Thermal vacuum test device and method for whole solar wing

Abstract

The invention provides a whole solar wing thermal vacuum test device and method. The whole solar wing thermal vacuum test device comprises a process hinge, a guide rail, a lifting rope and a standby force bearing hanger, the process hinge is connected with the adjacent wing plates of the solar wing and can rigidly lock and release the adjacent wing plates; a lifting rope hangs the whole solar wing on the guide rail through a pressing seat hole in a reinforcing area on each wing plate and a process hinge; one end of the standby force-bearing hanger is connected with the wing plate, the other end of the standby force-bearing hanger is hung on the guide rail, and the standby force-bearing hanger does not bear force when the lifting rope bears force. According to the device and the method, the inter-plate cable can be effectively protected in the carrying and hanging process, the thermal stress change generated in the thermal test process is released, a reliable and firm hanging scheme is provided, and the risk and the cost caused by disassembling the whole wing into a single plate are effectively reduced.

Description

Technical Field

[0001] The present invention belongs to the technical field of thermal vacuum testing of solar wings, and in particular relates to a device and method for thermal vacuum testing of an entire solar wing. Background Art

[0002] With the complexity and diversity of spacecraft missions and the development of mass production and cost reduction, solar arrays are often stored with the wings folded after assembly. However, the development cycle of solar arrays is long and the storage environment is sensitive. For solar arrays that have been stored for an extended period of time, thermal vacuum tests need to be carried out to evaluate the product status.

[0003] The existing thermal vacuum test of solar wings is often carried out on the state of single solar wing boards. Each solar wing board is taken out from the packaging box one by one and hung on the guide rail using tooling. There is no electrical connection of cables or mechanical connection of hinges between boards. For solar wings that have been stored and the circuits have been installed, the cables between boards have been laid and fixed, and the electrical connectors have been welded. Disassembling them into single boards may cause the cables to be damaged during removal and restoration, and introduce operational risks. If the thermal vacuum test is carried out on the whole wing, the solar wing is unfolded from the folded state in the packaging box and transported to the unfolded state on the guide rail. Problems such as damage to the cables between boards and external force collision of the battery cells may occur. In addition, the large area and heavy weight of the whole wing state pose challenges to the reliability and flexibility of the hanging. Problems such as failure of the hanging method and inability to release thermal vacuum stress may occur. Summary of the invention

[0004] The technical problem solved by the present invention is: in view of the fact that solar cell arrays cannot be disassembled into single panels, and participating in thermal tests in a whole-wing state faces practical needs such as thermal stress release and hanging reliability, a solar wing whole-wing thermal vacuum test device and method are proposed. The device and method can effectively protect the cables and cells between panels during transportation and hanging, and adapt to the changes in thermal vacuum stress during thermal tests. The main and standby hanging also enhances the reliability of the hanging method, which brings great economic significance to the development of solar wings.

[0005] The technical solution provided by the present invention is as follows:

[0006] In a first aspect, a thermal vacuum test device for an entire solar wing includes a process hinge, a guide rail, a lifting rope, and a spare load-bearing hanging member; the process hinge connects adjacent wing panels of the solar wing, and can rigidly lock and release the adjacent wing panels; the lifting rope hangs the entire solar wing on the guide rail via the clamping seat holes in the reinforced areas of each wing panel and the process hinge; one end of the spare load-bearing hanging member is connected to the wing panel, and the other end is hung on the guide rail, and the spare load-bearing hanging member does not bear load when the lifting rope bears load.

[0007] In a second aspect, a solar wing thermal vacuum test method includes:

[0008] When the solar wing is folded, the adjacent wing panels are connected by the process hinges, and the solar wing is unfolded around the process hinge shaft;

[0009] After the solar wing is unfolded, the process hinge shaft is locked to implement the rigid connection of each wing panel, and the unfolded solar wing is moved to the guide rail;

[0010] Use a lifting rope to bypass the guide rail, and lift the entire wing through the clamping seat holes and process hinges in the reinforced area of ​​each wing plate, remove the process hinge shaft, and release the rigid connection between the wing plates;

[0011] Connect one end of the load-bearing hanging piece to the wing plate, and hang the other end on the guide rail;

[0012] Confirm that multiple lifting ropes are taut and evenly stressed, and that the load is borne by the lifting ropes and the spare load-bearing hanging parts are not;

[0013] After the thermal vacuum test is completed, the process hinge shaft is locked, the solar wing is lifted down from the guide rail and folded after the process hinge is unlocked.

[0014] A solar wing thermal vacuum test device and method provided by the present invention has the following beneficial effects:

[0015] (1) Affected by the overall task changes or mass production requirements, the solar cell array is transferred to storage after the assembly work is completed. After the storage work is completed, the solar cell array that exceeds the life limit needs to be subjected to thermal vacuum testing to evaluate the product status. Since the solar wing in the storage state has completed the circuit layout work, disassembling it into a single board for thermal vacuum testing will increase the cost and time, and the restoration of wire welding after the thermal test may have power supply hazards. The area and weight of the solar wing in the whole wing state are large, which limits its flexibility in transportation and hanging, and it is difficult to solve the problem of thermal stress release between the whole wing boards and potential storage aging of embedded parts during the vacuum thermal test. The present invention adopts a process hinge to realize the rigid connection of each wing board before hanging, and releases the connection after hanging, which can effectively protect the cables between the boards during transportation and hanging, and release the thermal stress changes that occur during the thermal test, effectively reducing the risks and costs brought by disassembling the whole wing into a single board. At the same time, passing through the clamping seat hole during hanging can deal with the potential storage aging problem of the side embedded parts used in conventional hanging schemes.

[0016] (2) The present invention provides a solar wing thermal vacuum test device and method, in which the suspension is divided into a main load-bearing suspension and a backup load-bearing suspension. The main load-bearing suspension adopts a suspension rope to bear the load. At least two suspension points are set on each wing plate, providing a reliable and firm suspension solution.

[0017] (3) The present invention provides a solar wing thermal vacuum test device and method, in which the male hinge and the female hinge in the process hinge are processed with support ears on the opposite sides, and the rotating shaft passes through the support ears to connect the male hinge and the female hinge. The support ears on the opposite sides of the male hinge and the female hinge can meet the requirements of 0° folding to 180° unfolding of the male hinge and the female hinge; the rotating shaft is an assembly of bolts and nuts, and the locking and releasing of the rotating shaft are achieved by tightening or loosening the nuts, with a simple structure and high reliability.

[0018] (4) The present invention provides a thermal vacuum test device and method for the entire solar wing. The U-shaped connector of the load-bearing hanger can be placed on any part of the guide rail to facilitate threaded cooperation with the embedded threaded hole on the side of the wing plate. The diameter of the first connecting hole on the U-shaped connector is designed to be larger than the outer diameter of the screw of the adapter bolt. The stress state of the load-bearing hanger is evaluated by the axial deviation value between the adapter bolt and the first connecting hole on the U-shaped connector. The evaluation method is intuitive and simplifies the evaluation difficulty. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of the structure of the solar wing thermal vacuum test device;

[0020] Figure 2 It is a structural schematic diagram of the process hinge;

[0021] Figure 3 A schematic diagram of the structure of the load-bearing hanging parts;

[0022] Figure 4 It is a schematic diagram of the assembly of the load-bearing hanging parts, guide rails and wing plates. DETAILED DESCRIPTION

[0023] The following detailed description of the present invention will make the features and advantages of the present invention more clear and explicit.

[0024] The word “exemplary” is used exclusively herein to mean “serving as an example, example, or illustration.” Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments.

[0025] like Figure 1 As shown, the present invention provides a thermal vacuum test device for the entire solar wing, comprising a process hinge 3, a guide rail 4, a suspension rope 5 and a spare load-bearing suspension member; the process hinge 3 connects adjacent wing panels 1 of the solar wing, and can rigidly lock and release the adjacent wing panels 1; the suspension rope 5 hangs the entire solar wing on the guide rail 4 through the clamping seat holes 2 in the reinforced areas of each wing panel and the process hinge 3; one end of the spare load-bearing suspension member is connected to the wing panel 1, and the other end is suspended on the guide rail 4, and the spare load-bearing suspension member does not bear load when the suspension rope bears load.

[0026] like Figure 2As shown, the process hinge 3 includes a male hinge 6, a female hinge 7 and a rotating shaft 8. The male hinge 6 and the female hinge 7 are rotatably connected via the rotating shaft 8. The male hinge 6 and the female hinge 7 are respectively connected to two adjacent wing plates via connecting holes 9 thereon. The locking and releasing of the rotating shaft 8 locks and releases the rotational positions of the male hinge 6 and the female hinge 7, thereby completing the rigid fixed connection and release of the two adjacent wing plates.

[0027] Preferably, lugs are processed on the opposite sides of the male hinge 6 and the female hinge 7, and the rotating shaft 8 passes through the lugs to connect the male hinge 6 and the female hinge 7. The design of the lugs on the opposite sides of the male hinge 6 and the female hinge 7 can meet the requirements of 0° folding to 180° unfolding of the male hinge 6 and the female hinge.

[0028] Preferably, the male hinge 6 and the female hinge 7 are U-shaped plates, a connecting hole 9 is opened on the U-shaped plate, the wing plate is inserted into the opening of the U-shaped plate, the connecting hole 9 is aligned with the hinge hole on the wing plate, and is connected by a fastener passing through the connecting hole 9 and the hinge hole of the wing plate.

[0029] Preferably, the rotating shaft 8 is a bolt and nut assembly, and the locking and releasing of the rotating shaft is achieved by tightening or loosening the nut, which has a simple structure and high reliability.

[0030] like Figure 3 and Figure 4 As shown, the load-bearing hanging component includes a U-shaped connecting member 10, an adapter 12, an adapter screw 14 and an adapter bolt 15; the U-shaped connecting member 10 is hung on the guide rail 4, and two opposite first connecting holes 11 are opened on both sides; the adapter 12 is arranged in the opening of the U-shaped connecting member 10, and two second connecting holes 13 are opened at both ends, and the second connecting hole 13 is a threaded hole, and the U-shaped connecting member 10 and the adapter 12 are connected by the adapter bolt 15 passing through the first connecting hole 11 and the second connecting hole 13; the upper end of the adapter screw 14 is inserted into the adapter 12, and the lower end is threadedly matched with the embedded threaded hole 16 on the side of the wing plate to achieve connection with the wing plate. The adapter 12 is preferably a T-shaped adapter, and the upper end of the adapter screw 14 is inserted into the adapter at the lower end of the adapter 12.

[0031] The present invention provides a solar wing thermal vacuum test method, comprising the following steps:

[0032] (1) When the solar wing is folded, the adjacent wing panels 1 are connected by the process hinges 3. For example, each solar wing includes three wing panels, and two adjacent wing panels are connected by two process hinges 3. The male hinge 6 and the female hinge 7 of the process hinge 3 are connected to the hinge holes of the two adjacent wing panels 1 through the connecting holes 9, and the solar wing is unfolded around the process hinge shaft 8. After the solar wing is unfolded, the process hinge shaft 8 is locked to realize the rigid connection of each wing panel, and the unfolded solar wing is moved to the guide rail 4.

[0033] In this step, the transverse width of the process hinge 3 is shorter than the length of the inter-board cable, and the inter-board cable is in a relaxed state after the process hinge 3 links the adjacent wing panels.

[0034] (2) A single wing panel weighs 7 kg. A single lifting rope 5 such as a Kevlar rope with a load capacity of not less than 329 N is selected to pass around the guide rail 4, and the entire wing is lifted through the clamping seat hole 2 and the process hinge 3 of each wing panel reinforcement area. The process hinge shaft 8 is removed to release the rigid connection between the wing panels.

[0035] In this step, at least two hanging points are arranged on each wing plate, and the hanging points can be the clamping seat holes 2 or the process hinges 3 in the reinforcement area of ​​the wing plate.

[0036] In this step, after the process hinge shaft 8 is removed, the male and female hinges on both sides of the process hinge are not in contact with each other. If contact occurs, the hinges can be removed.

[0037] (3) Screw the adapter screw 14 on the adapter 12 into the embedded threaded hole 16 on the upper side of the wing plate, hang the U-shaped connector 10 on the guide rail 4, and then use the adapter bolt 15 to pass through the first connection hole 11 of the U-shaped connector 10 and the second connection hole 13 of the adapter 12 in sequence.

[0038] In this step, the depth of the adapter screw 14 on the adapter 12 screwed into the threaded hole 16 is adjusted to adapt to the height of the hanging rope 5 so that the U-shaped connector 10 does not bear the gravity of the adapter 12.

[0039] In this step, the diameter of the first connecting hole 11 on the U-shaped connecting member 10 is larger than the outer diameter of the screw rod of the adapter bolt 15 by at least 3 mm.

[0040] (4) Check the hanging state to confirm that the multiple hanging ropes 5 are taut and evenly stressed, and the U-shaped connector 10 does not bear the weight of the adapter 12.

[0041] In this step, the deviation of the tension meter measurement value of each suspension rope 5 does not exceed 5%, which serves as an evaluation index for the uniform force of the suspension rope.

[0042] In this step, the axis deviation value between the adapter bolt 15 and the first connection hole 11 on the U-shaped connector 10 is ≤1 mm, which serves as an evaluation index of the load-bearing state of the adapter 12 and the U-shaped connector 10 .

[0043] (5) After the thermal vacuum test is completed, the process hinge shaft 8 is locked, the solar wing is lifted down from the guide rail, and the process hinge 3 is unlocked and then folded into the packaging box.

[0044] The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions cannot be understood as limiting the present invention. Those skilled in the art understand that, without departing from the spirit and scope of the present invention, a variety of equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its implementation methods, all of which fall within the scope of the present invention. The scope of protection of the present invention shall be subject to the attached claims.

[0045] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A solar wing thermal vacuum test device, characterized in that: The invention comprises a process hinge (3), a guide rail (4), a suspension rope (5) and a spare load-bearing suspension member; the process hinge (3) connects adjacent wing panels of the solar wing and can rigidly lock and release the adjacent wing panels; the suspension rope (5) suspends the entire solar wing on the guide rail (4) through a clamping seat hole (2) in a reinforced area on each wing panel and the process hinge (3); one end of the spare load-bearing suspension member is connected to the wing panel and the other end is suspended on the guide rail (4); when the suspension rope bears load, the spare load-bearing suspension member does not bear load.

2. The solar wing thermal vacuum test device according to claim 1, characterized in that: The process hinge (3) comprises a male hinge (6), a female hinge (7) and a rotating shaft (8); the male hinge (6) and the female hinge (7) are rotatably connected via the rotating shaft (8); the male hinge (6) and the female hinge (7) are respectively connected to two adjacent wing plates via connecting holes (9) thereon.

3. The solar wing thermal vacuum test device according to claim 2, characterized in that: The male hinge (6) and the female hinge (7) are both provided with supporting ears on the opposite sides thereof, and the rotating shaft (8) passes through the supporting ears to connect the male hinge (6) and the female hinge (7).

4. The solar wing thermal vacuum test device according to claim 2, characterized in that: The male hinge (6) and the female hinge (7) are U-shaped plates, and a connecting hole (9) is provided on the U-shaped plate. The U-shaped plate opening is inserted into the wing plate, and the connecting hole (9) is aligned with the hinge hole on the wing plate, and is connected by a fastener passing through the connecting hole (9) and the hinge hole of the wing plate.

5. The solar wing thermal vacuum test device according to claim 2, characterized in that: The rotating shaft (8) is a bolt and nut assembly, and the rotating shaft is locked and released by tightening or loosening the nut.

6. The solar wing thermal vacuum test device according to claim 1, characterized in that: The load-bearing hanging component comprises a U-shaped connecting component (10), an adapter component (12), an adapter screw (14) and an adapter bolt (15); the U-shaped connecting component (10) is hung on the guide rail (4), and two opposite first connecting holes (11) are opened on both sides; the adapter component (12) is arranged in the opening of the U-shaped connecting component (10), and two second connecting holes (13) are opened at both ends, and the second connecting hole (13) is a threaded hole, and the U-shaped connecting component (10) and the adapter component (12) are connected by the adapter bolt (15) passing through the first connecting hole (11) and the second connecting hole (13); the upper end of the adapter screw (14) is inserted into the adapter component (12), and the lower end is threadedly matched with the embedded threaded hole (16) on the side surface of the wing plate to implement the connection with the wing plate.

7. A thermal vacuum test method for a solar wing, characterized in that: The solar wing thermal vacuum test device according to any one of claims 1 to 6 is used for implementation, comprising the following steps: When the solar wing is folded, the adjacent wing panels are connected by the process hinges, and the solar wing is unfolded around the process hinge shaft; After the solar wing is unfolded, the process hinge shaft is locked to implement the rigid connection of each wing panel, and the unfolded solar wing is moved to the guide rail; Use a lifting rope to bypass the guide rail, and lift the entire wing through the clamping seat holes and process hinges in the reinforced area of ​​each wing plate, remove the process hinge shaft, and release the rigid connection between the wing plates; Connect one end of the load-bearing hanging piece to the wing plate, and hang the other end on the guide rail; Confirm that multiple lifting ropes are taut and evenly stressed, and that the load is borne by the lifting ropes and the spare load-bearing hanging parts are not; After the thermal vacuum test is completed, the process hinge shaft is locked, the solar wing is lifted down from the guide rail and folded after the process hinge is unlocked.

8. The thermal vacuum test method for the entire solar wing according to claim 7, characterized in that: In the step of connecting adjacent wing panels via process hinges when the solar wings are folded, the transverse width of the process hinges is shorter than the length of the inter-board cables, and the inter-board cables are in a relaxed state after the process hinges connect the adjacent wing panels.

9. The solar wing thermal vacuum test method according to claim 7, characterized in that: In the step of using a lifting rope to bypass the guide rail and lift the entire wing through the process holes and process hinges of each wing panel reinforcement area, at least two hanging points are set on each wing panel, and the hanging points are the clamping seat holes or process hinges of the wing panel reinforcement area.

10. The solar wing thermal vacuum test method according to claim 7, characterized in that: In the step of confirming that multiple ropes are taut and in a uniform stress state, and that the ropes bear the stress and the spare load-bearing hanging parts do not bear the stress, the deviation of the tension meter measurement value of each rope does not exceed 5%, which is used as an evaluation indicator for the uniform stress of the ropes; and / or the axial deviation value between the adapter bolt and the first connecting hole on the U-shaped connecting part is ≤1mm, which is used as an evaluation indicator for the load-bearing state of the spare load-bearing hanging parts.

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