Ground simulation satellite and three-axis centroid fine adjustment mechanism thereof

Abstract

The application discloses a ground simulation satellite and a three-axis centroid fine adjustment mechanism thereof, and belongs to the technical field of satellite simulation. The satellite overall frame is internally provided with a centroid fine adjustment mechanism, the top of the centroid fine adjustment mechanism is provided with a horizontal centroid adjustment mass, and the lower surface of the horizontal centroid adjustment mass is provided with a horizontal centroid adjustment mass base. Through the three-axis adjustment structure, the adjustment direction of the horizontal centroid adjustment mechanism is arranged along the satellite X and Y axes, the horizontal direction position of the adjustable mass can be adjusted, and then the centroid in the X and Y directions of the satellite can be adjusted; the adjustment direction of the vertical centroid adjustment mechanism is arranged along the satellite Z axis, the vertical direction position of the adjustable mass can be adjusted, and then the centroid in the Z direction of the satellite can be adjusted; the horizontal centroid adjustment mechanism and the vertical centroid adjustment mechanism are mutually matched, and three-axis adjustment is realized.

Description

Technical Field

[0001] This invention relates to the field of satellite center of mass adjustment mechanisms, specifically a ground-based simulated satellite and its three-axis center of mass fine-tuning mechanism. Background Technology

[0002] Space science, as a cutting-edge, innovative, leading, and highly challenging scientific and technological field, plays a crucial role in the national innovation-driven development strategy. In recent years, the development and launch of space science satellites such as the dark matter detection satellite "Wukong," the dragless technology experimental satellites "Taiji-1" and "Tianqin-1," and the solar exploration science and technology experimental satellite "Xihe" have greatly enhanced my country's international influence in space science. Dragless satellites are key platforms for missions such as gravitational wave detection and gravity field measurement. However, satellites are high-value products with high technological content, characterized by the use of low-quality, high-strength materials, high production costs, and the carrying of high-precision instruments. Often, it is impossible to provide a real satellite for testing, thus requiring the design of a simulated satellite. However, simulated satellites typically use ordinary materials, leading to problems such as centroid deviation. Therefore, it is necessary to first build a simulation system on the ground to verify the effectiveness of its control system.

[0003] To minimize the centroid displacement deviation caused by the installation of the ground-based simulated satellite, a centroid fine-tuning mechanism needs to be designed. To ensure the ground-based simulated satellite remains level, a horizontal centroid adjustment mechanism is required. If the satellite's centroid and the thrust generated by the micro-thrusters are not on the same horizontal plane, it will lead to tilting horizontal coupling effects. That is, under the action of the micro-thrusters, the satellite structure will not only oscillate around the suspension point but also rotate around its own centroid, thus affecting the accuracy of the grating displacement sensor in detecting the displacement between the satellite and the test mass. Therefore, a vertical centroid adjustment mechanism is needed. Current satellite centroid adjustment mechanisms have the following main problems: 1. Most existing satellite centroid adjustment mechanisms are mainly applicable to in-orbit satellites. Their high-precision centroid adjustment systems for in-orbit satellites are designed to achieve high-precision centroid adjustment, but the systems are too complex and unsuitable for the centroid adjustment requirements of ground-based satellites; 2. Existing satellite centroid adjustment mechanisms use a screw-rail structure, which can only adjust the centroid in one axis. Therefore, three sets of screw-rail structures are needed for each of the three axes, which significantly occupies the satellite's internal space.

[0004] In summary, by innovating the existing satellite center of mass adjustment mechanism and designing the center of mass fine-tuning mechanism based on the mechanism of the ground-based simulated satellite, a ground-based simulated satellite and its three-axis center of mass fine-tuning mechanism are proposed. This mechanism simultaneously achieves center of mass adjustment in three axes, which facilitates fine-tuning of the satellite's center of mass, greatly reduces the space occupied on the satellite, and facilitates assembly with the satellite while avoiding interference problems relative to the simulated satellite. Summary of the Invention

[0005] The purpose of this invention is to provide a ground-based simulated satellite and its three-axis centroid fine-tuning mechanism to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, the present invention provides the following technical solution:

[0007] A three-axis centroid fine-tuning mechanism for a ground-based simulated satellite includes a satellite frame. A centroid fine-tuning mechanism is installed inside the satellite frame. A horizontal centroid adjustment mass block is mounted on the top of the centroid fine-tuning mechanism, and a horizontal centroid adjustment mass block base is mounted on the lower surface of the horizontal centroid adjustment mass block. A horizontal centroid adjustment mass block fixing base is fixedly mounted at the bottom of the horizontal centroid adjustment mass block base. A vertical centroid adjustment mechanism housing is installed below the horizontal centroid adjustment mass block fixing base. Vertical centroid adjustment mechanism knobs are connected to the left and right sides of the vertical centroid adjustment mechanism housing. A vertical centroid adjustment mechanism base is fixedly mounted at the bottom of the vertical centroid adjustment mechanism housing. A horizontal X-axis centroid adjustment knob is mounted on the left side of the horizontal centroid adjustment mass block base. A vertical centroid adjustment mechanism lifting screw is vertically arranged along the center line of the surface of the vertical centroid adjustment mechanism base, and a vertical centroid adjustment mass block is mounted on the top of the vertical centroid adjustment mechanism lifting screw.

[0008] In one embodiment of the present invention, a wall box is installed on the outer wall of the center of mass fine-tuning mechanism. An oil bladder is installed inside the wall box. A sealing interface is integrally provided on one side of the wall box, and the port of the sealing interface is connected to an oil pipe. An oil pump is installed at the end of the oil pipe away from the sealing interface. An oil pipe is connected to the inlet end of the oil pump. The oil bladder is interconnected with the oil pipe through the sealing interface. The oil pipe is interconnected with the oil pipe through the oil pump. An oil pipe box is installed at the lower end of the oil pipe. A connection port is integrally provided on the top of the oil pipe box. The oil pipe box is interconnected with the oil pipe through the connection port. A bottom cylinder is installed on the outside of the oil pipe box.

[0009] In one embodiment of the present invention, the lifting screw of the vertical center of gravity adjustment mechanism and the knob of the vertical center of gravity adjustment mechanism are meshed.

[0010] In one 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 connector is installed on the outside of the horizontal Y-axis centroid adjustment knob.

[0011] In one 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 horizontal X-axis centroid adjustment fixing bolts are provided above the horizontal centroid adjustment mass block.

[0012] As one embodiment of the present invention, a horizontal X-axis centroid adjustment knob and a mass block base connection are provided on the outer side of the horizontal X-axis centroid adjustment knob.

[0013] A ground-based simulated satellite includes an overall satellite frame, with a tungsten wire clamping housing mounted on top of the overall satellite frame;

[0014] A controller is installed on the left side inside the satellite's overall frame. Micro-thrusters are installed on the outer sides of the satellite's overall frame. A nitrogen storage tank is installed in the middle inside the satellite's overall frame. A power supply is installed on the right side of the nitrogen storage tank. Laser displacement sensors are installed on both the left and right sides of the bottom of the satellite's overall frame. A six-degree-of-freedom displacement stage is installed at the bottom of the satellite's overall frame.

[0015] A wedge block is installed inside the housing of the tungsten wire clamping component, and tungsten wires are inserted inside the wedge block. The bottom of the housing of the tungsten wire clamping component is provided with fastening bolts for suspension connection.

[0016] In one embodiment of the present invention, the micro-thrusters are distributed in a cross shape about the symmetrical center line of the satellite's overall frame.

[0017] In one embodiment of the present invention, the tungsten wire clamping housing is connected to the satellite's overall frame by fastening bolts, and the lower end of the tungsten wire is fixedly connected to the interior of the wedge block.

[0018] In one embodiment of the present invention, the six-degree-of-freedom displacement stage is movably connected to the bottom of the satellite's overall frame.

[0019] Compared with the prior art, the beneficial effects of the present invention are:

[0020] By setting up a three-axis adjustment structure, the three axes are a vertical center of mass adjustment mechanism and a horizontal center of mass adjustment mechanism. The horizontal center of mass adjustment mechanism is arranged along the X and Y axes of the satellite, adjusting the horizontal position of the mass block, thereby adjusting the center of mass of the satellite in the X and Y directions. The vertical center of mass adjustment mechanism is arranged along the Z axis of the satellite, adjusting the vertical position of the mass block, thereby adjusting the center of mass of the satellite in the Z direction. The horizontal and vertical center of mass adjustment mechanisms cooperate to achieve three-axis adjustment. The vertical center of mass adjustment mechanism mainly consists of a knob connected to a vertical center of mass adjustment mechanism lifting screw via a bevel gear set. This allows the vertical center of mass adjustment mechanism lifting screw to rotate simultaneously when the knob is rotated. The vertical center of mass adjustment mechanism mainly consists of a knob connected to a vertical center of mass adjustment mechanism lifting screw via a bevel gear set. When the knob of the vertical center of mass adjustment mechanism is rotated, the lifting screw of the vertical center of mass adjustment mechanism is also rotated. The fixed base of the horizontal center of mass adjustment mass block is fixed to the housing of the vertical center of mass adjustment mechanism by bolts. The knob of the vertical center of mass adjustment mechanism is connected through the reserved hole on the housing of the vertical center of mass adjustment mechanism. The housing of the vertical center of mass adjustment mechanism is fixed to the base of the vertical center of mass adjustment mechanism by bolts. The base of the vertical center of mass adjustment mechanism can be fixed to the housing of the vertical center of mass adjustment mechanism by bolts. At the same time, the bolts can be used to fix the base of the vertical center of mass adjustment mechanism and the satellite frame through the reserved through hole on the base of the vertical center of mass adjustment mechanism. In this way, the structural design of the vertical center of mass adjustment mechanism and the horizontal center of mass adjustment mechanism is more compact, and the center of mass adjustment in three axes is realized. This facilitates the fine adjustment of the satellite's center of mass, greatly reduces the space volume occupied on the satellite, facilitates the assembly with the satellite, and avoids interference problems relative to the simulated satellite.

[0021] 2. This simulated satellite has a simple, two-layered hexagonal structure. The upper layer houses the power supply, controller, micro-thrusters, and gas cylinders, while the lower layer contains hardware such as laser displacement sensors. The simulated satellite is suspended by tungsten wires to simulate weightlessness in space. The power supply powers the entire system, the controller precisely controls the micro-thrusters to generate thrust, and the nitrogen storage tank stores nitrogen. The micro-thrusters generate thrust to control the simulated satellite's position and attitude, and the laser displacement sensors... The system monitors the simulated satellite's position and status in real time, employing tungsten wire suspension to achieve this. The tungsten wire suspension is primarily achieved through a tungsten wire clamping mechanism, consisting of a clamping mechanism housing, wedge blocks, and fastening bolts. The tungsten wire passes through a through-hole in the upper part of the clamping mechanism housing, where the wedge blocks apply clamping force. The fastening bolts are bolted to the lower part of the clamping mechanism housing. Tightening the bolts provides a clamping force to the wedge blocks, ensuring sufficient clamping force on the tungsten wire. Additionally, the surfaces of the wedge blocks and the tungsten wire in contact are made as rough as possible to provide higher friction. A through-hole is designed in the center of the top cover above the satellite's overall frame, allowing the tungsten wire to pass through. The top cover is bolted to the satellite's overall frame, ensuring the ground-based simulated satellite can be suspended by the tungsten wire. This simplifies the overall operating process and is suitable for the needs of ground-based satellite center-of-gravity adjustment tasks. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of a ground-based simulated satellite provided by the present invention;

[0023] Figure 2 A schematic diagram of a tungsten wire clamping mechanism for ground-based simulated satellites provided by the present invention.

[0024] Figure 3 This is a schematic diagram of the three-axis centroid fine-tuning mechanism for ground-based simulated satellites provided by the present invention;

[0025] Figure 4 A schematic diagram of the vertical mass block centroid adjustment structure of the three-axis centroid fine-tuning mechanism for ground-based simulated satellites provided by the present invention;

[0026] Figure 5 A schematic diagram of the horizontal mass block centroid adjustment structure of the three-axis centroid fine-tuning mechanism for ground-based simulated satellites provided by the present invention;

[0027] Figure 6 A schematic diagram of the wall box structure of the three-axis centroid fine-tuning mechanism for ground-based simulated satellites provided by the present invention;

[0028] Figure 7 A schematic diagram of the bottom cylinder structure of the three-axis centroid fine-tuning mechanism for ground-based simulated satellites provided by the present invention.

[0029] In the diagram: 1. Satellite overall frame; 1-1. Base cylinder; 1-2. Oil pipe; 1-3. Connection port; 2. Center of mass fine-tuning mechanism; 2-1. Horizontal center of mass adjustment mass block; 2-2. Horizontal center of mass adjustment mass block base; 2-3. Horizontal center of mass adjustment mass block fixed base; 2-4. Vertical center of mass adjustment mechanism housing; 2-5. Vertical center of mass adjustment mechanism knob; 2-6. Vertical center of mass adjustment mechanism base; 2-7. Vertical center of mass adjustment mechanism lifting screw; 2-8. Vertical center of mass adjustment mass block; 2-9. Horizontal Y-axis center of mass adjustment knob; 2-10. Fixed base connector; 2-11. Horizontal X-axis... 1. Center of mass adjustment knob; 2-12. Connecting part between horizontal X-axis center of mass adjustment knob and mass block base; 2-13. Fixed bolt for horizontal Y-axis center of mass adjustment; 2-14. Fixed bolt for horizontal X-axis center of mass adjustment; 2-15. Wall box; 2-16. Oil bladder; 2-17. Sealing interface; 2-18. Oil pipe one; 2-19. Oil pump; 2-20. Oil pipe two; 3. Controller; 4. Micro thruster; 5. Nitrogen storage tank; 6. Power supply; 7. Laser displacement sensor; 8. Six-degree-of-freedom displacement stage; 9-1. Tungsten wire; 9-2. Wedge block; 9-3. Fastening bolt; 9-4. Tungsten wire clamping housing. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] Please see Figures 1 to 7 This invention provides a ground-based simulated satellite and its three-axis centroid fine-tuning mechanism, including a satellite frame 1. A centroid fine-tuning mechanism 2 is installed inside the satellite frame 1. A horizontal centroid adjustment mass block 2-1 is installed on the top of the centroid fine-tuning mechanism 2, and a horizontal centroid adjustment mass block base 2-2 is installed on the lower surface of the horizontal centroid adjustment mass block 2-1. A horizontal centroid adjustment mass block fixing base 2-3 is fixedly installed at the bottom of the horizontal centroid adjustment mass block base 2-2, and a vertical centroid adjustment mechanism is installed below the horizontal centroid adjustment mass block fixing base 2-3. The vertical center of gravity adjustment mechanism housing 2-4 is connected to the left and right sides of the vertical center of gravity adjustment mechanism housing 2-4 with vertical center of gravity adjustment mechanism knobs 2-5. The bottom of the vertical center of gravity adjustment mechanism housing 2-4 is fixedly installed with a vertical center of gravity adjustment mechanism base 2-6. The left side of the horizontal center of gravity adjustment mass block base 2-2 is installed with a horizontal X-axis center of gravity adjustment knob 2-11. The vertical center of gravity adjustment mechanism lifting screw 2-7 is vertically set on the center line of the surface of the vertical center of gravity adjustment mechanism base 2-6. The top of the vertical center of gravity adjustment mechanism lifting screw 2-7 is installed with a vertical center of gravity adjustment mass block 2-8.

[0032] The horizontal Y-axis center of mass adjustment base 2-2 is provided with horizontal Y-axis center of mass adjustment fixing bolts 2-13 for fixed installation on both the left and right sides. The horizontal X-axis center of mass adjustment base 2-1 is provided with horizontal X-axis center of mass adjustment fixing bolts 2-14 above the horizontal X-axis center of mass adjustment base. The horizontal X-axis center of mass adjustment knob 2-11 is provided with a horizontal X-axis center of mass adjustment knob and mass block base connecting piece 2-12 on the outside.

[0033] Specifically, the horizontal center of mass adjustment mechanism is arranged along the X and Y axes of the satellite, adjusting the horizontal position of the mass block to adjust the center of mass of the satellite in the X and Y directions. Furthermore, the horizontal center of mass adjustment mass block 2-1 weighs 5 kg, has a travel distance of not less than 30 mm, and the adjustment accuracy of the horizontal mass block (i.e., the bolt fit accuracy) is better than 0.1 mm. Further, m1 refers to the weight of the horizontal mass block being 5 kg, and a1 refers to the bolt fit accuracy being 0.1 mm. L1 is the travel distance of the horizontal mass block, which is 30 mm. The total weight of the satellite is M = 100 kg. Therefore, the satellite's horizontal center of mass adjustment range is x1 = (m1·L1) / M, and the center of mass adjustment accuracy is d1 = (m1·a1) / M. This results in a horizontal center of mass adjustment range of 0-1.5 mm and a center of mass adjustment accuracy of 0.005 mm, meeting the high-precision adjustment design requirements.

[0034] The horizontal center of gravity adjustment mechanism mainly consists of a horizontal center of gravity adjustment mass block 2-1 placed in a groove in the horizontal center of gravity adjustment mass block base 2-2. Fine-tuning of the center of gravity along the X-axis is achieved via a horizontal X-axis center of gravity adjustment knob. Tightening the horizontal X-axis center of gravity adjustment fixing bolt 2-14 fixes the position of the horizontal center of gravity adjustment mass block 2-1, thus determining the center of gravity position along the X-axis. The horizontal center of gravity adjustment mass block base 2-2 is placed in a groove in the horizontal center of gravity adjustment mass block fixing base 2-2, achieving horizontal Y-axis center of gravity adjustment. The horizontal center of gravity adjustment mass block fixing base 2-2 is bolted to the vertical center of gravity adjustment mechanism housing 2-4. The vertical center of gravity adjustment mechanism knob 2-5 is connected through a pre-drilled hole in the vertical center of gravity adjustment mechanism housing 2-4. The vertical center of gravity adjustment mechanism housing 2-4 is bolted to the vertical center of gravity adjustment mechanism base 2-6.

[0035] The vertical center of gravity adjustment mechanism lifting screw 2-7 and the vertical center of gravity adjustment mechanism knob 2-5 are meshing structures. The back of the horizontal center of gravity adjustment mass block base 2-2 is provided with a horizontal Y-axis center of gravity adjustment knob 2-9. A fixed base connector 2-10 is installed on the outside of the horizontal Y-axis center of gravity adjustment knob 2-9.

[0036] The vertical center of mass adjustment mechanism is arranged along the Z-axis of the satellite, which can adjust the vertical position of the mass block, thereby adjusting the center of mass of the satellite in the Z-direction. Furthermore, the vertical mass block weighs 8kg, and its travel is not less than 50mm. The position adjustment accuracy is determined by the fit accuracy of ordinary bolts and the fit accuracy of tapered bolts. Since the vertical center of mass adjustment mass blocks 2-8 are affected by gravity, the fit accuracy of ordinary bolts does not need to be considered, and only the fit accuracy of tapered bolts needs to be considered. Considering all factors, the position adjustment accuracy of the vertical mass block is better than 0.05mm. Furthermore, m2 refers to the weight of the vertical mass block being 8kg, and a2 refers to the position adjustment accuracy of the vertical mass block being 0.05mm. L2 represents the movable stroke of the horizontal mass block, which is 50mm. The total satellite weight is M=100kg. Therefore, the satellite's vertical center of mass adjustment range is x1=(m2·L2) / M, and the center of mass adjustment accuracy is d2=(m2·a2) / M. This results in a vertical center of mass adjustment range of 0-4mm and an accuracy of 0.004mm, meeting the high-precision adjustment design requirements. The vertical center of mass adjustment mechanism mainly consists of a knob 2-5 connected to a bevel gear set and a lifting screw 2-7. Rotating the knob 2-5 simultaneously rotates the lifting screw 2-7. This ensures that the vertical center of mass adjustment mechanism adjusts... The lifting screw 2-7 and the vertical center of gravity adjustment mass block 2-8 are connected by threads. The four sides of the vertical center of gravity adjustment mass block cooperate with the housing 2-4 of the vertical center of gravity adjustment mechanism to ensure that the vertical center of gravity adjustment mass block does not rotate. This allows the rotation of the lifting screw 2-7 to drive the vertical center of gravity adjustment mass block 2-8 to move up and down, thereby fulfilling the vertical center of gravity adjustment function. The base 2-6 of the vertical center of gravity adjustment mechanism can be fixed to the housing 2-4 of the vertical center of gravity adjustment mechanism by bolts. At the same time, the bolts can be used to fix the base 2-6 of the vertical center of gravity adjustment mechanism and the satellite overall frame 1 through the through holes reserved on the base 2-6.

[0037] The outer walls of the center of gravity fine-tuning mechanism 2 are equipped with wall boxes 2-15. Inside the wall boxes 2-15, oil bladders 2-16 are installed. A sealing interface 2-17 is integrated on one side of the wall boxes 2-15. The port of the sealing interface 2-17 is connected to an oil pipe 2-18. An oil pump 2-19 is installed at the end of the oil pipe 2-18 away from the sealing interface 2-17. The inlet end of the oil pump 2-19 is connected to an oil pipe 2-20. The oil bladder 2-16 is connected to the oil pipe 2-18 through the sealing interface 2-17. The oil pipe 2-18 is connected to the oil pipe 2-20 through the oil pump 2-19. An oil pipe box 1-2 is installed at the lower end of the oil pipe 2-20. A connection port 1-3 is integrated on the top of the oil pipe box 1-2. The oil pipe box 1-2 is connected to the oil pipe 2-20 through the connection port 1-3. A bottom cylinder 1-1 is installed on the outside of the oil pipe box 1-2.

[0038] Specifically, a wall box 2-15 is installed on the outer wall of the center of gravity fine-tuning mechanism 2. Oil pipe 2-20 and oil pipe 2-18 are connected by an oil pump 2-19. Oil from the inside of 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 center of gravity fine-tuning mechanism 2 increases. This, in conjunction with the three-axis adjustment structure of the center of gravity fine-tuning mechanism 2, adjusts the center of gravity. Based on the actual situation of the three-axis adjustment, oil is then added to the wall box on the corresponding side. Through the change in weight, the center of gravity of the center of gravity fine-tuning mechanism 2 is fine-tuned.

[0039] A ground-based simulated satellite includes an overall satellite frame 1. A tungsten wire clamping housing 9-4 is mounted on the top of the overall satellite frame 1. A wedge block 9-2 is installed inside the tungsten wire clamping housing 9-4. A tungsten wire 9-1 is inserted inside the wedge block 9-2. A fastening bolt 9-3 for suspension connection is provided at the bottom of the tungsten wire clamping housing 9-4. The tungsten wire clamping housing 9-4 is connected to the overall satellite frame 1 through the fastening bolt 9-3. The lower end of the tungsten wire 9-1 is fixedly connected to the interior of the wedge block 9-2.

[0040] Specifically, the tungsten wire 9-1 is clamped by a wedge block through a through hole in the upper part of the tungsten wire clamping housing 9-4. The fastening bolt 9-3 is connected to the lower part of the tungsten wire clamping housing 9-4 by bolts. Tightening the fastening bolt 9-3 can provide a tightening force to the wedge block 9-2, thereby ensuring that the wedge block 9-2 has a sufficiently large clamping force on the tungsten wire 9-1. In addition, the surface of the wedge block 9-2 in contact with the tungsten wire 9-1 is made as rough as possible to provide higher friction. The top cover above the satellite frame 1 has a through hole in the center to allow the tungsten wire to pass through, and the top cover is fixed to the satellite frame 1 by bolts, thereby ensuring that the ground simulation satellite can be suspended by the tungsten wire.

[0041] A controller 3 is installed on the left side inside the satellite frame 1. Micro-thrusters 4 are installed on the outside of the satellite frame 1. A nitrogen storage tank 5 is installed in the middle inside the satellite frame 1. A power supply 6 is installed on the right side of the nitrogen storage tank 5. Laser displacement sensors 7 are installed on the left and right sides of the bottom of the satellite frame 1. A six-degree-of-freedom displacement stage 8 is installed at the bottom of the satellite frame 1.

[0042] The micro-thrusters 4 are arranged in a cross shape about the symmetrical center line of the satellite's overall frame 1, and the six-degree-of-freedom displacement stage 8 is movably connected to the bottom of the satellite's overall frame 1. The satellite's overall frame 1 is suspended by tungsten wires to simulate the weightlessness of the satellite in space. Since tungsten wires have good tensile strength but poor shear strength, a tungsten wire clamping mechanism is used to connect the tungsten wires and the satellite, while avoiding the tungsten wires being subjected to shear forces.

[0043] Specifically, power supply 6 provides power to the entire system, ensuring the operation of the control system. Controller 3 precisely controls the micro-thrusters 4 to generate thrust. The micro-thrusters 4 are fixed to the satellite's overall frame 1 via connectors, and eight are distributed along the X and Y axes respectively. They control the position and attitude of the simulated satellite by generating thrust. Nitrogen storage tank 5 stores nitrogen, ensuring continuous system operation for two hours. The six-degree-of-freedom displacement stage 8 provides relative displacement with the simulated satellite for quality inspection. Laser displacement sensor 7 monitors the simulated satellite's position in real time and simultaneously feeds back signals to the control system.

[0044] Working principle: The upper structure of the satellite's overall frame 1 mainly houses the power supply 6, controller 3, micro-thruster 4, and nitrogen storage tank 5, while the lower structure mainly houses the laser displacement sensor 7 and other hardware, thereby simulating the satellite's weightlessness in space through the tungsten wire 9-1.

[0045] During triaxial adjustment, the horizontal center-of-gravity adjustment mass block 2-1 is placed in the groove of the horizontal center-of-gravity adjustment mass block base 2-2. Fine-tuning of the center of gravity along the X-axis is achieved via the horizontal X-axis center-of-gravity adjustment knob 2-11. Tightening the horizontal X-axis center-of-gravity adjustment fixing bolt 2-14 fixes the position of the horizontal center-of-gravity mass block, thus determining the center-of-gravity position along the X-axis. The horizontal center-of-gravity adjustment mass block base 2-2 is placed in the groove of the horizontal center-of-gravity adjustment mass block fixing base 2-3 to achieve horizontal Y-axis center-of-gravity adjustment. The horizontal center-of-gravity adjustment mass block fixing base 2-3 is bolted to the vertical center-of-gravity adjustment mechanism housing 2-4. The vertical center-of-gravity adjustment mechanism knob 2-5 is connected through a pre-drilled hole on the vertical center-of-gravity adjustment mechanism housing 2-4. The vertical center of gravity adjustment mechanism housing 2-4 is fixedly connected to the vertical center of gravity adjustment mechanism base 2-6 by bolts. Additionally, the horizontal center of gravity adjustment mass block 2-1 is placed in the groove of the horizontal center of gravity adjustment mass block base 2-2 and connected to the horizontal X-axis center of gravity adjustment knob 2-11 by threads. The horizontal X-axis center of gravity adjustment knob and mass block base connector 2-12 are fixedly connected to the horizontal center of gravity adjustment mass block base 2-2 by bolts, ensuring a fixed relative displacement of the horizontal X-axis center of gravity adjustment knob 2-11 and the horizontal center of gravity adjustment mass block base 2-2 along the X-axis. Rotating the horizontal X-axis center of gravity adjustment knob 2-11 then achieves fine-tuning of the center of gravity along the X-axis. Tightening the horizontal X-axis center of mass adjustment fixing bolt 2-14 can fix the position of the horizontal center of mass block, thereby determining the center of mass position along the X-axis. The horizontal center of mass adjustment block base 2-2 is placed in the groove of the horizontal center of mass adjustment block fixing base 2-3 and is connected to the horizontal Y-axis center of mass adjustment knob 2-9 by threads. The horizontal Y-axis center of mass adjustment knob and fixing base connector 2-10 are fixed to the horizontal center of mass adjustment block fixing base 2-3 by bolts, which can ensure that the relative displacement of the horizontal Y-axis center of mass adjustment knob 2-9 and the horizontal center of mass adjustment block fixing base 2-3 along the Y-axis is fixed, thereby realizing the function of fine adjustment of the center of mass along the horizontal Y-axis.

[0046] The vertical center of mass adjustment mechanism is arranged along the satellite's Z-axis, allowing adjustment of the mass block's vertical position to adjust the satellite's center of mass in the Z-direction. The vertical center of mass adjustment mechanism knob 2-5 is connected to the vertical center of mass adjustment mechanism lifting screw 2-7 via a bevel gear set, ensuring that rotating the knob 2-5 simultaneously rotates the lifting screw 2-7. Since the vertical center of mass adjustment mechanism lifting screw 2-7 and the vertical center of mass adjustment mass block 2-8 are connected by threads, the four sides of the vertical center of mass adjustment mass block 2-8... The vertical center of gravity adjustment mechanism housing 2-4 is used in conjunction with the vertical center of gravity adjustment mechanism housing 2-4 to ensure that the vertical center of gravity adjustment mass block 2-8 does not rotate. This allows the vertical center of gravity adjustment mechanism lifting screw 2-7 to rotate and drive the vertical center of gravity adjustment mass block 2-8 to move up and down, thereby fulfilling the vertical center of gravity adjustment function. The vertical center of gravity adjustment mechanism base 2-6 can be fixedly connected to the vertical center of gravity adjustment mechanism housing 2-4 by bolts. At the same time, the bolts can be used to fix the vertical center of gravity adjustment mechanism base 2-6 and the satellite overall frame 1 through the through holes reserved on the vertical center of gravity adjustment mechanism base 2-6.

[0047] The position of the horizontal centroid mass block can be fixed by tightening the horizontal Y-axis centroid adjustment fixing bolt 2-13, thereby determining the centroid position along the Y-axis. The X-axis, Y-axis and Z-axis of the satellite are determined by the vertical centroid adjustment mechanism and the horizontal centroid adjustment mechanism, respectively, realizing the centroid adjustment of three axes at the same time. This facilitates the fine adjustment of the satellite's centroid, greatly reduces the space volume occupied on the satellite, facilitates the assembly with the satellite, and avoids interference problems relative to the simulated satellite.

[0048] The center of gravity fine-tuning mechanism 2 has wall boxes 2-15 installed on all four sides, and oil bladders 2-16 are installed inside each wall box 2-15. The structure and weight of the wall boxes 2-15 on all four sides are the same. When no oil is filled into the oil bladders 2-16, the center of gravity fine-tuning mechanism 2 maintains its initial balance and then performs center of gravity adjustment in three axes. The oil pump 2-19 inputs the oil from the oil pipe box 1-2 into the oil pipe 2-18 through the second oil pipe 2-20. The oil is then poured into the oil bladders 2-16 through the first oil pipe 2-18. When the oil enters the oil bladders 2-16, the weight of the center of gravity fine-tuning mechanism 2 on the side with oil in it increases, while the other three sides remain the same. The center of gravity is shifted and adjusted by filling the oil bladders 2-16 with oil, which in turn works with the three-axis adjustment structure of the center of gravity fine-tuning mechanism 2 to adjust the center of gravity.

[0049] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A three-axis centroid fine-tuning mechanism for ground-based simulated satellites, characterized in that, The system includes a satellite overall frame (1), inside which a center of mass fine-tuning mechanism (2) is installed. A horizontal center of mass adjustment mass block (2-1) is installed on the top of the center of mass fine-tuning mechanism (2), and a horizontal center of mass adjustment mass block base (2-2) is installed on the lower surface of the horizontal center of mass adjustment mass block (2-1). Wall boxes (2-15) are installed on the outer walls of the center of mass fine-tuning mechanism (2), and an oil bladder (2-16) is installed inside the wall box (2-15). A sealing interface (2-17) is integrally provided on one side of the wall box (2-15). The sealing interface (2-17) is connected to an oil pipe (2-18). An oil pump (2-19) is installed at the end of the oil pipe (2-18) away from the sealing interface (2-17). The inlet of the oil pump (2-19) is connected to an oil pipe (2-20). The oil bladder (2-16) is interconnected with the oil pipe (2-18) through the sealing interface (2-17). The oil pipe (2-18) is interconnected with the oil pipe (2-20) through the oil pump (2-19). An oil pipe box (1-) is installed at the lower end of the oil pipe (2-10). 2) The top of the oil pipe box (1-2) is integrally provided with a connection port (1-3). The oil pipe box (1-2) is connected to the second oil pipe (2-20) through the connection port (1-3). A bottom cylinder (1-1) is installed on the outside of the oil pipe box (1-2). A horizontal center of gravity adjustment mass block fixing base (2-3) is fixedly installed at the bottom of the horizontal center of gravity adjustment mass block fixing base (2-2). A vertical center of gravity adjustment mechanism housing (2-4) is installed below the horizontal center of gravity adjustment mass block fixing base (2-3). The left and right sides of 2-4) are connected with vertical center of mass adjustment mechanism knobs (2-5). The bottom of the vertical center of mass adjustment mechanism housing (2-4) is fixedly installed 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 installed with a horizontal X-axis center of mass adjustment knob (2-11). The vertical center of mass adjustment mechanism lifting screw (2-7) is vertically set at the center line of the surface of the vertical center of mass adjustment mechanism base (2-6). The top of the vertical center of mass adjustment mechanism lifting screw (2-7) is installed with a vertical center of mass adjustment mass block (2-8).

2. The three-axis centroid fine-tuning mechanism for a ground-based simulated satellite according to claim 1, characterized in that, The vertical center of gravity adjustment mechanism lifting screw (2-7) and the vertical center of gravity adjustment mechanism knob (2-5) are meshed.

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

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

5. The three-axis centroid fine-tuning mechanism for a ground-based simulated satellite according to claim 1, characterized in that, The horizontal X-axis centroid adjustment knob (2-11) is provided with a horizontal X-axis centroid adjustment knob and mass block base connector (2-12) on its outer side.

6. A ground-based simulated satellite, characterized in that, Includes the three-axis centroid fine-tuning mechanism as described in any one of claims 1-5; the top of the satellite overall frame (1) is equipped with a tungsten wire clamping housing (9-4). A controller (3) is installed on the left side inside the satellite frame (1). Micro-thrusters (4) are installed on the outside of the satellite frame (1). A nitrogen storage tank (5) is installed in the middle inside the satellite frame (1). A power supply (6) is installed on the right side of the nitrogen storage tank (5). Laser displacement sensors (7) are installed on the left and right sides of the bottom of the satellite frame (1). A six-degree-of-freedom displacement stage (8) is installed at the bottom of the satellite frame (1). A wedge block (9-2) is installed inside the tungsten wire clamping housing (9-4), and a tungsten wire (9-1) is inserted inside the wedge block (9-2). A fastening bolt (9-3) for suspension connection is provided at the bottom of the tungsten wire clamping housing (9-4).

7. A ground-based simulated satellite according to claim 6, characterized in that, The micro-thrusters (4) are arranged in a cross shape about the symmetrical center line of the overall satellite frame (1).

8. A ground-based simulated satellite according to claim 7, characterized in that, The tungsten wire clamp housing (9-4) is connected to the satellite frame (1) by fastening bolts (9-3), and the lower end of the tungsten wire (9-1) is fixedly connected to the inside of the wedge block (9-2).

9. A ground-based simulated satellite according to claim 6, characterized in that, The six-degree-of-freedom displacement stage (8) is connected to the bottom of the satellite's overall frame (1) by a movable connection.

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