A gravity unloading hanging beam tooling for satellite deployable structure

Abstract

The present invention provides a gravity unloading hanging beam fixture for a satellite deployable structure, including a hanging beam bracket, a connecting stud assembly, a suspension assembly, a longitudinal adjustment assembly and a lateral adjustment assembly. One side of the present invention is connected to the hanging point holes left on the deployable solar wing / deployable antenna substrate structure through multiple connecting studs, and the other side is connected to the zero gravity hanging system through the hanging ring led out of the fixture; the hanging beam fixture has the function of coarse adjustment and fine adjustment of the position in the two-dimensional direction, and can accurately adjust the hanging force of the zero gravity hanging system to the center of gravity position of the deployable solar wing / deployable antenna, so that there is no disturbance torque during the deployment process of the deployment mechanism; the hanging beam fixture is installed with a self-aligning bearing, which releases the rotational freedom of the hanging system and the deployable solar wing / deployable antenna substrate during the deployment process of the deployment mechanism, thereby improving the smoothness of the deployment; the hanging beam fixture has the advantages of simple structure, few types of parts, and convenient assembly and position adjustment.

Description

Technical Field

[0001] The invention relates to the field of measurement and testing technology, and in particular to a gravity unloading hanging beam tooling of a satellite deployable structure. Background Art

[0002] The deployable solar wing / deployable antenna on the satellite is connected to the satellite through the deployment mechanism. During the satellite AIT stage (assembly, testing, and experimentation), the deployment mechanism needs to be tested multiple times to verify the deployment accuracy and mechanical environment adaptability of the deployment mechanism. Generally, the base structure of the deployable solar wing / deployable antenna adopts a flat plate structure, that is, it has 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 of the base structure.

[0003] Since there is no influence of gravity in space, gravity factors are not considered when designing the driving force of the deployment mechanism. Under the condition that the driving static moment margin is greater than 1, the driving force should not be too large to reduce the impact when it is deployed.

[0004] However, there is the influence of gravity on the ground. When the mass of the unfolded solar wing / deployable antenna installed at the rotating end of the unfolding mechanism is small, gravity can be ignored and the unfolding mechanism unfolds directly; when the mass of the unfolded solar wing / deployable antenna installed at the rotating end of the unfolding mechanism is large, the influence of gravity cannot be ignored. Gravity will produce a torque on the rotating shaft of the unfolding mechanism. In this state, it will cause the unfolding to fail or will affect or even damage the accuracy and smoothness of the unfolding mechanism. It is necessary to gravity unload the unfoldable solar wing / deployable antenna to simulate the weightlessness in space as much as possible. The usual practice is to make the unfolding mechanism rotating shaft of the unfoldable solar wing / deployable antenna perpendicular to the ground, and the center of gravity position of the unfoldable solar wing / deployable antenna will not change from the rotating shaft of the unfolding mechanism. At the same time, the upper part of the unfoldable solar wing / deployable antenna unloads gravity through the suspension system (the suspension force is equal to gravity). In this way, the unfoldable solar wing / deployable antenna is in a zero gravity state during the entire unfolding process, which can better protect the unfolding mechanism.

[0005] In order to unload the gravity of the deployable solar wing / deployable antenna, the suspension system needs to pass the center of mass of the equipment. The greater the deviation, the greater the additional torque generated, and the greater the damage to the deployment mechanism. When designing the structure of the deployable solar wing / deployable antenna substrate, multiple suspension point interfaces will be reserved. The suspension point interfaces are generally geometrically symmetrical to facilitate the subsequent lifting and maintain a stable state. Multiple suspension point interfaces will be transferred to the suspension system through the hanging beam tooling. However, since various accessories, cables, glue, etc. will be installed on the front and back of the substrate structure of the actual finished product, the center of mass position of the finished product will deviate from the design state. Therefore, the hanging beam tooling needs to have a position adjustable function. According to the actual center of mass position of the deployable solar wing / deployable antenna, the suspension force of the suspension system is adjusted to pass through the center of mass. Summary of the invention

[0006] The present invention is to solve the problem of adjusting the center of gravity of a hanging beam fixture and provides a gravity unloading hanging beam fixture for a satellite deployable structure, one side of which is connected to the hanging point holes left on the deployable solar wing / deployable antenna substrate structure through a plurality of connecting studs, and the other side is connected to the zero-gravity hanging system through a hanging ring led out of the fixture; the hanging beam fixture has the functions of coarse 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 solar wing / deployable antenna, so that there is no disturbance torque during the deployment process of the deployment mechanism; a self-aligning bearing is installed on the hanging beam fixture, which releases the rotational freedom of the hanging system and the deployable solar wing / deployable antenna substrate during the deployment process of the deployment mechanism, thereby improving the smoothness of the deployment; the hanging beam fixture has the advantages of simple structure, few types of parts, and convenient assembly and position adjustment.

[0007] The present invention provides a gravity unloading hanging beam tooling for a satellite deployable structure, comprising a hanging beam bracket, a connecting stud assembly connecting the hanging beam bracket with a satellite to-be-deployed mechanism, a suspension assembly connecting the hanging beam bracket with a zero-gravity hanging system, a longitudinal adjustment assembly for longitudinally adjusting the satellite to-be-deployed mechanism, and a transverse adjustment assembly for transversely adjusting the satellite to-be-deployed mechanism;

[0008] One end of the connecting stud assembly is connected to the hanging beam bracket, and the other end is connected to the top of the satellite to-be-deployed mechanism; the bottom of the suspension assembly passes through the hanging beam bracket and is located inside the lateral adjustment assembly, the longitudinal adjustment assembly is located on the longitudinal side of the suspension assembly and the lateral adjustment assembly, and the lateral adjustment block of the lateral adjustment assembly is connected to the outside of the hanging beam bracket, one side of which is threadedly connected to the longitudinal adjustment assembly, and the other side is in contact with the suspension assembly;

[0009] The longitudinal position of the lateral adjustment assembly on the suspension beam bracket is adjusted by changing the longitudinal relative position of the fine-tuning screw of the longitudinal adjustment assembly and the longitudinal position of the center of mass of the satellite to be deployed is adjusted. The lateral position of the suspension assembly is adjusted by adjusting the relative position of the fine-tuning screw of the lateral adjustment assembly to adjust the lateral position of the center of mass of the satellite to be deployed.

[0010] The gravity unloading hanging beam tooling of a satellite deployable structure described in the present invention, as a preferred embodiment, the hanging beam bracket includes a hanging beam bracket body, a long slot hole connected to the middle of the hanging beam bracket body, and circular through holes connected to the hanging beam bracket body and located on both sides of the long slot hole, the hanging beam bracket body is a long strip structure with a U-shaped cross-section, and the number of the circular through holes is the same as the number of the studs and washers and is at least 2;

[0011] The connecting stud assembly comprises a stud and a washer embedded in a circular through hole, the middle part of the stud is an outer hexagonal body, and both the upper and lower sides are screw rods with threads;

[0012] The screw rod at the lower side of the stud is threadedly connected to the hanging point hole of the satellite to-be-deployed mechanism, and the screw rod at the upper side of the stud is fixedly connected to the nut after passing through the washer.

[0013] The gravity unloading hanging beam fixture of a satellite deployable structure described in the present invention, as a preferred embodiment, the hanging assembly includes a hanging point, a hanging point connecting block, a self-aligning bearing arranged in sequence, a hanging rod passing through the self-aligning bearing, the hanging point connecting block and the hanging point, and a pressing plate passing through the bottom of the hanging rod and connected to the bottom of the hanging beam bracket body;

[0014] The upper end of the suspension point is connected to the zero gravity suspension system, and the lower end is threadedly connected to the suspension rod. The suspension point connection block, the suspension beam bracket body and the clamping plate are connected in sequence by screws. The self-aligning bearing is embedded in the suspension point connection block and is interference fit. The self-aligning bearing can make the suspension rod and the suspension point connection block rotate;

[0015] One lateral side of the suspension point connection block is connected to the side of the lateral adjustment component through a lateral fine-tuning screw. The bottom of the suspension point connection block is embedded in the lateral adjustment component and can only move laterally in the lateral adjustment component. The lateral position of the suspension point connection block and the self-aligning bearing is adjusted by adjusting the relative position of the lateral fine-tuning screw, and the suspension rod and the suspension point connection block are rotated to adjust the lateral position of the center of mass of the satellite to be deployed mechanism.

[0016] The gravity unloading hanging beam tooling of a satellite deployable structure described in the present invention is preferably such that the upper end of the hanging point is a hanging ear with a hole, a screw rod for connecting with a zero gravity hanging system is installed in the hole of the hanging ear, and a nut connected with the screw rod is installed outside;

[0017] The lifting point connection block comprises a lifting point connection block body, a screw mounting plate vertically connected to one lateral side of the lifting point connection block body and extending upward, a self-aligning bearing mounting body connected to the upper surface of the lifting point connection block body, a fixing hole connected to the lifting point connection block body, a screw hole connected to the screw mounting plate and a self-aligning bearing mounting hole connected to the self-aligning bearing mounting body, and the lifting point connection block body is located in the lateral adjustment assembly and can only be moved lateraly in the lateral adjustment assembly;

[0018] The main body of the suspension point connection block is a plate-like structure, the screw mounting plate is a block-like structure connected to one side of the self-aligning bearing mounting body, the self-aligning bearing mounting body is a hollow cylinder including an upper surface, and the bottom is connected to the main body of the suspension point connection block, the fixing holes are located on both sides of the self-aligning bearing mounting hole, the screw holes are symmetrically arranged, the screw mounting plate is connected to the side of the lateral adjustment component through the fine adjustment screw of the lateral adjustment component, the self-aligning bearing mounting hole is a through hole, and the suspension rod passes through the self-aligning bearing mounting hole, the self-aligning bearing mounting body, and the main body of the suspension point connection block and extends downward;

[0019] By tightening or loosening the fine-adjusting screw of the lateral adjustment assembly, the position of the suspension point connection block body in the lateral adjustment assembly is adjusted, and the self-aligning bearing drives the suspension rod and the suspension point to produce lateral displacement, thereby adjusting the lateral position of the center of mass of the satellite to be deployed mechanism.

[0020] The gravity unloading hanging beam tooling of a satellite deployable structure described in the present invention, as a preferred embodiment, the longitudinal adjustment assembly includes a longitudinal adjustment frame, a longitudinal fine-adjustment screw passing through a longitudinal side of the top of the longitudinal adjustment frame, and a longitudinal retaining ring connected to the front end of the longitudinal fine-adjustment screw, the bottom of the longitudinal adjustment frame can slide in the long slot hole and can be tightened and fixed by screws and gaskets, and a fine-adjustment screw mounting boss is provided at one end of the longitudinal adjustment frame close to the lateral adjustment assembly;

[0021] The transverse adjustment assembly includes a transverse adjustment block, which includes a hollow block body, an internal rectangular notch connected to both longitudinal sides of the block body, a longitudinal adjustment assembly mounting plate connected to the longitudinal edge of the block body and extending upward, a screw hole connected to the longitudinal adjustment assembly mounting plate, and an external rectangular notch connected to the upper surface of the block body;

[0022] The block body is inserted into the beam support body through the internal rectangular notch, the suspension point connection block body is embedded between the external rectangular notches and can only move horizontally, and the longitudinal fine adjustment screw passes through the screw hole and extends longitudinally;

[0023] The longitudinal position of the transverse adjustment block on the suspension beam bracket is adjusted by changing the longitudinal relative position of the longitudinal fine-adjustment screw rod, and the longitudinal position of the center of mass of the satellite to be deployed mechanism is adjusted.

[0024] The gravity unloading hanging beam fixture of the satellite deployable structure described in the present invention, as a preferred embodiment, the longitudinal adjustment frame includes a T-shaped plate with a long slot hole passing through the lower part and being fixed to the hanging beam bracket body by screws, and a threaded hole boss connected to the longitudinal end of the T-shaped plate and extending upward, and the threaded hole boss is adjacent to the mounting plate between the longitudinal adjustment components;

[0025] The longitudinal fine adjustment screw comprises a longitudinal screw body, a first square boss connected to one end of the longitudinal screw body, and a first annular notch connected to the other end of the longitudinal screw body. The longitudinal screw body is a cylinder connected with fine threads. The longitudinal screw body is used for fine position adjustment and anti-loosening. The longitudinal retaining rings are respectively installed in the first annular notch for limiting. The number of the first annular notch and the number of the longitudinal retaining rings are both two.

[0026] The longitudinal fine adjustment screw is screwed into the threaded hole boss through threaded matching, and the end thereof extends into the mounting plate between the longitudinal adjustment components and is fixed by two longitudinal retaining rings at both ends;

[0027] Fix the T-shaped plate on the hanging beam bracket body, use a tool to rotate the first square boss to adjust the relative position of the T-shaped plate and the transverse adjustment block, thereby changing the longitudinal position of the transverse adjustment block on the hanging beam bracket and adjusting the longitudinal position of the suspension point.

[0028] The gravity unloading hanging beam fixture of the satellite deployable structure described in the present invention, as a preferred embodiment, the lateral adjustment assembly also includes a set screw, a lateral adjustment frame screwed to the lateral side of the lateral adjustment block, a lateral fine adjustment screw threadedly connected to the lateral adjustment frame, and a lateral retaining ring connected to the end of the lateral fine adjustment screw;

[0029] The lateral adjustment block also includes threaded through holes connected to the lateral side of the block body, and the number of the screw holes is 4;

[0030] The transverse adjustment frame includes a first transverse adjustment plate, a second transverse adjustment plate and a third transverse adjustment plate which are vertically connected in sequence. The first transverse adjustment plate, the second transverse adjustment plate and the third transverse adjustment plate are all plate-shaped structures. The third transverse adjustment plate is parallel to the first transverse adjustment plate and is located at the upper part of the first transverse adjustment plate. The first transverse adjustment plate is connected to the vertical surface of the block body through screws and two screw holes in the middle. The set screws are fixed to the block body on the hanging beam bracket body through two screw holes at both ends.

[0031] The lateral movement range of the hanging point connection block within the external rectangular notch is ±10mm.

[0032] The gravity unloading beam fixture of the satellite deployable structure described in the present invention, as a preferred embodiment, the transverse fine adjustment screw comprises a transverse screw body, a second square boss connected to one end of the transverse screw body and a second annular notch connected to the other end of the transverse screw body, and the transverse screw body is a cylinder connected with fine threads;

[0033] The transverse screw body is used for fine position adjustment and anti-loosening. The transverse retaining rings are installed in the first annular notch for limiting. The number of the second annular notch and the transverse retaining rings are two. The transverse screw body is screwed into the third transverse adjustment plate through threaded cooperation, and the end extends into the screw mounting plate of the hanging point connection block and is fixed by two transverse retaining rings at both ends.

[0034] The method for using the gravity unloading hanging beam tooling of the satellite deployable structure described in the present invention, as a preferred embodiment, comprises the following steps:

[0035] S1. The actual center of mass position of the satellite to be deployed mechanism is first obtained through mass measurement, and one end of the stud connecting the stud assembly is screwed into the hanging point hole reserved on the base plate structure of the satellite to be deployed mechanism, and torque is applied to prevent loosening. The other end is passed through the washer in the hole of the hanging beam bracket and fixed with a nut to fasten the hanging beam bracket and the satellite to be deployed mechanism together;

[0036] S2, assembling the suspension assembly, the longitudinal adjustment assembly, and the transverse adjustment assembly on the hanging beam bracket, with all the set screws in an untightened state, adjusting the transverse adjustment block of the transverse adjustment assembly on the hanging beam bracket so that the transverse adjustment block is roughly adjusted to above the center of mass position of the satellite to be deployed mechanism, and then tightening and fixing the longitudinal adjustment frame of the longitudinal adjustment assembly on the hanging beam bracket with screws and gaskets, and the rough adjustment is completed;

[0037] S3, enter longitudinal fine adjustment: change the longitudinal fine adjustment screw of the longitudinal adjustment assembly relative position on the longitudinal adjustment frame to adjust the longitudinal position of the transverse adjustment block on the suspension beam bracket, the suspension assembly also changes with the change of the transverse adjustment block position, after accurately adjusting to the longitudinal position of the satellite deployment mechanism center of mass, screw in two set screws on the transverse adjustment block to fix the transverse adjustment block on the suspension beam bracket, and the longitudinal fine adjustment is completed;

[0038] S4, enter the lateral fine-tuning stage: adjust the positions of the two lateral fine-tuning screws on the lateral adjustment frame of the lateral adjustment assembly, and accurately adjust the position of the suspension point connection block on the lateral adjustment block laterally. When the center of mass of the satellite to be deployed is adjusted to the lateral position, the suspension point connection block of the suspension assembly is screwed to the clamping plate at the lower end by two screws and the suspension beam bracket is tightened to fix the suspension point connection block on the suspension beam bracket. The lateral fine-tuning is completed, and a method for using a gravity unloading suspension beam tooling for a satellite deployable structure is completed.

[0039] The method for using the gravity unloading hanging beam tooling of a satellite deployable structure of the present invention comprises: in step S1, the satellite to-be-deployed structure is a deployable solar wing or a deployable antenna product; the number of studs is 4;

[0040] In step S3, the number of longitudinal fine-adjusting screws is 2;

[0041] In step S4, the number of transverse fine-adjusting screws is 2.

[0042] The present invention has the following advantages:

[0043] One side of the present invention is connected to the hanging point holes left on the deployable solar wing / deployable antenna substrate structure through multiple connecting studs, and the other side is connected to the zero-gravity suspension system through a lifting ring led out of the tooling; it has the functions of coarse and fine adjustment of the two-dimensional position, and can accurately adjust the suspension force of the zero-gravity suspension system to the center of gravity position of the deployable solar wing / deployable antenna, so that there is no disturbance torque during the deployment of the deployment mechanism; the present invention is equipped with a self-aligning bearing, which releases the rotational freedom of the suspension system and the deployable solar wing / deployable antenna substrate during the deployment process of the deployment mechanism, thereby improving the smoothness of the deployment; the present invention has the advantages of simple structure, few types of parts, and convenient assembly and position adjustment. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 A schematic diagram of a connection state between a lifting beam fixture and a flat plate structure of a gravity unloading lifting beam fixture of a satellite deployable structure;

[0045] Figure 2 It is a structural schematic diagram of a gravity unloading hanging beam tooling of a satellite deployable structure;

[0046] Figure 3 It is an exploded schematic diagram of a gravity unloading hanging beam tooling of a satellite deployable structure;

[0047] Figure 4 A schematic cross-sectional view of a suspension assembly of a gravity unloading beam fixture for a satellite deployable structure;

[0048] Figure 5 A schematic diagram of the connection structure of the lifting points of a gravity unloading lifting beam tooling for a satellite deployable structure;

[0049] Figure 6 A cross-sectional view of a lifting point connection block of a gravity unloading lifting beam tooling of a satellite deployable structure;

[0050] Figure 7 A schematic diagram of a longitudinal fine-adjusting screw structure of a gravity unloading hanging beam tooling of a satellite deployable structure;

[0051] Figure 8 A schematic diagram of the use of a longitudinal adjustment component 4 of a gravity unloading hanging beam tooling of a satellite deployable structure;

[0052] Fig. 9 It is a schematic diagram of the structure of a lateral adjustment block of a gravity unloading hanging beam tooling of a satellite deployable structure;

[0053] Fig.10 It is a schematic diagram of a transverse fine adjustment screw structure of a gravity unloading hanging beam tooling of a satellite deployable structure;

[0054] Fig.11 The present invention is a schematic diagram showing the adjustment process of the longitudinal adjustment component and the transverse adjustment component of a gravity unloading hanging beam tooling of a satellite deployable structure.

[0055] Reference numerals:

[0056] 1. Beam bracket; 11. Beam bracket body; 12. Long slot hole; 13. Round through hole; 2. Connecting stud assembly; 21. Stud; 22. Washer; 3. Suspension assembly; 31. Suspension point; 32. Suspension point connection block; 321. Suspension point connection block body; 322. Screw mounting plate; 323. Self-aligning bearing mounting body; 324. Fixing hole; 325. Screw hole; 326. Self-aligning bearing mounting hole; 33. Self-aligning bearing; 34. Suspension rod; 35. Pressing plate; 4. Longitudinal adjustment assembly; 41. Longitudinal adjustment frame; 411. T-shaped plate; 412. Threaded hole boss; 42. Longitudinal fine-adjustment screw; 421. Longitudinal screw body; 422 , first square boss; 423, first annular notch; 43, longitudinal retaining ring; 5, transverse adjustment component; 51, transverse adjustment block; 511, block body; 512, internal rectangular notch; 513, mounting plate between longitudinal adjustment components; 514, screw hole; 515, external rectangular notch; 516, threaded through hole; 52, set screw; 53, transverse adjustment frame; 531, first transverse adjustment plate; 532, second transverse adjustment plate; 533, third transverse adjustment plate; 54, transverse fine-tuning screw; 541, transverse screw body; 542, second square boss; 543, second annular notch; 55, transverse retaining ring. DETAILED DESCRIPTION

[0057] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0058] Example 1

[0059] like Figures 1 to 11 As shown, a gravity unloading hanging beam tooling of a satellite deployable structure, in this technical solution, the longitudinal direction is the long direction of the hanging beam bracket 1, that is, the left-right direction in the figure, and the transverse direction is the short direction of the hanging beam bracket 1, that is, the front-back direction in the figure;

[0060] like Figure 1 The figure shows the connection status of the hanging beam tooling and the flat-plate structure. The upper part is the hanging beam tooling, and the lower part is the flat-plate structure of the satellite to be deployed, which can be a deployable solar wing or a deployable antenna.

[0061] like Figure 2 As shown: the hanging beam tooling mainly includes 5 parts, the hanging beam bracket 1, the connecting stud assembly 2, the suspension assembly 3, the longitudinal adjustment assembly 4, the lateral adjustment assembly 5 and the corresponding standard parts.

[0062] Figure 3The figure is a schematic diagram of the exploded view of the hanging beam tooling. The connecting stud assembly 2 includes a stud 21 and a washer 22; the suspension assembly 3 mainly includes a suspension point 31, a suspension point connection block 32, a self-aligning bearing 33, a suspension rod 34, and a clamping plate 35; the longitudinal adjustment assembly 4 includes a longitudinal adjustment frame 41, a longitudinal fine-adjustment screw 42, and a longitudinal retaining ring 43; the transverse adjustment assembly 5 mainly includes a transverse adjustment block 51, a set screw 52, ​​a transverse adjustment frame 53, a transverse fine-adjustment screw 54, and a transverse retaining ring 55.

[0063] Figure 3 As shown; the beam bracket body 11 is U-shaped slot aluminum, and a plurality of circular through holes 13 are distributed on the bottom surface for connecting with the studs 21. A slot hole 12 of a certain length is left in the middle of the bottom surface for longitudinally adjusting the position of the component 4 in the slot hole 12, with an approximate adjustment range of ±110mm.

[0064] Figure 3 As shown: the middle of the stud 21 is an outer hexagonal feature for easy rotation with tools, and the two ends are M5 studs. The washer 22 is embedded in the hole of the hanging beam bracket 1, one end of the stud 21 is threaded with the hanging point hole reserved for the deployable solar wing / deployable antenna, and the other end passes through the washer 22 in the hole of the hanging beam bracket 1 and is fixed by a nut, so that the hanging beam bracket 1 and the deployable solar wing / deployable antenna are fastened together.

[0065] Figure 4 As shown, the suspension assembly 3 mainly includes a suspension point 31, a suspension point connecting block 32, a self-aligning bearing 33, a suspension rod 34, and a clamping plate 35.

[0066] Figure 5 As shown, the suspension point connection block 32 includes a suspension point connection block body 321, a screw mounting plate 322, a self-aligning bearing mounting body 323, a fixing hole 324, a screw hole 325, and a self-aligning bearing mounting hole 326. The screw hole 325 is used to install the longitudinal fine adjustment screw 42 to accurately adjust the position, the fixing hole 324 is used to fix the suspension point connection block body 321 on the suspension beam bracket 1, and the self-aligning bearing mounting hole 326 is used to install the self-aligning bearing 33.

[0067] Two screws pass through the fixing holes 324 on the suspension point connection block 32 and are screwed to the clamping plate 35 at the lower end to clamp the suspension beam bracket 1, thereby fixing the suspension point connection block 32 on the suspension beam bracket 1. One end of the suspension point 31 is a threaded hole screwed to the suspension rod 34, and the other end is a hanging ear with a hole. The hanging ear hole is equipped with a screw and a nut for connecting with the zero gravity suspension system; the self-aligning bearing 33 is embedded in the suspension point connection block 32, and the outer ring of the self-aligning bearing 33 is interference fit with the suspension point connection block 32. The outer ring end of the self-aligning bearing 33 contacts the connection block 32, and the lower end contacts the suspension rod 34, so that the suspension rod 34 can rotate with the suspension point connection block 32 in a small range.

[0068] Figures 7-8 As shown, the main body 421 of the longitudinal fine-adjustment screw 42 is circular with fine thread features, which can be used for fine position adjustment and anti-loosening effect. One end has a first square boss 422 for rotating the longitudinal fine-adjustment screw 42 using a tool, and the other end has two annular notches 423 for installing the longitudinal retaining ring 43.

[0069] like Figure 3 As shown, the transverse adjustment assembly 5 includes a transverse adjustment block 51, a set screw 52, ​​a transverse adjustment frame 53, a transverse fine-adjustment screw 54 and a transverse retaining ring 55. The transverse fine-adjustment screw 54 is the same as the longitudinal fine-adjustment screw 42, and the transverse retaining ring 55 is the same as the longitudinal retaining ring 43.

[0070] The transverse adjustment frame 53 includes a first transverse adjustment plate 531, a second transverse adjustment plate 532 and a third transverse adjustment plate 533 which are vertically connected in sequence. The first transverse adjustment plate 531, the second transverse adjustment plate 532 and the third transverse adjustment plate 533 are all plate-shaped structures. The third transverse adjustment plate 533 is parallel to the first transverse adjustment plate 531 and is located on the upper part of the first transverse adjustment plate 531. The first transverse adjustment plate 531 is connected to the vertical surface of the block body 511 through screws and two screw holes 514 in the middle. The set screw 52 fixes the block body 511 to the suspension beam bracket body 11 through two screw holes 514 at both ends.

[0071] Fig. 9 As shown, the transverse adjustment block 51 mainly has the following features: a block body 511, an internal rectangular notch 512, a mounting plate 513 between longitudinal adjustment components, a screw hole 514, an external rectangular notch 515, and a threaded through hole 516;

[0072] The screw hole 514 is used in conjunction with the longitudinal fine-adjustment screw 42; the four threaded through holes 516, the two in the middle are used to connect with the transverse adjustment frame 53 by screws, and the two at both ends are used to install the set screws 52, which plays the role of fixing the position of the transverse adjustment block 51; the internal rectangular notch 512 allows the transverse adjustment block 51 to be inserted into the hanging beam bracket 1 and slide on the hanging beam bracket 1; the external rectangular notch 515 is used to embed the hanging point connection block 32, so that the hanging point connection block 32 can only move horizontally in the rectangular notch 515, with an approximate adjustment range of ±10mm.

[0073] Fig.10 As shown, the main body 541 of the transverse screw rod is circular with fine thread features, which can be used for fine position adjustment and anti-loosening effect. There is a second square boss 542 at one end for rotating the transverse fine-tuning screw rod 54 using a tool, and there are two annular notches 543 at the other end for installing the transverse retaining ring 43.

[0074] Figure 8 ,11 This is a schematic diagram of the use of the longitudinal adjustment component 4. The lower boss 411 of the longitudinal adjustment frame 41 can slide in the grooved hole 12 on the beam bracket 1 and be tightened and fixed by screws and gaskets; the upper end of the adjustment frame 41 is provided with a threaded hole boss 412, and the longitudinal fine-tuning screw 42 is screwed into the threaded hole boss 412 on the upper end of the adjustment frame 41 through threaded cooperation, and the cooperation length can be adjusted by using a tool to rotate the first square boss 421; the two longitudinal retaining rings 43 installed on the longitudinal fine-tuning screw 42 are located on both sides of the screw hole 514, which play a double limit role for the screw hole 514. When the adjustment frame 41 is fixed to the beam bracket 1, the relative position of the longitudinal fine-tuning screw 42 on the adjustment frame 41 is changed, and the position of the lateral adjustment block 51 on the beam bracket 1 is also changed accordingly, which plays a role in fine-tuning the longitudinal position.

[0075] Fig.11 The diagram is a schematic diagram of the adjustment process of the longitudinal adjustment component 4 and the transverse adjustment component 5. The first step is to roughly adjust the suspension component 3, the longitudinal adjustment component 4, and the transverse adjustment component 5 to the approximate position on the suspension beam bracket 1; the second step is to tighten and fix the adjustment frame 41 to the suspension beam bracket 1 by screws and washers; the third step is to change the relative position of the longitudinal fine adjustment screw 42 on the adjustment frame 41 to adjust the position of the transverse adjustment block 51 on the suspension beam bracket 1, and the suspension component 3 also changes with the position change of the transverse adjustment block 51. After the adjustment is in place, two set screws 52 are screwed into the transverse adjustment block 51 to fix the transverse adjustment block 51 on the suspension beam bracket 1; the fourth step is to adjust the position of the two transverse fine adjustment screws 54 on the transverse adjustment frame 53 to accurately adjust the position of the suspension point connection block 32 on the transverse adjustment block 51 in the transverse direction. When the adjustment is in place, the suspension point connection block 32 is screwed to the clamping plate 35 at the lower end by two screws to clamp the suspension beam bracket 1, thereby fixing the suspension point connection block 32 on the suspension beam bracket 1. At this point, the longitudinal and lateral fine-tuning process is completed.

[0076] Specific implementation method:

[0077] The actual center of mass position of the deployable solar wing / deployable antenna product is first obtained through quality measurement, and one end of the four studs 21 is screwed into the reserved hanging point hole on the substrate structure, and torque is applied to prevent loosening. The other end passes through the washer 22 in the hole of the hanging beam bracket 1 and is fixed by a nut, and the hanging beam bracket 1 and the deployable solar wing / deployable antenna are fastened together. The suspension component 3, the longitudinal adjustment component 4, and the transverse adjustment component 5 are combined on the hanging beam bracket 1, and all the set screws are in an untightened state. The position of the transverse adjustment block 51 on the beam bracket 1 is manually adjusted to roughly above the center of mass position of the deployable solar wing / deployable antenna. At this time, the longitudinal adjustment frame 41 is tightened and fixed to the hanging beam bracket 1 with screws and gaskets. After the rough adjustment, the longitudinal fine adjustment and transverse fine adjustment stages are entered. The position of the transverse adjustment block 51 on the suspension beam bracket 1 is adjusted by changing the relative position of the longitudinal fine-tuning screw 42 on the adjustment frame 41. The suspension assembly 3 also changes with the position change of the transverse adjustment block 51. After the center of mass of the deployable solar wing / deployable antenna is accurately adjusted to the longitudinal position, two set screws 52 are screwed into the transverse adjustment block 51 to fix the transverse adjustment block 51 on the suspension beam bracket 1, and the longitudinal fine-tuning is completed. The positions of the two transverse fine-tuning screws 42 on the transverse adjustment frame 53 are adjusted to accurately adjust the position of the suspension point connection block 32 on the transverse adjustment block 51 in the transverse direction. When the center of mass of the deployable solar wing / deployable antenna is adjusted to the transverse position, the suspension point connection block 32 is screwed to the pressing plate 35 at the lower end by two screws to press the suspension beam bracket 1, which plays the role of fixing the suspension point connection block 32 on the suspension beam bracket 1, and the transverse fine-tuning is completed. At this point, the suspension force of the zero-gravity suspension system can be accurately adjusted to the center of mass position of the deployable solar wing / deployable antenna through the adjustment of the suspension beam assembly.

[0078] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A gravity unloading hanging beam tooling for a satellite deployable structure, characterized in that: It comprises a hanging beam bracket (1), a connecting stud assembly (2) connecting the hanging beam bracket (1) with a satellite deployable mechanism, a suspension assembly (3) connecting the hanging beam bracket (1) with a zero-gravity suspension system, a longitudinal adjustment assembly (4) for longitudinally adjusting the satellite deployable mechanism, and a transverse adjustment assembly (5) for transversely adjusting the satellite deployable mechanism; One end of the connecting stud assembly (2) is connected to the hanging beam bracket (1), and the other end is connected to the top of the satellite deployable mechanism; the bottom of the suspension assembly (3) passes through the hanging beam bracket (1) and is located inside the lateral adjustment assembly (5); the longitudinal adjustment assembly (4) is located on the longitudinal side of the suspension assembly (3) and the lateral adjustment assembly (5); the lateral adjustment block of the lateral adjustment assembly (5) is connected to the outside of the hanging beam bracket (1) and one side is threadedly connected to the longitudinal adjustment assembly (4) and the other side is in contact with the suspension assembly (3); The suspension beam support (1) comprises a suspension beam support body (11) and a long slot hole (12) connected to the middle part of the suspension beam support body (11); The suspension assembly (3) comprises a suspension point (31), a suspension point connection block (32), and a self-aligning bearing (33) which are arranged in sequence; the suspension point connection block (32) comprises a suspension point connection block body (321); The longitudinal adjustment assembly (4) comprises a longitudinal adjustment frame (41), a longitudinal fine-adjustment screw (42) passing through a longitudinal side of the top of the longitudinal adjustment frame (41), and a longitudinal retaining ring (43) connected to the front end of the longitudinal fine-adjustment screw (42); the bottom of the longitudinal adjustment frame (41) can slide in the long slot hole (12) and can be tightened and fixed by screws and gaskets; and a fine-adjustment screw mounting boss is provided at one end of the longitudinal adjustment frame (41) close to the lateral adjustment assembly (5); The lateral adjustment component (5) comprises a lateral adjustment block (51), a set screw (52), a lateral adjustment frame (53) threadedly connected to the lateral side of the lateral adjustment block (51), and a lateral fine adjustment screw (54) threadedly connected to the lateral adjustment frame (53); the lateral adjustment block (51) comprises a hollow block body (511), internal rectangular notches (512) connected to both longitudinal sides of the block body (511), a longitudinal adjustment component inter-mounting plate (513) connected to the longitudinal edge of the block body (511) and extending upward, a lateral adjustment block screw hole (514) connected to the longitudinal adjustment component inter-mounting plate (513), and an external rectangular notch (515) connected to the upper surface of the block body (511); The block body (511) is inserted into the suspension beam support body (11) through the inner rectangular notches (512), the suspension point connection block body (321) is embedded between the outer rectangular notches (515) and can only move horizontally, and the longitudinal fine adjustment screw (42) passes through the transverse adjustment block screw hole (514) and extends longitudinally; The longitudinal position of the transverse adjustment block (51) on the suspension beam bracket (1) is adjusted by changing the longitudinal relative position of the longitudinal fine-adjustment screw (42), and the longitudinal position of the center of mass of the satellite deployable mechanism is adjusted; the transverse position of the suspension assembly (3) is adjusted by adjusting the relative position of the transverse fine-adjustment screw (54), so as to adjust the transverse position of the center of mass of the satellite deployable mechanism.

2. The gravity unloading hanging beam tooling of a satellite deployable structure according to claim 1, characterized in that: The hanging beam support (1) further comprises circular through holes (13) connected to the hanging beam support body (11) and located on both sides of the long slot hole (12); the hanging beam support body (11) is a long strip structure with a U-shaped cross section; The connecting stud assembly (2) comprises a stud (21) and a washer (22) embedded in the circular through hole (13); The number of the circular through holes (13) is the same as the number of the studs (21) and the washers (22), and is at least 2; The middle part of the stud (21) is an outer hexagonal body, and the upper and lower sides are both screw rods with threads; The lower screw rod of the stud (21) is threadedly connected to the suspension point hole of the satellite deployable mechanism, and the upper screw rod of the stud (21) passes through the washer (22) and is fixedly connected to a nut.

3. The gravity unloading hanging beam tooling of a satellite deployable structure according to claim 2, characterized in that: The suspension assembly (3) further comprises a suspension rod (34) passing through the self-aligning bearing (33), the suspension point connection block (32) and the suspension point (31), and a clamping plate (35) passing through the bottom of the suspension rod (34) and connected to the bottom of the suspension beam support body (11); The upper end of the suspension point (31) is connected to the zero-gravity suspension system, and the lower end is threadedly connected to the suspension rod (34); the suspension point connection block (32), the suspension beam bracket body (11) and the clamping plate (35) are sequentially connected by screws; the self-aligning bearing (33) is embedded in the suspension point connection block (32) and is interference-fitted; the self-aligning bearing (33) can enable the suspension rod (34) and the suspension point connection block (32) to rotate; One lateral side of the suspension point connection block (32) is connected to the side of the lateral adjustment component (5) via a lateral fine-tuning screw. The bottom of the suspension point connection block (32) is embedded in the lateral adjustment component (5) and can only move laterally in the lateral adjustment component (5). By adjusting the relative position of the lateral fine-tuning screw, the lateral position of the suspension point connection block (32) and the self-aligning bearing (33) is adjusted, and the suspension rod (34) and the suspension point connection block (32) are rotated, thereby adjusting the lateral position of the center of mass of the satellite deployable mechanism.

4. The gravity unloading hanging beam tooling of a satellite deployable structure according to claim 3, characterized in that: The upper end of the suspension point (31) is a hanging ear with a hole, a screw rod for connecting to the zero-gravity suspension system is installed in the hole of the hanging ear, and a nut connected to the screw rod is installed outside; The suspension point connection block (32) further comprises a screw mounting plate (322) vertically connected to a lateral side of the suspension point connection block body (321) and extending upward, a self-aligning bearing mounting body (323) connected to the upper surface of the suspension point connection block body (321), a fixing hole (324) connected to the suspension point connection block body (321), a screw hole (325) connected to the screw mounting plate (322), and a self-aligning bearing mounting hole (326) connected to the self-aligning bearing mounting body (323); the suspension point connection block body (321) is located in the lateral adjustment component (5) and can only move laterally in the lateral adjustment component (5); The suspension point connection block body (321) is a plate-like structure, the screw mounting plate (322) is a block-like structure connected to one side of the self-aligning bearing mounting body (323), the self-aligning bearing mounting body (323) is a hollow cylinder including an upper surface, and the bottom is connected to the suspension point connection block body (321), the fixing holes (324) are located on both sides of the self-aligning bearing mounting hole (326), the screw holes (325) are symmetrically arranged, the screw mounting plate (322) is connected to the side of the lateral adjustment component (5) through the fine adjustment screw of the lateral adjustment component (5), the self-aligning bearing mounting hole (326) is a through hole, and the suspension rod (34) passes through the self-aligning bearing mounting hole (326), the self-aligning bearing mounting body (323), and the suspension point connection block body (321) and extends downward; The position of the suspension point connection block body (321) in the lateral adjustment component (5) is adjusted by tightening or loosening the fine adjustment screw of the lateral adjustment component (5), so that the self-aligning bearing (33) drives the suspension rod (34) and the suspension point (31) to produce lateral displacement, thereby adjusting the lateral position of the center of mass of the satellite deployable mechanism.

5. The gravity unloading hanging beam tooling of a satellite deployable structure according to claim 3, characterized in that: The longitudinal adjustment frame (41) comprises a T-shaped plate (411) whose lower portion passes through the long slot hole (12) and can be fixed to the suspension beam support body (11) by screws, and a threaded hole boss (412) connected to the longitudinal end of the T-shaped plate (411) and extending upward, wherein the threaded hole boss (412) is adjacent to the longitudinal adjustment component inter-mounting plate (513); The longitudinal fine-adjusting screw (42) comprises a longitudinal screw body (421), a first square boss (422) connected to one end of the longitudinal screw body (421), and a first annular notch (423) connected to the other end of the longitudinal screw body (421); the longitudinal screw body (421) is a cylinder connected with fine threads; the longitudinal screw body (421) is used for fine position adjustment and anti-loosening; the longitudinal retaining rings (43) are respectively installed in the first annular notch (423) for limiting; the number of the first annular notch (423) and the number of the longitudinal retaining rings (43) are both two; The longitudinal fine-adjusting screw (42) is screwed into the threaded hole boss (412) through threaded engagement, and the end thereof extends into the longitudinal adjustment component inter-mounting plate (513) and is fixed by two longitudinal retaining rings (43) at both ends; The T-shaped plate (411) is fixed to the suspension beam support body (11), and the first square boss (422) is rotated using a tool to adjust the relative position of the T-shaped plate (411) and the transverse adjustment block (51), thereby changing the longitudinal position of the transverse adjustment block (51) on the suspension beam support (1) and adjusting the longitudinal position of the suspension point (31).

6. The gravity unloading hanging beam tooling of the satellite deployable structure according to claim 5, characterized in that: The lateral adjustment assembly (5) further comprises a lateral retaining ring (55) connected to the end of the lateral fine-adjustment screw rod (54); The lateral adjustment block (51) further comprises threaded through holes (516) connected to the lateral side of the block body (511), and the number of the threaded through holes (516) is four; The transverse adjustment frame (53) comprises a first transverse adjustment plate (531), a second transverse adjustment plate (532) and a third transverse adjustment plate (533) which are vertically connected in sequence; the first transverse adjustment plate (531), the second transverse adjustment plate (532) and the third transverse adjustment plate (533) are all plate-shaped structures; the third transverse adjustment plate (533) is parallel to the first transverse adjustment plate (531) and is located on the upper part of the first transverse adjustment plate (531); the first transverse adjustment plate (531) is connected to the vertical surface of the block body (511) through screws and two middle transverse adjustment block screw holes (514); the set screw (52) is used to fix the block body (511) to the suspension beam support body (11) through two transverse adjustment block screw holes (514) at both ends; The range of lateral movement of the suspension point connection block (32) within the outer rectangular row notch (515) is ±10 mm.

7. The gravity unloading hanging beam tooling of a satellite deployable structure according to claim 6, characterized in that: The transverse fine-adjusting screw (54) comprises a transverse screw body (541), a second square boss (542) connected to one end of the transverse screw body (541), and a second annular notch (543) connected to the other end of the transverse screw body (541); the transverse screw body (541) is a cylinder connected with fine threads; The transverse screw body (541) is used for fine position adjustment and anti-loosening. The transverse retaining rings (55) are respectively installed in the second annular notch (543) for limiting. The number of the second annular notch (543) and the transverse retaining rings (55) are both two. The transverse screw body (541) is screwed into the third transverse adjustment plate (533) through threaded engagement, and the end thereof extends into the screw mounting plate (322) of the suspension point connection block (32) and is fixed by the two transverse retaining rings (55) at both ends.

8. A gravity unloading hanging beam tooling for a satellite deployable structure according to any one of claims 1 to 7, characterized in that: The method of using the gravity unloading lifting beam tooling includes the following steps: S1. The actual center of mass position of the satellite deployable mechanism is first obtained by mass measurement, one end of the stud (21) of the connecting stud assembly (2) is screwed into the hanging point hole reserved on the base structure of the satellite deployable mechanism, torque is applied to prevent loosening, and the other end is passed through the washer (22) in the hole of the hanging beam bracket (1) and fixed with a nut, so that the hanging beam bracket (1) and the satellite deployable mechanism are fastened together; S2, assembling the suspension assembly (3), the longitudinal adjustment assembly (4), and the transverse adjustment assembly (5) on the suspension beam bracket (1), with all the set screws in an untightened state, adjusting the position of the transverse adjustment block (51) of the transverse adjustment assembly (5) on the suspension beam bracket (1) so that the transverse adjustment block (51) is roughly adjusted to a position above the center of mass of the satellite deployable mechanism, and then tightening and fixing the longitudinal adjustment frame (41) of the longitudinal adjustment assembly (4) on the suspension beam bracket (1) by means of screws and gaskets, and the rough adjustment is completed; S3, enter longitudinal fine adjustment: change the longitudinal fine adjustment screw (42) of the longitudinal adjustment component (4) relative to the longitudinal adjustment frame (41) to adjust the longitudinal position of the transverse adjustment block (51) on the suspension beam bracket (1), and the suspension component (3) also changes with the position change of the transverse adjustment block (51). After the center of mass of the satellite deployable mechanism is accurately adjusted to the longitudinal position, two set screws (52) are screwed into the transverse adjustment block (51) to fix the transverse adjustment block (51) on the suspension beam bracket (1), and the longitudinal fine adjustment is completed; S4, entering the lateral fine-tuning stage: adjusting the positions of the two lateral fine-tuning screws (54) on the lateral adjustment frame (53) of the lateral adjustment component (5), and accurately adjusting the position of the suspension point connection block (32) on the lateral adjustment block (51) laterally. When the center of mass of the satellite deployable mechanism is adjusted to be in the lateral position, the suspension point connection block (32) of the suspension component (3) is screwed to the clamping plate (35) at the lower end by two screws and the suspension beam bracket (1) is clamped to fix the suspension point connection block (32) on the suspension beam bracket (1). The lateral fine-tuning is completed, and a method for using a gravity unloading suspension beam tooling for a satellite deployable structure is completed.

9. The gravity unloading hanging beam tooling of the satellite deployable structure according to claim 8, characterized in that: In step S1, the satellite deployable mechanism is a deployable solar wing or a deployable antenna product; the number of the studs (21) is 4; In step S3, the number of the longitudinal fine-adjusting screws (42) is 2; In step S4, the number of the transverse fine-adjusting screws (54) is 2.

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