A deployable satellite characteristic testing device

Abstract

The present invention discloses a deployable satellite characteristic testing device, comprising a satellite, the satellite being mounted on one end of a satellite connection ring, the other end of the satellite connection ring being provided with a rotating disk, the rotating disk being connected to one end of a vertical system, the rotating disk being capable of self-rotation on one end of the vertical system, the other end of the vertical system being provided with an axial hole and a plurality of connecting and fixing screws, and a horizontal system, one end of the horizontal system being provided with a rotating shaft and a plurality of small steel sleeves, the plurality of connecting and fixing screws being in a one-to-one correspondence with the plurality of small steel sleeves, the rotating shaft being inserted into the axial hole to form a movable connection structure, the connecting and fixing screws being inserted into corresponding small steel sleeves and being threadedly connected thereto. The beneficial effects of the present invention are simple structure and wide applicability.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite characteristic monitoring, in particular to a deployable satellite characteristic testing device. Background Art

[0002] After satellite assembly is complete, the satellite's Z-axis center of mass needs to be tested. Currently, satellites can only be lifted vertically, and the lifting device does not have the ability to flip the satellite. To test the satellite's Z-axis center of mass, another device must be used to flip the satellite 90°.

[0003] To address these technical issues, during satellite production, technicians typically use traditional L-shaped beams to perform testing, which can be time-consuming and unreliable. To improve efficiency and ensure safety, a new, deployable characteristic testing device must be developed to increase testing efficiency. Summary of the Invention

[0004] The purpose of the present invention is to solve the above problems and to design a deployable satellite characteristic testing device.

[0005] The technical solution of the present invention to achieve the above-mentioned object is a deployable satellite characteristic testing device, comprising a satellite, the satellite being mounted on one end of a satellite connection ring, and a rotating disk being provided on the other end of the satellite connection ring.

[0006] The rotating disc is connected to one end of the vertical system, and the rotating disc can rotate on one end of the vertical system. The other end of the vertical system is provided with an axial hole and a plurality of connecting and fixing screws. It also includes a horizontal system, and one end of the horizontal system is provided with a rotating shaft and a plurality of small steel sleeves. The plurality of connecting and fixing screws and the plurality of small steel sleeves are in a one-to-one correspondence. The rotating shaft is inserted into the axial hole to form a movable connection structure, and the connecting and fixing screws are inserted into the corresponding small steel sleeves and are threadedly connected thereto.

[0007] The horizontal system includes a horizontal beam, the rotating shaft and several small steel sleeves are located at one end of the horizontal beam, a fixed counterweight is installed on the other end of the horizontal beam, a counterweight mounting screw is fixedly installed on the fixed counterweight, one end of the counterweight mounting screw is inserted into the fixed counterweight, several movable counterweights are inserted into the counterweight mounting screw, a hexagonal nut is installed on the other end of the counterweight mounting screw, a lifting hole is provided on the horizontal beam, the lifting hole is close to the other end of the horizontal beam, a fixed bracket is installed at the lower edge of the horizontal beam, a connecting disc is fixedly installed on the lower end of the fixed bracket, and a center positioning shaft is fixedly installed on the lower surface of the connecting disc.

[0008] A vernier caliper is fixedly mounted on the horizontal beam, and the vernier caliper is close to the lower edge of the horizontal beam. The length direction of the vernier caliper is the same as the length direction of the horizontal beam. A slide rail is arranged below the vernier caliper, and the length direction of the slide rail is parallel to the length direction of the vernier caliper. A pointer is provided on the slide rail, and the pointer can slide along the length direction of the slide rail. A bearing mounting seat is fixedly mounted on the lower edge of the horizontal beam, and an isolation ring is installed in the bearing mounting seat. Planar thrust ball bearings are installed on both sides of the isolation ring. It also includes a moving screw, one end of the moving screw rod passes through the bearing mounting seat, and one end of the moving screw rod passes through the isolation ring and thrust ball bearing in the bearing mounting seat. The other end of the moving screw rod passes through the pointer and is threadedly connected to the pointer. When the moving screw rod rotates, it can drive the pointer to slide along the length direction of the guide rail.

[0009] The length direction of the counterweight mounting screw is the same as the length direction of the horizontal beam. The movable counterweight is a sheet-like body with a through hole in the center. A lifting hole reinforcement sleeve is installed on the lifting hole.

[0010] The vertical system includes a vertical beam, the axial hole and several connecting and fixing screws are all located at the other end of the vertical beam, a shell is fixedly installed on one end of the vertical beam, two conical thrust bearings are installed in the shell, and the two conical thrust bearings are respectively close to the two ends of the shell, a rotating main shaft is provided on the shell, the rotating main shaft passes through the two conical thrust bearings, both ends of the rotating main shaft extend outside the shell, the shell is a shell with one end closed and the other end open, a rear support mounting plate is fixedly installed at the opening of the other end of the shell, thrust ball bearings are both installed on the closed surface of the shell and the rear support mounting plate, one end of the shell is movably connected to the rotating disk through the thrust ball bearing, one end of the rotating main shaft is inserted into one end face of the satellite connecting ring and fixedly connected thereto by bolts, the rotating main shaft can drive the satellite connecting ring to rotate synchronously, the rear support mounting plate is movably connected to the rotating scale disk through the thrust ball bearing, the other end of the rotating main shaft passes through the rotating scale disk, and a rotating mechanism is installed on the other end of the rotating main shaft, and the rotating mechanism drives the rotating main shaft to rotate.

[0011] The rotating mechanism includes a turbine mounted on the other end of the rotating main shaft, the turbine is fixedly connected to the other end of the rotating main shaft through a round locking nut to form a synchronous rotation structure, and also includes a rotating worm, the rotating worm is engaged with the turbine, and the turbine rotates under the drive of the rotating worm.

[0012] A correction gasket is provided between one end surface of the satellite connection ring and one end surface of the shell.

[0013] A cylindrical hole self-aligning ball bearing is embedded on the side surface of the satellite connecting ring, a self-aligning bearing bracket is installed on the cylindrical hole self-aligning ball bearing, a height adjustment screw is installed on the self-aligning bearing bracket, one end of the height adjustment screw is fixedly connected to the self-aligning bearing bracket, and a support frame is provided on the other end of the height adjustment screw. The other end of the height adjustment screw is inserted into the support frame and threadedly connected to the support frame, and the support frame can move along the length direction of the height adjustment screw.

[0014] The center line of the cylindrical hole self-aligning ball bearing, the center line of the self-aligning bearing bracket, the center line of the height adjustment screw and the center line of the support frame are all located on the same straight line, and the straight line is perpendicular to the side surface of the satellite connecting ring. The support frame is a cylinder with one end open and the other end closed. The other end of the height adjustment screw is inserted into the open end of the support frame and threadedly connected to the open end of the support frame.

[0015] The connecting and fixing screws are distributed on the same circumference at equal angles with the shaft hole as the center.

[0016] Beneficial effects

[0017] A deployable satellite characteristic testing device manufactured using the technical solution of the present invention has the following advantages:

[0018] 1. The device itself is light in weight, has little deformation, is easy to operate, has a reasonable structure and is easy to assemble. It also has the advantages of easy operation, fast assembly speed, safety and reliability. The effect of satellite testing is very good.

[0019] 2. This device solves the problems of long test operation time, poor safety and reliability, etc. At the same time, it is easy to operate, safe and reliable, and improves work efficiency by nearly 2 times;

[0020] 3. This device is highly versatile and can be used to test the mass, center of mass, and moment of inertia of satellites of different sizes. It can also be used to measure the mass, center of mass, and moment of inertia of other products. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 1 is a schematic structural diagram of a deployable satellite characteristic testing device in an initial state according to the present invention;

[0022] Figure 2 It is a structural diagram of the horizontal system of the present invention;

[0023] Figure 3 Schematic diagram of the cross-sectional structure of the AA surface of the present invention;

[0024] Figure 4 It is a partial enlarged structural diagram of the bearing mounting seat of the present invention;

[0025] Figure 5 It is a structural schematic diagram of the vertical system of the present invention;

[0026] Figure 6 It is a schematic structural diagram of a deployable satellite characteristic testing device according to the present invention in a state ready for testing;

[0027] Figure 7 is a process flow chart for preparing the horizontal beam according to the present invention;

[0028] Figure 8 is a process flow chart for preparing a satellite connection ring according to the present invention;

[0029] In the figure, 1. Satellite; 2. Satellite connecting ring; 3. Rotating disk; 4. Vertical system; 5. Axis hole; 6. Connecting screw; 7. Horizontal system; 8. Rotating axis; 9. Small steel sleeve; 10. Horizontal beam; 11. Fixed counterweight; 12. Counterweight mounting screw; 13. Movable counterweight; 14. Hexagonal nut; 15. Lifting hole; 16. Fixed bracket; 17. Connecting disk; 18. Centering shaft; 19. Vernier scale; 20. Slide rail; 21. Pointer; 22. Bearing Mounting seat; 23. Isolation ring; 24. Plane thrust ball bearing; 25. Moving screw; 26. Vertical beam; 27. Housing; 28. Conical thrust bearing; 29. ​​Rotating spindle; 30. Rear support mounting plate; 31. Thrust ball bearing; 32. Rotating scale disk; 33. Turbine; 34. Round locking nut; 35. Rotating worm; 36. Correction gasket; 37. Cylindrical hole self-aligning ball bearing; 38. Self-aligning bearing bracket; 39. Height adjustment screw; 40. Support frame. DETAILED DESCRIPTION

[0030] The present invention will be described in detail below with reference to the accompanying drawings. Figure 1-8 As shown;

[0031] The invention of the present application lies in that a rotating disc is connected to one end of a vertical system 4, and the rotating disc can rotate on one end of the vertical system. The other end of the vertical system is provided with an axial hole 5 and a plurality of connecting and fixing screws 6. The horizontal system also includes a horizontal system, and one end of the horizontal system 7 is provided with a rotating shaft 8 and a plurality of small steel sleeves 9. The plurality of connecting and fixing screws and the plurality of small steel sleeves are in a one-to-one correspondence. The rotating shaft is inserted into the axial hole to form a movable connection structure, and the connecting and fixing screws are inserted into the corresponding small steel sleeves and are threadedly connected thereto.

[0032] The invention of the present application also lies in that the horizontal system includes a horizontal beam 10, the rotating shaft and several small steel sleeves are located at one end of the horizontal beam, a fixed counterweight 11 is installed on the other end of the horizontal beam, a counterweight mounting screw 12 is fixedly installed on the fixed counterweight, one end of the counterweight mounting screw is inserted into the fixed counterweight, and several movable counterweights 13 are inserted into the counterweight mounting screw, a hexagonal nut 14 is installed on the other end of the counterweight mounting screw, a lifting hole 15 is provided on the horizontal beam, and the lifting hole is close to the other end of the horizontal beam, a fixed bracket 16 is installed at the lower edge of the horizontal beam, a connecting disc 17 is fixedly installed on the lower end of the fixed bracket, a center positioning shaft 18 is fixedly installed on the lower surface of the connecting disc, a vernier scale 19 is fixedly installed on the horizontal beam, and the vernier scale Close to the lower edge of the horizontal beam, the length direction of the vernier is the same as the length direction of the horizontal beam, and a slide rail 20 is arranged below the vernier, and the length direction of the slide rail is parallel to the length direction of the vernier, and a pointer 21 is provided on the slide rail, and the pointer can slide along the length direction of the slide rail, and a bearing mounting seat 22 is fixedly installed on the lower edge of the horizontal beam, and an isolation ring 23 is installed in the bearing mounting seat, and plane thrust ball bearings 24 are installed on both sides of the isolation ring, and also include a moving screw 25, one end of the moving screw passes through the bearing mounting seat, and one end of the moving screw passes through the isolation ring and the thrust ball bearing in the bearing mounting seat, and the other end of the moving screw passes through the pointer and is threadedly connected to the pointer, and when the moving screw rotates, it can drive the pointer to slide along the length direction of the guide rail;

[0033] The innovation of the present application is that the vertical system includes a vertical beam 26, the axial hole and several connecting and fixing screws are located at the other end of the vertical beam, a shell 27 is fixedly installed on one end of the vertical beam, two conical thrust bearings 28 are installed in the shell, and the two conical thrust bearings are close to the two ends of the shell respectively, a rotating main shaft 29 is provided on the shell, the rotating main shaft passes through the two conical thrust bearings, both ends of the rotating main shaft extend outside the shell, the shell is a shell with one end closed and the other end open, a rear support mounting plate 30 is fixedly installed at the opening at the other end of the shell, thrust ball bearings 31 are installed on the closed surface and the rear support mounting plate of the shell, one end of the shell is movably connected to the rotating disc through the thrust ball bearing, and one end of the rotating main shaft Insert one end face of the satellite connecting ring and fix it with bolts. The rotating main shaft can drive the satellite connecting ring to rotate synchronously. The rear support mounting plate is movably connected to the rotating scale disk 32 through a thrust ball bearing. The other end of the rotating main shaft passes through the rotating scale disk. A rotating mechanism is installed on the other end of the rotating main shaft. The rotating mechanism drives the rotating main shaft to rotate. The rotating mechanism includes a turbine 33 sleeved on the other end of the rotating main shaft. The turbine is fixedly connected to the other end of the rotating main shaft through a circular locking nut 34 to form a synchronous rotation structure. It also includes a rotating worm 35. The rotating worm is engaged with the turbine. The turbine rotates under the drive of the rotating worm. A correction gasket 36 is provided between one end face of the satellite connecting ring and one end face of the shell.

[0034] The creative point of the present application is that a cylindrical hole self-aligning ball bearing 37 is embedded on the side surface of the satellite connecting ring, a self-aligning bearing bracket 38 is installed on the cylindrical hole self-aligning ball bearing, and a height adjustment screw 39 is installed on the self-aligning bearing bracket. One end of the height adjustment screw is fixedly connected to the self-aligning bearing bracket, and the other end of the height adjustment screw is provided with a support frame 40. The other end of the height adjustment screw is inserted into the support frame and threadedly connected to the support frame, and the support frame can move along the length direction of the height adjustment screw.

[0035] During the implementation of the technical solution of this application, eight small steel sleeves, a rotating shaft, a lifting hole, and a lifting hole reinforcement sleeve are provided on the horizontal beam. A vernier scale is provided on the horizontal beam. The movable screw, bearing mounting seat, isolation ring, and two plane thrust ball bearings constitute the driving structure of the pointer on the vernier scale. The horizontal beam is equipped with an 88.5 kg fixed counterweight, 18 movable counterweight blocks, two counterweight mounting screws, and two hexagonal nuts.

[0036] The vertical system includes a vertical beam, which is connected to the horizontal beam through eight connecting and fixing screws. Both the vertical beam and the horizontal beam are made of ZL204 cast aluminum. The rotating spindle is installed on the shell through two 30000 tapered roller bearings. The rotating spindle is installed back to back. Two 51000 thrust ball bearings are installed in front and behind the vertical beam shell to increase the bending resistance of the rotating spindle. In order to achieve a clearance of 0.01mm after installation, the gap distance is determined by measuring the dimensions of the vertical beam shell and the rotating spindle and calculating. The shaft clearance after installation is adjusted to 0.01mm by adjusting the correction gasket. The rear support mounting plate is mounted on the shell of the vertical beam via a locking nut. The rotating mechanism comprises a rotating worm, a turbine, two M60X2 round nuts, and a rotating scale disk. After installation, one M60X2 round nut is used to lock the nut, and the other M60X2 round nut is reversely locked to prevent the nut from loosening. The support and protection device comprises a satellite connecting ring, two 10000 type cylindrical bore self-aligning ball bearings, a self-aligning bearing bracket, two height adjustment screws, and two support frames.

[0037] In the technical solution of this application, a vernier scale is installed on the horizontal system to display the position of the pointer. The vertical system is equipped with a satellite connection ring, which allows for 90-degree rotation on the horizontal system through eight connecting screws and a rotating axis. Both the horizontal and vertical systems are also equipped with dedicated lifting holes.

[0038] Figure 1 and Figure 6 The figure shows two states of the device: in one state, the horizontal system and the vertical system are in a straight line, and satellite 1 is lifted to the satellite connection disk of the vertical system using a sling and a sling, and then connected to the satellite connection disk using 24 M6 bolts, washers and nuts; in the other state, the satellite and the vertical system are rotated 90° around the rotation axis using a sling and a sling, and then fixed with connecting screws and nuts.

[0039] The horizontal system includes 8 small steel sleeves (4) made of 1Cr18Ni9Ti material with an inner hole of ￠10.5mm and a wall thickness of 1mm, a 40Cr quenched ￠80 inner hole of ￠50 rotating shaft, and a horizontal beam which is a one-piece cast aluminum alloy (ZL204) part with a length of 2800mm, a width of 350mm and a height of 400mm. It is composed of 4 pieces of 10mm thick aluminum plates and has reinforcing ribs at the bottom and in the middle. The specific production process of the horizontal beam is shown in the following figure. Figure 7 As shown;

[0040] according to Figure 7 It can be seen that the process flow of horizontal beams is as follows:

[0041] 1. The wooden mold is made according to the horizontal beam drawing, with an 8mm machining allowance added to the parts that need to be machined. In order to facilitate the mold removal, a 5° draft angle is added to the middle rib. Then the wooden mold is made, painted and dried after completion.

[0042] 2. The modeling is to use wooden molds to make upper molds, lower molds and clay cores;

[0043] 3. Sizing is to apply epoxy resin on the surface of the outer mold and mud core;

[0044] 4. Baking the mold is to ensure that there is no moisture in the outer film and the mud core. The baking temperature is 45° and the baking time is 5 hours.

[0045] 5. Mould closing is to put the upper mould, lower mould and clay core together;

[0046] 6. Casting is to inject the molten aluminum alloy (ZL204) into the mold through the casting port;

[0047] 7. Demolding is the process of taking out the cast parts after they have cooled naturally for 24 hours, removing the pouring nozzles and cleaning the sand.

[0048] 8. Tempering is to put the processed parts into the oven to remove casting stress. The tempering temperature is 185°, the tempering time is 8 hours, and the furnace insulation time is 24 hours before taking out the parts.

[0049] 9. Rough machining is to use a machining center to process the surface that needs to be processed, leaving a machining allowance of 3mm according to the drawing size;

[0050] 10. Stress relief is to put the rough-machined parts into the oven to remove the machining stress. The stress relief temperature is 195°, the stress relief time is 10 hours, and the furnace insulation time is 24 hours.

[0051] 11. Semi-finishing is the second processing on the surface that needs to be processed, leaving a 1mm margin according to the size of the drawing;

[0052] 12. Stabilization treatment is to put the semi-finished parts into a low-temperature box for low-temperature stress treatment at a temperature of -56°C for 4 hours and a furnace holding time of 12 hours, and then perform high-temperature stress relief treatment at a temperature of 165°C for 8 hours and a furnace holding time of 20 hours;

[0053] 13. Finishing is to process the required surface of the parts according to the drawing requirements to achieve the accuracy requirements of the drawing;

[0054] 14. Place the finished parts in a static state to achieve static balance on their surface;

[0055] 15. The surface treatment is to apply white spray paint according to the drawing requirements;

[0056] 16. Acceptance refers to the acceptance personnel checking the product item by item according to the requirements of the drawings;

[0057] 17. Warehousing means placing the processed parts into the warehouse and waiting for assembly.

[0058] The horizontal system shown is provided with a center of mass positioning point, and the center of mass positioning point includes a cross-slot pan head screw, a vernier caliper, a pointer, a connecting disc, and a center positioning shaft; the horizontal system shown is provided with a counterweight, and the counterweight includes a fixed counterweight. Due to the situation of the vertical beam system being installed, 500-600Kg of lead is poured at the tail end of the horizontal beam as a fixed counterweight; the movable counterweight is counterweighted according to actual conditions during the test; the counterweight mounting screw and hexagonal nut are used to install the movable counterweight; the horizontal system shown is provided with a moving device, and the moving device includes a fixed bracket, a moving screw, a bearing mounting seat, an isolation ring, and a plane thrust ball bearing; a lifting hole reinforcement sleeve with an inner hole of ￠60mm and a wall thickness of 1.5mm made of 1Cr18Ni9Ti material.

[0059] The vertical system includes a satellite connecting ring, which is an integrally cast aluminum alloy (ZL204) part. The specific production process of the satellite connecting ring is basically the same as the horizontal beam production process, among which the surface treatment of the satellite connecting ring is different. The surface treatment of the horizontal beam is sprayed with white paint, while the vertical beam is subjected to surface cold hardening and oxidation polarization. The specific production process is as follows: Figure 8 As shown;

[0060] according to Figure 8 It can be seen that the process flow of satellite connection ring is as follows:

[0061] 1. Deburring is to use chamfering tools to remove the sharp corners on the surface of the parts to prevent tip discharge during the oxidation process;

[0062] 2. Ultrasonic cleaning is to use an ultrasonic cleaning machine to clean parts and remove excess materials and impurities on the surface of parts and screw holes;

[0063] 3. Alkaline degreasing cleaning is done in an alkaline water tank. The temperature of the tank liquid (NaOH) is 50-58°C. The tank liquid cleans the surface of the parts while rolling.

[0064] 4. Rinsing is to clean the cleaned parts in a distilled water tank with the tank liquid in a rolling state;

[0065] 5. Cold hard oxidation treatment is carried out in a sulfuric acid solution tank with a concentration of 28-32%. When the temperature of the tank liquid (H2SO4) is 1-2°C, the oxidation time is 2.5-2.6 hours, and a DC power supply is added to the surface of the part with a voltage of 36-40V and a current of 2.5A / dm2. A very hard oxide film (Al2O3) is formed on the surface of the part. The thickness of the oxide film is 0.03mm and the hardness of the oxide film surface (HRC) is 50.

[0066] 6. Rinse again by placing the cold-hard oxidized parts in a distilled water tank with the tank liquid rolling;

[0067] 7. Acceptance refers to the acceptance personnel checking the product item by item according to the requirements of the drawings;

[0068] 8. Warehousing means placing the processed parts into the warehouse and waiting for assembly.

[0069] The vertical system is provided with a supporting device, which includes a cylindrical hole self-aligning ball bearing, a self-aligning bearing bracket, a height adjustment screw, a support frame, a connecting and fixing screw, and an adjusting height adjustment screw to enable the two sets of cylindrical hole self-aligning ball bearings to rollably contact the rotating disc 39.

[0070] The vertical system is provided with a rotating spindle device, which includes a rear support mounting plate, a rotating worm, a turbine, a round locking nut, a rotating spindle, a thrust ball bearing, a rotating scale disc, a locking nut, a tapered thrust bearing, a thrust bearing, a rotating disc and a correction gasket.

[0071] The rotating spindle is installed back-to-back, with two thrust ball bearings mounted on the vertical beam housing to increase bending resistance. After measuring the dimensions of the vertical beam housing and the rotating spindle, and determining the clearance distance through measurement and calculation, the size of the correction shims was adjusted to achieve the required 0.01mm clearance between the shafting after installation. To ensure the rotating spindle's flexible rotation, molybdenum disulfide was sprayed on all four shafts.

[0072] The rotating main shaft is provided with a rotating worm, a turbine and a rotating scale disk. After installation, they are locked with a round nut and another M60X2 round nut is reversely locked to prevent the nut from loosening, thereby achieving the purpose of small gap, flexible rotation and easy operation.

[0073] The materials and processing technology of the vertical beams and rotating discs in the vertical system are consistent with those of the horizontal beams and satellite connecting rings.

[0074] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include," "comprise," or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article, or device that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or elements inherent to such process, method, article, or device. In the absence of further limitations. The phrase "includes an element defined by..." does not exclude the presence of other identical elements in the process, method, article, or device that includes the element.

[0075] The above technical solutions only reflect the preferred technical solutions of the technical solutions of the present invention. Any changes that may be made to certain parts thereof by those skilled in the art all reflect the principles of the present invention and fall within the scope of protection of the present invention.

Claims

1. A deployable satellite characteristic test device, comprising a satellite (1), the satellite being mounted on one end of a satellite connection ring (2), and a rotating disk (3) being provided on the other end of the satellite connection ring, characterized in that: The rotating disc is connected to one end of the vertical system (4), and the rotating disc can rotate on one end of the vertical system. The other end of the vertical system is provided with an axial hole (5) and a plurality of connecting and fixing screws (6). The horizontal system also includes a horizontal system. One end of the horizontal system (7) is provided with a rotating shaft (8) and a plurality of small steel sleeves (9). The plurality of connecting and fixing screws and the plurality of small steel sleeves are in a one-to-one correspondence. The rotating shaft is inserted into the axial hole to form a movable connection structure. The connecting and fixing screws are inserted into the corresponding small steel sleeves and are threadedly connected thereto. The horizontal system includes a horizontal beam (10), a rotating shaft and a plurality of small steel sleeves are located at one end of the horizontal beam, a fixed counterweight (11) is installed on the other end of the horizontal beam, a counterweight mounting screw (12) is fixedly installed on the fixed counterweight, one end of the counterweight mounting screw is inserted into the fixed counterweight, a plurality of movable counterweights (13) are inserted into the counterweight mounting screw, a hexagonal nut (14) is installed on the other end of the counterweight mounting screw, a lifting hole (15) is provided on the horizontal beam, the lifting hole is close to the other end of the horizontal beam, a fixed bracket (16) is installed at the lower edge of the horizontal beam, a connecting disc (17) is fixedly installed at the lower end of the fixed bracket, and a center positioning shaft (18) is fixedly installed on the lower surface of the connecting disc; A vernier scale (19) is fixedly mounted on the horizontal beam, the vernier scale is close to the lower edge of the horizontal beam, the length direction of the vernier scale is the same as the length direction of the horizontal beam, a slide rail (20) is configured below the vernier scale, the length direction of the slide rail is parallel to the length direction of the vernier scale, a pointer (21) is provided on the slide rail, the pointer can slide along the length direction of the slide rail, a bearing mounting seat (22) is fixedly mounted on the lower edge of the horizontal beam, an isolation ring (23) is installed in the bearing mounting seat, and plane thrust ball bearings (24) are installed on both sides of the isolation ring. It also includes a moving screw (25), one end of the moving screw passes through the bearing mounting seat, one end of the moving screw passes through the isolation ring and the thrust ball bearing in the bearing mounting seat, the other end of the moving screw passes through the pointer and is threadedly connected to the pointer, and when the moving screw rotates, it can drive the pointer to slide along the length direction of the guide rail; The length direction of the counterweight installation screw is the same as the length direction of the horizontal beam. The movable counterweight is a sheet-like body with a through hole in the center, and a lifting hole reinforcement sleeve is installed on the lifting hole.

2. The deployable satellite characteristic testing device according to claim 1, characterized in that: The vertical system includes a vertical beam (26), the shaft hole and a plurality of connecting and fixing screws are located at the other end of the vertical beam, a housing (27) is fixedly installed on one end of the vertical beam, two conical thrust bearings (28) are installed in the housing, and the two conical thrust bearings are respectively close to the two ends of the housing, a rotating main shaft (29) is provided on the housing, the rotating main shaft passes through the two conical thrust bearings, and both ends of the rotating main shaft extend outside the housing, the housing is a housing with one end closed and the other end open, and a rear support mounting plate (30) is fixedly installed at the opening at the other end of the housing. ), the closed surface of the shell and the rear support mounting plate are both installed with a thrust ball bearing (31), one end of the shell is movably connected to the rotating disc through the thrust ball bearing, one end of the rotating main shaft is inserted into one end face of the satellite connecting ring and is fixedly connected thereto by a bolt, the rotating main shaft can drive the satellite connecting ring to rotate synchronously, the rear support mounting plate is movably connected to the rotating scale disc (32) through the thrust ball bearing, the other end of the rotating main shaft passes through the rotating scale disc, and a rotating mechanism is installed on the other end of the rotating main shaft, and the rotating mechanism drives the rotating main shaft to rotate.

3. The deployable satellite characteristic testing device according to claim 2, characterized in that: The rotating mechanism comprises a turbine (33) sleeved on the other end of the rotating main shaft, the turbine being fixedly connected to the other end of the rotating main shaft via a circular locking nut (34) to form a synchronous rotating structure, and further comprises a rotating worm (35) meshing with the turbine, and the turbine rotates under the drive of the rotating worm.

4. The deployable satellite characteristic testing device according to claim 2, characterized in that: A correction gasket (36) is provided between one end surface of the satellite connection ring and one end surface of the shell.

5. The deployable satellite characteristic testing device according to claim 4, characterized in that: A cylindrical hole self-aligning ball bearing (37) is embedded on the side surface of the satellite connection ring, a self-aligning bearing bracket (38) is installed on the cylindrical hole self-aligning ball bearing, and a height adjustment screw (39) is installed on the self-aligning bearing bracket. One end of the height adjustment screw is fixedly connected to the self-aligning bearing bracket, and the other end of the height adjustment screw is provided with a support frame (40). The other end of the height adjustment screw is inserted into the support frame and is threadedly connected to the support frame. The support frame can move along the length direction of the height adjustment screw.

6. The deployable satellite characteristic testing device according to claim 5, characterized in that: The center line of the cylindrical hole self-aligning ball bearing, the center line of the self-aligning bearing bracket, the center line of the height adjustment screw and the center line of the support frame are all located on the same straight line, and the straight line is perpendicular to the side surface of the satellite connecting ring. The support frame is a cylinder with one end open and the other end closed. The other end of the height adjustment screw is inserted into the open end of the support frame and threadedly connected to the open end of the support frame.

7. The deployable satellite characteristic testing device according to claim 1, characterized in that: The connecting and fixing screws are distributed on the same circumference at equal angles with the shaft hole as the center.

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