An attitude adjustment parking device and method for zero-gravity deployment tests

Abstract

The present invention provides an attitude adjustment and parking device and method for zero-gravity deployment tests, which includes a simulation wall assembly, a bracket assembly supported on both sides of the simulation wall assembly, and a pitch adjustment assembly and a roll adjustment assembly that respectively connect both sides of the simulation wall assembly to the bracket assembly. The bracket assembly can drive the simulation wall assembly to perform yaw-direction adjustment, the pitch adjustment assembly can drive the simulation wall assembly to perform pitch-direction adjustment, and the roll adjustment assembly can drive the simulation wall assembly to perform roll-direction adjustment. The present invention can support and park deployable solar wings / antennas and precisely adjust multi-degree-of-freedom attitudes. It adopts a detachable method, and the storage space occupied in the disassembled state is small, making transportation relatively convenient. It is easy to expand according to the size of the test equipment, and only a few parts need to be changed. It has the advantages of simple structure, few types of parts, and convenient assembly.

Description

Technical Field

[0001] The present invention relates to the technical field of measurement and testing, and particularly relates to an attitude adjustment and parking device and method for zero-gravity deployment tests. Background Art

[0002] Deployable solar wings / deployable antennas on satellites are connected to the satellites through deployment mechanisms. During the AIT stage (assembly, integration, and test) of the satellites, multiple deployment tests need to be carried out on the deployment mechanisms to verify the deployment accuracy of the deployment mechanisms and their ability to adapt to mechanical environments. Generally, the base structures of deployable solar wings / deployable antennas adopt flat plate structures, which have a large surface-to-thickness ratio (the thickness H dimension is much smaller than the length L and width B dimensions), and other accessories are installed on the front and back sides of the base structure.

[0003] Due to the influence of gravity on the ground, when testing the deployment mechanisms of solar wings / antennas, it is necessary to unload the gravity of the deployed solar wings / deployable antennas. Otherwise, gravity will generate additional torques on the rotating shafts of the deployment mechanisms, which will affect the smoothness of deployment and damage the accuracy of the deployment mechanisms, ultimately reducing the reliability of the deployment mechanisms during on-orbit deployment. The common practice is to make the rotating axis of the deployment mechanism of the deployable solar wing / deployable antenna perpendicular to the horizontal plane (the plane perpendicular to the direction of the gravity vector). In this way, the distance between the center of gravity position of the deployable solar wing / deployable antenna and the rotating shaft of the deployment mechanism is a constant value. At the same time, the gravity of the upper part of the deployable solar wing / deployable antenna is unloaded through a hanging system (the suspension force is equal to the force), so that the influence of gravity can be eliminated during the entire deployment process, and the deployment mechanism can be better protected.

[0004] In order to better unload the gravity of the deployable solar wing / deployable antenna, ideally, the rotating axis of the deployment mechanism needs to be precisely perpendicular to the horizontal plane. Generally, the solar wing / antenna needs to be installed on a simulation wall and supported and parked by a tooling. Since the usually tested ground is not ideally horizontal and errors will accumulate during the processing and assembly of the supporting tooling, it is very difficult to reach the ideal predetermined state after the solar wing / antenna is installed. Therefore, an attitude adjustment and parking device for deployment tests is needed, which can stably support and precisely adjust the attitude of the tested solar wing / antenna. The rotating axis of the deployment mechanism of the solar wing / antenna is adjusted to be as close as possible to the ideal predetermined state, so that the deployment mechanism can be better protected during multiple deployment tests. Summary of the Invention

[0005] The present invention aims to solve the problem of deploying and testing deployable solar wings / antennas, and provides an attitude adjustment and parking device and method for zero-gravity deployment tests. The device can support and park the deployable solar wings / antennas and accurately adjust their multi-degree-of-freedom attitudes. The device is detachable, and in a disassembled state, it occupies little storage space and is convenient to transport. The device can be expanded according to the size of the test equipment, and only a few parts need to be changed. The device has the advantages of a simple structure, a small number of parts, and easy assembly.

[0006] The present invention provides an attitude adjustment parking device for zero-gravity deployment testing, comprising a simulated wall assembly, a bracket assembly supported on both sides of the simulated wall assembly, and a pitch adjustment assembly and a roll adjustment assembly respectively connecting the two sides of the simulated wall assembly to the bracket assembly. The bracket assembly can drive the simulated wall assembly to adjust the yaw direction, the pitch adjustment assembly can drive the simulated wall assembly to adjust the pitch direction, and the roll adjustment assembly can drive the simulated wall assembly to adjust the roll direction.

[0007] The test product's body-fitting plate is fixedly connected to the simulated wall assembly. The test product is initially in a folded and compressed state. The test product's rotation axis is made perpendicular to the horizontal plane by adjusting the bracket assembly, pitch adjustment assembly, and roll adjustment assembly multiple times. The gravity unloading sling is then adjusted to unload the gravity of the test product's unfolded plate. The unfolded plate is then unlocked and unfolded.

[0008] The bracket assembly uses four brake casters connected to the bottom to adjust the yaw direction of the product under test around the Y axis. Once adjusted, it is fixed to the ground using a screw jack. The components of the bracket assembly are all detachable and can be expanded according to the size of the test product.

[0009] The pitch adjustment assembly is mounted on the outside of the vertical beam of the bracket assembly along the X-axis direction and is connected to both sides of the simulated wall assembly through the pitch adjustment block. When the pitch adjustment assembly is loose, it can move up and down along the second vertical beam to allow the product to be tested to be pitch adjusted around the X-axis. When adjusted to the appropriate position, it is fixed on the vertical beam of the bracket assembly by rotating and tightening the knurled adjustment screw.

[0010] The posture adjustment parking device for zero-gravity deployment testing described in the present invention preferably comprises a simulation wall assembly comprising a simulation wall body and connecting shafts, wherein the connecting shafts are two and are connected to the left and right sides of the simulation wall body respectively;

[0011] The simulation wall body is a plate-like structure with screw mounting holes on the left and right sides. Holes can be drilled in the simulation wall body according to the mechanical interface of the product to be tested. Both sides of the simulation wall body are connected to the pitch adjustment components.

[0012] The connecting shaft is T-shaped, one side of which is connected to the side of the simulation wall body through screws, and the other side extends into the roll adjustment component.

[0013] A posture adjustment and parking device for zero - gravity deployment test, as a preferred mode, the bracket assembly includes two cross - beams arranged in parallel along the Z - axis direction, a first vertical beam and a second vertical beam that are sequentially and perpendicularly connected to the middle of the cross - beam and extend in the Y - axis direction, a longitudinal beam connected between the two cross - beams, a screw - type jack connected to the outside of the cross - beam and extendable to the ground, and brake casters connected to both ends of the cross - beam;

[0014] The second vertical beam is connected to the top of the first vertical beam and co - axial with the first vertical beam. The simulation wall assembly is arranged between the two first vertical beams and the second vertical beam. The pitch adjustment assembly is movably connected to the first vertical beam or the second vertical beam. The connecting shaft and the rolling adjustment assembly are both connected to the top of the second vertical beam;

[0015] There are 2 cross - beams, 2 first vertical beams and 2 second vertical beams. The number of screw - type jacks and brake casters is 4. The brake casters can drive the simulation wall body to move or brake separately;

[0016] The cross - beam and the first vertical beam, the first vertical beam and the second vertical beam, and the longitudinal beam and the cross - beam are all detachably connected by screws;

[0017] Adjust the yaw direction around the Y - axis through 4 brake casters. After the adjustment is in place, use the screw - type jack to support and fix with the ground;

[0018] There are 4 bosses at the four corners of the simulation wall, and lifting point mounting holes for hoisting the posture adjustment and parking device are connected to the bosses. One side of the connecting shaft is fixed to the simulation wall by four screws, two as a group.

[0019] A posture adjustment and parking device for zero - gravity deployment test, as a preferred mode, the cross - beam, the first vertical beam, the second vertical beam, and the longitudinal beam are all hollow steel pipes with assembly interfaces. The number of longitudinal beams is two and they are symmetrically distributed;

[0020] The heights of the first vertical beam and the second vertical beam can be selected according to the size of the test product.

[0021] A posture adjustment and parking device for zero - gravity deployment test, as a preferred mode, the pitch adjustment assembly includes a compression knurled adjustment screw, a pitch mounting plate passing through the compression knurled adjustment screw, an extrusion block that is pressed against the end of the compression knurled adjustment screw, a connecting rod passing through the extrusion block and connected to both ends of the pitch mounting plate, a pitch adjustment block connected to the other end of the connecting rod, a pitch knurled adjustment screw connected to the other end of the pitch adjustment block, and a mounting tightening post connected to the end of the pitch knurled adjustment screw;

[0022] The connecting rod connects the pitching mounting plate and the pitching adjusting block into a whole and sleeves them on the second vertical beam. The extrusion block is embedded in the connecting rod, and the pitching knurled adjusting screw and the mounting tightening column fixedly connect the simulated wall body;

[0023] The pressing knurled adjusting screw includes a screw rod and an operating head with knurling and internal hexagon features. The pitching mounting plate is a plate-like structure that is threadedly connected to the screw rod of the pressing knurled adjusting screw in the middle and threadedly connected to the connecting rod at both ends. The screw rod of the pressing knurled adjusting screw is in threaded cooperation with the pitching mounting plate. The knurling of the operating head adjusts the mating depth until the end of the screw rod abuts against the extrusion block. A torque can be applied to the internal hexagon feature of the operating head through a tool to tighten the extrusion block;

[0024] The extrusion block is a plate-like structure with notches for avoiding the connecting rod at both ends. The extrusion block is placed on the outer wall of the second vertical beam. Threaded holes are provided at both ends of the connecting rod, and the pitching mounting plate and the pitching adjusting block are connected into a whole by screws. The notches at both ends of the extrusion block enable the connecting rod to be vertically embedded and wrap the second vertical beam inside;

[0025] The pitching adjusting block includes a horizontal plate threadedly connected to the connecting rod and extension plates vertically connected to both ends of the horizontal plate and extending towards the simulated wall body. The direction of the horizontal plate of the pitching adjusting block is the same as that of the pitching mounting plate and the extrusion block. Threaded mounting holes are provided at the ends of the extension plates of the pitching adjusting block. The pitching knurled adjusting screw includes a screw rod and an operating head with knurling and internal hexagon features. The screw rod of the pitching knurled adjusting screw is in threaded cooperation with the threaded hole of the extension plate of the pitching adjusting block, and the top end of the screw rod is threadedly connected to the tightening column. The tightening column tightly fixes the simulated wall body;

[0026] When the adjusting assembly is loose, it can move up and down along the second vertical beam. When adjusted to the appropriate position, manually adjust the pressing knurled adjusting screw so that the end of the screw rod of the pressing knurled adjusting screw abuts against the extrusion block, and apply a torque through a tool to tighten the extrusion block. The extrusion block and the pitching adjusting block jointly press and fix the second vertical beam.

[0027] In a preferred embodiment of the attitude adjustment and parking device for zero-gravity deployment test according to the present invention, the number of connecting rods is 4, two in a group, and the number of pitching knurled adjusting screws and tightening columns is both 2;

[0028] The 4 connecting rods connect the pitching mounting plate and the pitching adjusting block into a whole and sleeve them on the second vertical beam. The extrusion block is embedded in the 4 connecting rods.

[0029] In a preferred embodiment of the attitude adjustment and parking device for zero-gravity deployment test according to the present invention, the lower end of the rolling adjustment assembly is embedded inside the second vertical beam, the horizontal shaft of the connecting shaft is tightly fixed on the lifting block of the rolling adjustment assembly, and the horizontal roll direction of the connecting shaft is adjusted by changing the height of the lifting block of the rolling adjustment assembly, driving the simulated wall to perform a horizontal roll direction adjustment around the Z axis.

[0030] A posture adjustment and parking device for zero-gravity deployment test according to the present invention. As a preferred embodiment, the rolling adjustment assembly includes a vertical beam mounting block embedded in the lower end of the second vertical beam, an adjustment lifting ring whose lower end cylinder is matched with the central hole of the vertical beam mounting block, a lifting block screwed to the lower end of the adjustment lifting ring, a pressing connecting rod connected to one side of the top of the lifting block, a connecting shaft pin connecting the top of the pressing connecting rod to one side of the lifting block, a lifting pressing plate movably connected to the connecting shaft pin, a connecting screw passing through the lifting block and detachably connecting to the other end of the lifting pressing plate, and a set screw passing through the second vertical beam and the vertical beam mounting block in sequence and pressing against the side wall of the adjustment lifting ring;

[0031] The lower end of the vertical beam mounting block is a square structure smaller than the length and width inside the second vertical beam, the upper part is a docking boss larger than the length and width outside the second vertical beam, a threaded mounting hole for installing the set screw is arranged on the side along the Y-axis direction, and a circular through hole for inserting the adjustment lifting ring is arranged in the center;

[0032] The lower end of the adjustment lifting ring is a cylinder and a horizontally distributed annular notch is connected to the lower part of the cylinder, the upper end is a polygonal flange structure with a circular hole connected to the side, and the center of the adjustment lifting ring is an internal thread through hole threadedly connected to the lower end of the lifting block;

[0033] The lower end of the lifting block is an external threaded rod, the upper end is a convex platform with a V-shaped groove, and the horizontal shaft of the connecting shaft extends into the V-shaped groove;

[0034] The lifting pressing plate opens and closes with the connecting shaft pin as the axis. The bottom of the lifting pressing plate is connected with an arc-shaped notch in the same direction as the extension direction of the connecting shaft. The connecting shaft is placed in the V-shaped groove of the lifting block, and the connecting screw presses the connecting shaft between the lifting pressing plate and the lifting block;

[0035] The cylinder at the lower end of the adjustment lifting ring is installed in the central hole of the vertical beam mounting block. Two set screws pass through the side wall of the second vertical beam and the side wall of the vertical beam mounting block in sequence and are embedded in the annular notch at the lower end of the adjustment lifting ring for limiting. The lifting block is screwed to the adjustment lifting ring through the lower end screw, and the height of the lifting block can be changed by changing the thread engagement length;

[0036] The number of the adjustment assemblies 4 is 2 groups, and the two connecting shafts are respectively pressed;

[0037] The present invention provides a posture adjustment and parking method for zero-gravity deployment test, including the following steps:

[0038] S1. Assemble the simulation wall assembly, the bracket assembly, the pitch adjustment assembly and the roll adjustment assembly;

[0039] S2. First, install the body board of the test product on the simulation wall, and the unfolding board is suspended by the gravity unloading sling. The initial state of the test product is that the unfolding board is folded and pressed against the body board;

[0040] S3. Adjust the brake casters of the support assembly multiple times for yaw adjustment about the Y-axis, adjust the knurled adjustment screw of the pitch adjustment assembly multiple times for pitch adjustment about the X-axis, and adjust the height of the lifting block of the rolling adjustment assembly multiple times for roll adjustment about the Z-axis until the rotation axis of the test product is perpendicular to the horizontal plane, where the horizontal plane is a plane perpendicular to the direction of the gravity vector;

[0041] S4. Adjust the gravity unloading sling to unload the gravity of the deployment board;

[0042] S5. Unfold the deployment board around the body attachment board until it is coplanar with the body attachment board, and a posture adjustment and parking method for zero-gravity deployment test is completed.

[0043] In the posture adjustment and parking method for zero-gravity deployment test described in the present invention, as a preferred mode, in step S2, the test product is a solar wing panel or a phased array antenna including three sub-arrays. When the test product is a phased array antenna, the initial state of the phased array antenna is that the left and right phased array antenna sub-arrays are folded and pressed against the middle phased array antenna sub-array on the same side, the middle phased array antenna sub-array is connected to the simulation wall body, and the number of gravity unloading slings is two and they respectively suspend the left and right phased array antenna sub-arrays;

[0044] In step S5, the left and right phased array antenna sub-arrays are unfolded in sequence. First, the outermost phased array antenna sub-array is unfolded, and then the other phased array antenna sub-array is unfolded until the three phased array antenna sub-arrays are coplanar

[0045] The present invention has the following advantages:

[0046] (1) The present invention can support, park, and precisely adjust the multi-degree-of-freedom postures of deployable solar wings / antennas, eliminate the influence of gravity during the deployment test, and better protect the satellite deployment mechanism;

[0047] (2) The present invention adopts a detachable method. In the disassembled state, the storage occupies a small space and the transportation is relatively convenient; it is convenient to expand according to the size of the test equipment, and only a few parts need to be changed; it has the advantages of simple structure, few types of parts, and convenient assembly. Description of the Drawings

[0048] Figure 1 It is a structural schematic diagram of a posture adjustment and parking device for zero-gravity deployment test;

[0049] Figure 2 It is a structural schematic diagram of the simulation wall assembly of a posture adjustment and parking device for zero-gravity deployment test;

[0050] Figure 3Schematic structural diagram of a support assembly for an attitude adjustment and parking device used in zero-gravity deployment tests;

[0051] Figure 4 Exploded schematic diagram of a support assembly for an attitude adjustment and parking device used in zero-gravity deployment tests;

[0052] Figure 5 Exploded schematic diagram of a pitch adjustment assembly for an attitude adjustment and parking device used in zero-gravity deployment tests;

[0053] Figure 6 Schematic structural diagram of a pitch adjustment assembly for an attitude adjustment and parking device used in zero-gravity deployment tests;

[0054] Figure 7 Front view of a pitch adjustment assembly for an attitude adjustment and parking device used in zero-gravity deployment tests;

[0055] Figure 8 Exploded schematic diagram of a rolling adjustment assembly for an attitude adjustment and parking device used in zero-gravity deployment tests;

[0056] Figure 9 Schematic structural diagram of a rolling adjustment assembly for an attitude adjustment and parking device used in zero-gravity deployment tests;

[0057] Figure 10 Schematic sectional view of the installation state of a rolling adjustment assembly for an attitude adjustment and parking device used in zero-gravity deployment tests;

[0058] Figure 11 Schematic diagram of the usage state of an attitude adjustment and parking device used in zero-gravity deployment tests;

[0059] Figure 12a Schematic diagram of the initial deployment state of an attitude adjustment and parking device used in zero-gravity deployment tests;

[0060] Figure 12b Schematic diagram of the state during the deployment process of an attitude adjustment and parking device used in zero-gravity deployment tests;

[0061] Figure 12c Schematic diagram of the state when the deployment of an attitude adjustment and parking device used in zero-gravity deployment tests is completed;

[0062] Figure 13 Schematic diagram of the usage state of an attitude adjustment and parking device used in zero-gravity deployment tests for adjusting a phased array antenna;

[0063] Figure 14 Partial enlarged view of the hoisting for an attitude adjustment and parking device used in zero-gravity deployment tests for adjusting a phased array antenna;

[0064] Figure 15a Schematic diagram of the starting deployment state of the phased array antenna adjusted by an attitude adjustment and parking device for zero-gravity deployment test

[0065] Figure 15b Schematic diagram of the state during the deployment process of the phased array antenna adjusted by an attitude adjustment and parking device for zero-gravity deployment test

[0066] Figure 15c Schematic diagram of the state when the deployment of the phased array antenna adjusted by an attitude adjustment and parking device for zero-gravity deployment test is completed

[0067] Figure 16 Flowchart of the usage method of an attitude adjustment and parking device for zero-gravity deployment test

[0068] Reference numerals:

[0069] 1. Simulation wall assembly; 11. Simulation wall body; 12. Connecting shaft; 2. Bracket assembly; 21. Cross beam; 22. First vertical beam; 23. Second vertical beam; 24. Longitudinal beam; 25. Screw jack; 26. Brake caster; 3. Pitch adjustment assembly; 31. Pressing knurled adjustment screw; 32. Pitch mounting plate; 33. Extrusion block; 34. Connecting rod; 35. Pitch adjustment block; 36. Pitch knurled adjustment screw; 37. Mounting tightening column; 4. Rolling adjustment assembly; 41. Vertical beam mounting block; 42. Adjusting lifting ring; 43. Lifting block; 44. Pressing connecting rod; 45. Connecting shaft pin; 46. Lifting pressing plate; 47. Connecting screw; 48. Set screw; 5. Considerate plate; 6. Deployment plate; 7. Inter-plate deployment mechanism; 8. Gravity unloading sling Detailed implementation manners

[0070] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to 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.

[0071] Embodiment 1

[0072] An attitude adjustment and parking device and method for zero-gravity deployment test

[0073] As Figure 1As shown in the figure, the attitude adjustment and parking device schematic diagram includes a simulated wall assembly 1, a bracket assembly 2, a pitch adjustment assembly 3, and a rolling adjustment assembly 4. The simulated wall assembly 1 is installed on the rolling adjustment assembly 4, and the pitch adjustment assembly 3 and the roll adjustment assembly 4 are installed on the bracket assembly 2. The specified coordinate system is located at the geometric center of the simulated wall assembly 1, and the three coordinate axes are as shown in the figure. The simulated wall assembly 1 rotates around the X-axis in the pitch direction, around the Y-axis in the yaw direction, and around the Z-axis in the rolling direction.

[0074] As Figure 2 shown, the simulated wall assembly 1 mainly includes two parts: a simulated wall 11 and two connecting shafts 12. The two connecting shafts 12 are located on both sides of the simulated wall 11 in the X direction and are installed and connected by screws. Four bosses and hoisting point mounting holes are left at the four corners of the simulated wall 11 for hoisting use. Openings can be made in the plane of the simulated wall 11 according to the mechanical interfaces of the installed solar panel or antenna.

[0075] Figure 3 and Figure 4 is a schematic diagram of the bracket assembly 2. It mainly includes two cross beams 21, two first vertical beams 22, two second vertical beams 23, two longitudinal beams 24, four screw jacks 25, and four brake casters 26. The cross beams 21, the first vertical beams 22, the second vertical beams 23, and the longitudinal beams 24 are all welded by Q235 steel pipes with square cross-sections and steel plates with thicknesses of 4 mm and 8 mm. External interfaces are left on the thick steel plates for assembly. The screw jacks 25 and the brake casters 26 are installed on the cross beams 21. The two ends of the longitudinal beams 24 are connected to the cross beams 21 by screws; the first vertical beams 22 and the second vertical beams 23 are connected by screws, and the first vertical beams 22 are connected to the cross beams 21 by screws. The four brake casters 26 can adjust the bracket assembly 2 in the yaw direction around the Y-axis. After the adjustment is in place, the four screw jacks 25 are used for ground support and fixation. The bracket assembly is of a detachable type. In the disassembled state, the storage space occupied is small and the transportation is relatively convenient; the bracket assembly is convenient for expansion according to the size of the test equipment. If the size of the later deployed solar wing / deployable antenna is too large and exceeds the size of the current simulated wall assembly 1, only the second vertical beams 23 and the longitudinal beams 24 with longer sizes need to be replaced.

[0076] Figure 5As shown in the figure; the pitch adjustment component 3 mainly consists of a pressing knurled adjustment screw 31, a pitch mounting plate 32, a pressing block 33, a connecting rod 34, a pitch adjustment block 35, a pitch knurled adjustment screw 36, and a pressing column 37. The pressing knurled adjustment screw 31 consists of a screw rod and an operating head with knurling and an internal hexagon feature. The screw rod is used for threaded cooperation with the pitch mounting plate 32. The knurling is used to quickly adjust the cooperation depth until the end of the screw rod abuts against the pressing block 33. The internal hexagon feature can apply a moment through a tool to tighten the pressing block 33. The two ends of the 4 connecting rods 34 are threaded holes, and the pitch mounting plate 32 and the pitch adjustment block 35 are connected into a whole by screws. The notches at both ends of the pressing block 33 can just be inserted into the 4 connecting rods 34. The pitch knurled adjustment screw 36 consists of a screw rod and an operating head with knurling and an internal hexagon feature. The screw rod is in threaded cooperation with the threaded hole of the pitch adjustment block 35, and the pressing column 37 is installed at the top end of the screw rod.

[0077] Figure 6 As shown in the figure of the pitch adjustment component 3 installed on the second vertical beam 23, the 4 connecting rods 34 connect the pitch mounting plate 32 and the pitch adjustment block 35 into a whole and sleeved on the second vertical beam 23, and the pressing block 33 is inserted into the 4 connecting rods 34. When the adjustment component 3 is loose, it can move up and down along the second vertical beam 23. When adjusted to the appropriate position, manually adjust the pressing knurled adjustment screw 31 to make the end of the screw rod of the pressing knurled adjustment screw 31 abut against the pressing block 33, and apply a moment through a tool to tighten the pressing block 33. The pressing block 33 and the pitch adjustment block 35 jointly press the second vertical beam 23 to play a role in fixing the position.

[0078] Figure 7 As shown in the figure of the pitch adjustment of the simulation wall component 1 by the pitch adjustment component 3. After the 2 pitch knurled adjustment screws 36 are screwed into the pitch adjustment block 35, the pressing columns 37 are installed. The 2 pressing columns 37 cooperate to limit the simulation wall 11 of the simulation wall component 1 around the connecting shaft 12 at a fixed angle. When the pitch adjustment of the simulation wall component 1 is required, adjust the screwing depth of the 2 pitch knurled adjustment screws 36, so as to adjust the rotation angle of the simulation wall component 1 around the connecting shaft 12.

[0079] Figure 8It consists of a rolling adjustment component 4, which is mainly composed of a vertical beam mounting block 41, an adjustment lifting ring 42, a lifting block 43, a pressing connecting rod 44, a connecting axle pin 45, a lifting pressing plate 46, a connecting screw 47, and a set screw 48. The lower end of the vertical beam mounting block 41 is square and can be embedded into the interior of the second vertical beam 23, with a butt joint boss on the upper end. There are two threaded holes at the lower end of the vertical beam mounting block 41 for installing the set screw 48, and the center of the vertical beam mounting block 41 is a circular through-hole; the lower end of the adjustment lifting ring 42 is a cylinder with an annular notch at the lower part of the cylinder, and the upper end is a polygonal flange with a circular hole on the flange edge. The center of the adjustment lifting ring 42 is an internal threaded through-hole. The adjustment lifting ring 42 is fitted with the central hole of the vertical beam mounting block 41 through the cylinder at the lower end. By operating the circular hole on the polygonal flange at the upper end of the adjustment lifting ring 42 with a tool, it can be rotated relatively. The set screw 48 passes through the vertical beam mounting block 41 and gets stuck in the annular notch of the cylinder at the lower end of the adjustment lifting ring 42, preventing it from coming out. When the set screw 48 is tightened, the adjustment lifting ring 42 can be fastened; the lower end of the lifting block 43 is an external threaded rod, and the upper end has a V-shaped groove boss. The lifting block 43 is screwed to the adjustment lifting ring 42 through the screw at the lower end, and is fitted with the connecting axle 12 of the simulation wall component 1 through the V-shaped groove at the upper end. The connecting axle 12 is pressed on the lifting block 43 through the cooperation of the pressing connecting rod 44, the connecting axle pin 45, and the lifting pressing plate 46.

[0080] Figure 9 , Figure 10 It is a schematic diagram of the pitching adjustment of the simulation wall component 1 by the rolling adjustment component 4. The lower end of the vertical beam mounting block 41 is embedded into the interior of the second vertical beam 23, and the adjustment lifting ring 42 is installed in the central hole of the vertical beam mounting block 41 through the cylinder at the lower end. Two set screws 48 are installed on the vertical beam mounting block 41 and embedded into the annular notch of the cylinder at the lower end of the adjustment lifting ring 42 for positioning. The lifting block 43 is screwed to the adjustment lifting ring 42 through the screw at the lower end. By changing the length of the thread fit, the height of the lifting block 43 can be changed. The connecting axle 12 is pressed on the lifting block 43 through the cooperation of the pressing connecting rod 44, the connecting axle pin 45, and the lifting pressing plate 46. There are 2 groups of rolling adjustment components 4 pressing on the 2 connecting axles 12 of the simulation wall component 1.

[0081] Figure 11 and Figure 12a , 12b, 12c briefly introduces the deployment test process of the solar wing panel. First, install the solar wing panel on the simulation wall assembly 1 of the attitude adjustment and parking device. The solar wing panel includes a considerate board 5, a deployment board 6, and two in-board deployment mechanisms 7. The considerate board 5 is installed on the simulation wall 11, and the deployment board 6 is suspended by a gravity unloading sling 8. The initial state is the state where the deployment board 6 is retracted and pressed. By adjusting the pitch adjustment component 3 and the roll adjustment component 4 of the attitude adjustment and parking device multiple times until the rotation axes of the two in-board deployment mechanisms 7 are perpendicular to the horizontal plane (the plane perpendicular to the direction of the gravity vector), and then adjust the gravity unloading sling 8 to unload the gravity of the deployment board 6. Figure 12a , 12b , 12c is a schematic diagram of the deployment process of the deployment board 6 of the solar wing. They are the states at the beginning of deployment, during deployment, and after deployment respectively.

[0082] As Figure 16 shown, a usage method of an attitude adjustment and parking device for zero-gravity deployment test is as follows: First, install a test product such as a deployable solar wing / deployable antenna on the simulation wall assembly 1 of the attitude adjustment and parking device. The initial state is the retracted and pressed state. By adjusting the pitch adjustment component 3 and the roll adjustment component 4 of the attitude adjustment and parking device multiple times until the rotation axis of the test product is perpendicular to the horizontal plane (the plane perpendicular to the direction of the gravity vector), and then adjust the gravity unloading sling 8 to unload the gravity of the deployment board. Then perform unlocking and deployment.

[0083] Figure 13 , 14 , 15a, 15b, 15c are schematic diagrams of the zero-gravity deployment test of a phased array antenna composed of three sub-boards. Through the attitude adjustment and parking device and the suspension beam tooling, the phased array antenna can be in a zero-gravity state during the deployment process, which can better protect the deployment mechanism. The body-mounted sub-array of the phased array antenna is installed on the simulation wall of the attitude adjustment and parking device. The attitude adjustment and parking device can provide stable support and precise attitude adjustment for the phased array antenna, and adjust the rotation axis of the deployment mechanism to be as close as possible to the ideal predetermined state; each deployable sub-array is equipped with a suspension beam tooling, and the suspension beam tooling has the functions of rough adjustment and fine adjustment of the position in two-dimensional directions, and can accurately adjust the suspension force of the zero-gravity hanging system to the center of gravity position of the deployable sub-array, so that there is no disturbing torque during the deployment process of the deployment mechanism.

[0084] The above is only the preferred specific implementation manner of the present invention, 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. An attitude adjustment and parking device for zero-gravity deployment tests, characterized in that: It includes a simulated wall component (1), a bracket component (2) supported on both sides of the simulated wall component (1), and a pitch adjustment component (3) and a roll adjustment component (4) that connect both sides of the simulated wall component (1) to the bracket component (2) respectively. The bracket component (2) can drive the simulated wall component (1) to make adjustments in the yaw direction, the pitch adjustment component (3) can drive the simulated wall component (1) to make adjustments in the pitch direction, and the roll adjustment component (4) can drive the simulated wall component (1) to make adjustments in the roll direction; Fix the feeler plate of the test product to the simulated wall component (1) fixedly. The initial state of the test product is in a retracted and compressed state. By adjusting the bracket component (2), the pitch adjustment component (3) and the roll adjustment component (4) multiple times, make the rotation axis of the test product perpendicular to the horizontal plane. Then adjust the gravity unloading sling to unload the gravity of the unfolding plate of the test product, and then unlock and unfold the unfolding plate; The bracket component (2) makes the product to be tested perform yaw direction adjustment around the Y axis through four brake casters connected to the bottom. After the adjustment is in place, use a screw jack to fix it with the ground support; the components of the bracket component (2) are all detachably connected and can be expanded according to the size of the test product; The bracket component (2) includes two cross beams (21) arranged parallel to each other in the Z-axis direction, a first vertical beam (22) and a second vertical beam (23) that are successively and perpendicularly connected to the middle of the cross beam (21) and extend in the Y-axis direction; The pitch adjustment component (3) is sleeved outside the vertical beam of the bracket component (2) in the X-axis direction and is connected to both sides of the simulated wall component (1) through pitch adjustment blocks. The pitch adjustment component (3) can move up and down along the second vertical beam (23) when loose. When adjusted to the appropriate position, it is fixed by rotating and pressing the knurled adjustment screw against the vertical beam of the bracket component (2). By adjusting the screwing depth of the 2 pitch knurled adjustment screws, make the product to be tested perform pitch adjustment around the X axis; The simulated wall component (1) includes a simulated wall body (11) and a connecting shaft (12). The number of the connecting shafts (12) is two, which are respectively connected to the left and right sides of the simulated wall body (11); The simulated wall body (11) is a plate-like structure, with screw mounting holes provided on the left and right side surfaces. The simulated wall body (11) can be drilled according to the mechanical interface of the product to be tested. Both sides of the simulated wall body (11) are connected to the pitch adjustment component (3); The connecting shaft (12) is T-shaped, one side is connected to the side part of the simulated wall body (11) by screws, and the other side extends into the roll adjustment component (4); The pitching adjustment assembly (3) includes a pressing knurled adjustment screw (31), a pitching mounting plate (32) passing through the pressing knurled adjustment screw (31), a pressing block (33) tightly abutted against the end of the pressing knurled adjustment screw (31), a connecting rod (34) passing through the pressing block (33) and connected to both ends of the pitching mounting plate (32), a pitching adjustment block (35) connected to the other end of the connecting rod (34), a pitching knurled adjustment screw (36) connected to the other end of the pitching adjustment block (35), and a pressing column (37) connected to the end of the pitching knurled adjustment screw (36). After the two pitching knurled adjustment screws (36) are screwed into the pitching adjustment block (35) from the front end and the rear end respectively, the pressing column (37) is installed. The two pressing columns (37) cooperate to limit the simulation wall body (11) around the connecting shaft (12) at a fixed angle; when the pitching adjustment of the simulation wall assembly (1) is required, the screwing depths of the two pitching knurled adjustment screws (36) are adjusted, so that the simulation wall body (11) rotates around the connecting shaft (12).

2. The attitude adjustment and parking device for zero-gravity deployment test according to claim 1, characterized in that: The bracket assembly (2) further includes a longitudinal beam (24) connected between the two cross beams (21), a screw jack (25) connected to the outside of the cross beam (21) and extending to the ground, and a brake caster (26) connected to both ends of the cross beam (21). The second vertical beam (23) is connected to the top of the first vertical beam (22) and is coaxial with the first vertical beam (22). The simulation wall assembly (1) is arranged between the two first vertical beams (22) and the second vertical beam (23). The pitching adjustment assembly (3) is movably connected to the first vertical beam (22) or the second vertical beam (23). The connecting shaft (12) and the rolling adjustment assembly (4) are both connected to the top of the second vertical beam (23). The number of the cross beam (21), the first vertical beam (22), and the second vertical beam (23) is 2 each. The number of the screw jack (25) and the brake caster (26) is 4. The brake caster (26) can drive the simulation wall body (11) to move or brake separately. The cross beam (21) and the first vertical beam (22), the first vertical beam (22) and the second vertical beam (23), and the longitudinal beam (24) and the cross beam (21) are all detachably connected by screws. The yaw direction adjustment around the Y axis is performed by the 4 brake casters (26). After the adjustment is in place, the screw jack (25) is used to support and fix to the ground. Four bosses are left at the four corners of the simulation wall body (11), and lifting point mounting holes for hoisting the attitude adjustment and parking device are connected to the bosses. One side of the connecting shaft (12) is fixed to the simulation wall body (11) by four screws, two in a group.

3. The attitude adjustment and parking device for zero-gravity deployment test according to claim 2, characterized in that: The cross beam (21), the first vertical beam (22), the second vertical beam (23), and the longitudinal beam (24) are all hollow steel pipes with assembly interfaces left. The number of the longitudinal beams (24) is two and they are symmetrically distributed. The heights of the first vertical beam (22) and the second vertical beam (23) can be selected according to the size of the test product.

4. The attitude adjustment and parking device for zero-gravity deployment test according to claim 2, wherein: The connecting rod (34) connects the pitching mounting plate (32) and the pitching adjustment block (35) into a whole and slews them onto the second vertical beam (23). The extrusion block (33) is embedded in the connecting rod (34). The pitching knurled adjustment screw (36) and the jacking column (37) fixedly connect the simulation wall body (11). The pressing knurled adjustment screw (31) includes a screw rod and an operating head with knurling and internal hexagon features. The pitching mounting plate (32) is a plate-like structure that is threadedly connected to the screw rod of the pressing knurled adjustment screw (31) in the middle and threadedly connected to the connecting rod (34) at both ends. The screw rod of the pressing knurled adjustment screw (31) is in threaded fit with the pitching mounting plate (32). The knurling of the operating head adjusts the fitting depth until the end of the screw rod abuts against the extrusion block (33). A torque can be applied to the internal hexagon feature of the operating head through a tool to tighten the extrusion block (33). The extrusion block (33) is a plate-like structure with notches at both ends to avoid the connecting rod (34). The extrusion block (33) is placed on the outer wall of the second vertical beam (23). Threaded holes are provided at both ends of the connecting rod (34), and the pitching mounting plate (32) and the pitching adjustment block (35) are connected into a whole by screws. The notches at both ends of the extrusion block (33) enable the connecting rod (34) to be vertically embedded and wrap the second vertical beam (23) inside. The pitching adjustment block (35) includes a horizontal plate threadedly connected to the connecting rod (34) and extension plates vertically connected to both ends of the horizontal plate and extending towards the simulation wall body (11). The direction of the horizontal plate of the pitching adjustment block (35) is the same as that of the pitching mounting plate (32) and the extrusion block (33). Threaded mounting holes are provided at the ends of the extension plates of the pitching adjustment block (35). The pitching knurled adjustment screw (36) includes a screw rod and an operating head with knurling and internal hexagon features. The screw rod of the pitching knurled adjustment screw (36) is in threaded fit with the threaded hole of the extension plate of the pitching adjustment block (35), and the top end of the screw rod is threadedly connected to the jacking column (37). The jacking column (37) tightly fixes the simulation wall body (11). When the adjustment assembly (a) is loose, it can move up and down along the second vertical beam (23). When adjusted to the appropriate position, manually adjust the pressing knurled adjustment screw (31) to make the screw rod end of the pressing knurled adjustment screw (31) abut against the extrusion block (33), and apply a torque through a tool to tighten the extrusion block (33). The extrusion block (33) and the pitching adjustment block (35) jointly clamp and fix the second vertical beam (23).

5. The attitude adjustment and parking device for zero-gravity deployment test according to claim 4, characterized in that: The number of the connecting rods (34) is four, with two as a group. The number of the pitching knurled adjusting screws (36) and the pressing columns (37) is two each. The four connecting rods (34) connect the pitching mounting plate (32) and the pitching adjusting block (35) into a whole and sleeved on the second vertical beam (23), and the extrusion block (33) is embedded in the four connecting rods (34).

6. The attitude adjustment and parking device for zero-gravity deployment test according to claim 4, wherein: The lower end of the rolling adjustment assembly (4) is embedded inside the second vertical beam (23). The horizontal shaft of the connecting shaft (12) is tightly fixed on the lifting block of the rolling adjustment assembly (4). By changing the height of the lifting block of the rolling adjustment assembly (4), the connecting shaft (12) is adjusted in the rolling direction and drives the simulation wall body (11) to adjust in the rolling direction around the Z axis.

7. The attitude adjustment and parking device for zero-gravity deployment test according to claim 6, characterized in that: The rolling adjustment assembly (4) includes a vertical beam mounting block (41) with its lower end embedded inside the second vertical beam (23), an adjustment lifting ring (42) whose lower end cylinder is matched with the central hole of the vertical beam mounting block (41), a lifting block (43) whose lower end is screwed to the adjustment lifting ring (42), a pressing connecting rod (44) connected to one side of the top of the lifting block (43), a connecting shaft pin (45) connecting the top of the pressing connecting rod (44) and one side of the lifting block (43), a lifting pressing plate (46) movably connected to the connecting shaft pin (45), a connecting screw rod (47) passing through the lifting block (43) and detachably connected to the other end of the lifting pressing plate (46), and a set screw (48) passing through the second vertical beam (23) and the vertical beam mounting block (41) in sequence and propping against the side wall of the adjustment lifting ring (42); The lower end of the vertical beam mounting block (41) is a square structure smaller than the inner length and width of the second vertical beam (23), the upper part is a docking boss larger than the outer length and width of the second vertical beam (23), a threaded mounting hole for installing the set screw (48) is arranged on the side surface along the Y axis direction, and a circular through hole for inserting the adjustment lifting ring (42) is arranged in the center; The lower end of the adjustment lifting ring (42) is a cylinder and a circumferential notch is connected to the lower part of the cylinder horizontally. The upper end is a polygonal flange structure with a circular hole connected to the side surface. The center of the adjustment lifting ring (42) is an internal threaded through hole threadedly connected to the lower end of the lifting block (43); The lower end of the lifting block (43) is an external threaded rod, and the upper end is a boss with a V-shaped groove. The horizontal shaft of the connecting shaft (12) extends into the V-shaped groove; The lifting pressing plate (46) opens and closes with the connecting shaft pin (45) as the axis. The bottom of the lifting pressing plate (46) is connected with an arc-shaped notch in the same extending direction as the connecting shaft (12). The connecting shaft (12) is placed in the V-shaped groove of the lifting block (43), and the connecting screw rod (47) presses the connecting shaft (12) between the lifting pressing plate (46) and the lifting block (43); The cylinder at the lower end of the adjusting lifting ring (42) is installed in the central hole of the vertical beam mounting block (41). The two set screws (48) sequentially pass through the side wall of the second vertical beam (23) and the side wall of the vertical beam mounting block (41) and are embedded in the annular notch at the lower end of the adjusting lifting ring (42) for limiting. The lifting block (43) is screwed to the adjusting lifting ring (42) through the lower end screw rod, and the height of the lifting block (43) can be changed by changing the length of the thread fit. The number of the adjusting assemblies 4 is two groups, and the two connecting shafts (12) are respectively pressed.

8. The attitude adjustment and parking device for zero-gravity deployment test according to claim 1, characterized in that: In step S2, the test product is a solar wing sailboard or a phased array antenna including three sub-arrays. When the test product is a phased array antenna, the initial state of the phased array antenna is that the left and right phased array antenna sub-arrays are folded and pressed on the middle phased array antenna sub-array on the same side in a high-low manner. The middle phased array antenna sub-array is connected to the simulation wall body (11). The number of the gravity unloading slings (8) is two, and the left and right phased array antenna sub-arrays are respectively suspended. In step S5, the left and right phased array antenna sub-arrays are deployed in sequence. First, the outermost phased array antenna sub-array is deployed, and then the other phased array antenna sub-array is deployed until the three phased array antenna sub-arrays are coplanar.

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