge-shaped block (9-2), and a fastening bolt (9-3) for suspension connection is arranged at the bottom of the tungsten wire clamping piece housing (9-4).

8. A ground simulation satellite according to claim 7, characterized in that: The micro-thrusters (4) are distributed in a cross shape with respect to the symmetric center line of the satellite overall frame (1).

9. A ground simulation satellite according to claim 7, characterized in that: The tungsten wire clamping piece housing (9-4) is connected to the satellite overall frame (1) via a fastening bolt (9-3), and the lower end of the tungsten wire (9-1) is fixedly connected to the inside of the wedge-shaped block (9-2).

10. A ground simulation satellite according to claim 7, characterized in that: The six-degree-of-freedom displacement platform (8) is movably connected to the bottom of the satellite overall frame (1).

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