A spacecraft multi-folded solar array deployment experimental testing device and testing method

Abstract

The application discloses a kind of spacecraft with multiple folding solar array deployment experimental test device and testing method, it is related to aerospace technology field, after satellite launch vehicle separates, satellite solar cell solar array deployment, satellite solar array deployment needs a series of ground test, existing experimental test device is realized by the establishment of physical model, parameter collection to simulate, but sky environment changes greatly, existing experimental test device is poor to scene simulation, the present application simulates the complex environment of space by pressure test, wherein in pressure test, by different angles of traction makes the connecting point of solar array body and satellite body stress, by acceleration to satellite body, so that satellite body is in motion state, and then the state of solar array body is monitored, test is carried out under the condition of acceleration, test can obtain more excellent effect, simulation effect is also more excellent, reduce the existence rate of later fault.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a multi-fold solar array deployment experimental testing device and testing method for a spacecraft. BACKGROUND

[0002] A satellite solar array is a device that converts solar energy into electrical energy, commonly used on satellites and spacecraft to provide power supply. Satellite solar arrays use the photovoltaic effect to convert solar radiation into electrical energy. The surface of the solar array is covered with solar cells. When sunlight hits the solar cells, photons hit the crystalline silicon or other materials, exciting electrons and generating electric current. These electric currents can supply power to the equipment and systems on the satellite through circuit connection.

[0003] To this end, Chinese patent number CN109665124A discloses a spacecraft panel deployable structure thermal environment simulation suspension experimental device, which includes a load-bearing support, a deployable solar array suspended below the load-bearing support by a suspension device connected by self-locking hinges, a motor drive module fixed on the side of the load-bearing support to provide power for the folding movement of the deployable solar array, a synchronous pulley mechanism installed between the deployable solar arrays to transmit synchronous folding and unfolding movements between the solar arrays, and a thermal environment simulation device installed on the front and back of the load-bearing support to provide a thermal environment for the deployable solar array. The present application can simulate the deployment and locking process of the spacecraft deployable structure, and can simulate the deformation of the panel under the conditions of space microgravity and thermal radiation, test the dynamic characteristics of the deployable structure, and has very important significance for the design and on-orbit performance of the spacecraft deployable structure.

[0004] After the satellite is separated from the launch vehicle, the satellite solar array is deployed. A series of ground tests are required to verify the rationality of the design and the effectiveness of the solar array deployment. In the deployment simulation test of the solar array, a test device needs to be specified to complete the simulation. The existing experimental testing device realizes simulation through the establishment of a physical model and the collection of parameters. However, the sky environment changes greatly, and the existing experimental testing device has poor scene simulation.

[0005] To solve the above problems, a multi-fold solar array deployment experimental testing device and testing method for a spacecraft are proposed. SUMMARY

[0006] The present application aims to provide a multi-fold solar array deployment experimental testing device and testing method for a spacecraft, which solves the problem of being unable to simulate different environments in the background art.

[0007] In order to achieve the above object, the present application provides the following technical scheme: a spacecraft multi-folded sailboard unfolding experimental testing device, comprising a simulation component, the simulation component comprises an experimental frame, a glass plate is embedded in the inside of the experimental frame, an upper cover plate is installed at the top end of the experimental frame, a bottom plate is connected to the bottom end of the experimental frame, and the experimental frame, the glass plate, the upper cover plate and the bottom plate constitute a sealed frame structure;

[0008] A traction assembly is installed on the outer wall of the upper cover plate, a traction bin is installed on the outer wall of the upper cover plate, a drive motor is installed on the outer wall of the traction bin, a transmission roller is connected to the output end of the drive motor, the transmission roller is embedded in the inside of the traction bin, a gear set is connected to the other side of the transmission roller, a traction rope is embedded in the inside of the transmission roller, the traction rope is connected to the sailboard body on one side, a satellite body is arranged in the inside of the experimental frame, the sailboard body is connected to the top end of the satellite body, and the traction rope is connected to the sailboard body.

[0009] A simulation assembly is connected to the inner wall of the experimental frame, the simulation assembly comprises a mounting frame, the mounting frame is connected to the inner wall of the experimental frame, a support bracket is fixedly connected to the bottom end of the mounting frame, a support frame is embedded in the inside of the mounting frame, the satellite body is placed on the top surface of the support frame, the bottom end of the satellite body is embedded in the inside of the mounting frame, a through slot is formed in the top surface of the mounting frame, a booster ball is installed in the through slot, the booster ball is attached to the bottom end of the satellite body on one side, a fixing frame is fixedly connected to the bottom end of the support frame, a propelling roller is installed on one side of the fixing frame, the propelling roller is driven by a motor, an engaging propelling belt is sleeved on the outer surface of the propelling roller, the engaging propelling belt is engaged with a propelling tooth at the top end, and the propelling tooth is fixedly connected to the bottom end of the satellite body.

[0010] An adjustment experimental assembly is installed on the inner wall of the experimental frame.

[0011] Preferably, a cross frame plate is arranged at the top end of the experimental frame, a limiting roller is embedded in the inside of the cross frame plate, a sliding frame is slidably connected to the top surface of the cross frame plate, a limiting frame is embedded in the inside of the sliding frame, a positioning pulley is installed in the inside of the limiting frame, and the traction rope is embedded in the inside of the limiting frame through the inside of the transmission roller.

[0012] Preferably, the traction rope is embedded between the limiting frame and the positioning pulley, and one side wall of the traction rope is attached to the surface of the positioning pulley.

[0013] Preferably, the satellite body is horizontally and slidably connected to the mounting frame, and the bottom surface of the satellite body is located on the top surface of the support frame and slides on the surface of the support frame.

[0014] Preferably, the middle position of the support frame is provided with an opening, and the engaging advancing belt is embedded in the opening and located directly below the advancing clamping tooth.

[0015] Preferably, the adjusting experimental assembly comprises a positioning strip, the inner wall of the experimental frame is provided with the positioning strip, the inner part of the positioning strip is provided with a positioning groove, and the inner part of the positioning groove is embedded with a positioning rod, one side of the positioning rod is fixedly connected to the side wall of the mounting frame, and the positioning rod slides in the positioning groove.

[0016] Preferably, the positioning strip is in an arc shape, and the arc center of the positioning strip is consistent with the deflection center of the mounting frame.

[0017] Preferably, the inner wall of the experimental frame is fixedly connected with a motor set, the output end of the motor set is connected with a rotating disc, one side of the rotating disc is fixedly connected to the side wall of the mounting frame, and the center of the rotating disc is consistent with the center of the positioning strip.

[0018] A testing method of a spacecraft multi-folded sailboard deployment experimental testing device, in which a satellite body is installed to the upper end of a support frame, a traction rope is connected between the sailboard body, the rotation of a transmission roller drives the traction rope to traction, and the traction drives the sailboard body to deploy.

[0019] Preferably, the deployment of the sailboard body, the motor drives the engaging advancing belt to rotate, the rotation drives the satellite body to move forward, and after the satellite body moves to the top end of the support frame, the motor drives the satellite body to move in the opposite direction.

[0020] Compared with the prior art, the spacecraft multi-folded sailboard deployment experimental testing device and the testing method have the following beneficial effects:

[0021] 1. The spacecraft multi-folded sailboard deployment experimental testing device and the testing method provided by the application can keep the inside of the experimental frame in a relatively vacuum state by evacuating the inside of the experimental frame through an air pump, complete the experiment in the vacuum state, and observe the test state through the glass plate for the convenience of observation. In order to realize simulation of different states, pressure test is conducted on the connecting point, the connecting point of the sailboard body and the satellite body is stressed by traction at different angles, the satellite body is accelerated, the satellite body is in a motion state, and the state of the sailboard body is monitored. The test is conducted in the acceleration state, and the test can achieve more excellent effects and more excellent simulation effects, and the existence rate of faults in the later period is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 It is a schematic diagram of the overall structure of the application;

[0023] Figure 2 It is the structural schematic diagram of the experiment frame and the upper cover plate of the present application;

[0024] Figure 3 It is the sectional structural schematic diagram of the upper cover plate of the present application;

[0025] Figure 4 It is the structural schematic diagram of the traction rope and the sliding frame of the present application;

[0026] Figure 5 It is the structural schematic diagram of the support frame and the power ball of the present application;

[0027] Figure 6 It is the structural schematic diagram of the sail plate body and the satellite body of the present application;

[0028] Figure 7 It is the structural schematic diagram of the support frame and the meshed propulsion belt of the present application;

[0029] Figure 8 It is the structural schematic diagram of the propulsion tooth and the meshed propulsion belt of the present application.

[0030] In the figure: 1, simulation component; 11, experiment frame; 12, glass plate; 13, upper cover plate; 14, bottom plate; 15, sail plate body; 16, satellite body; 2, traction assembly; 21, traction bin; 22, cross frame plate; 23, transmission roller; 24, gear set; 25, drive motor; 26, traction rope; 27, limiting roller; 28, sliding frame; 29, limiting frame; 30, positioning pulley; 3, simulation assembly; 31, mounting frame; 32, support frame; 33, power ball; 34, propulsion tooth; 35, meshed propulsion belt; 36, propulsion roller; 37, fixed frame; 38, support bracket; 4, adjustment experiment assembly; 41, positioning strip; 42, positioning rod; 43, positioning groove; 44, motor set; 45, turntable. DETAILED DESCRIPTION

[0031] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the present application.

[0032] The present application will be described in detail with reference to the drawings for further understanding the present application.

[0033] Combined with the drawings Figures 1-8The application discloses a spacecraft multi-folded sailboard deployment experimental testing device, which comprises a simulation component 1, the simulation component 1 comprises an experimental frame 11, a glass plate 12 is embedded in the experimental frame 11, an upper cover plate 13 is installed at the top end of the experimental frame 11, a bottom plate 14 is connected to the bottom end of the experimental frame 11, and the experimental frame 11, the glass plate 12, the upper cover plate 13 and the bottom plate 14 form a sealed frame structure, in order to better simulate the space environment, the sailboard body 15 and the satellite body 16 are sealed, the deployment of the sailboard body 15 is simulated in the sealed environment, the simulation of the environment can improve the precision of the experimental test, the sailboard body 15 and the satellite body 16 are first stored in the experimental frame 11, the inside of the experimental frame 11 is sealed through the glass plate 12 and the upper cover plate 13, the upper end of the upper cover plate 13 is provided with an air extraction hole, the inside of the experimental frame 11 is evacuated through an air extraction pump, the inside of the experimental frame 11 is kept in a relatively vacuum state by extracting the internal air, and the experiment is completed in the vacuum state, in order to facilitate observation of the test, the test state can be observed through the glass plate 12;

[0034] A horizontal frame plate 22 is arranged at the top end of the experimental frame 11, a limiting roller 27 is embedded in the horizontal frame plate 22, a sliding frame 28 is slidably connected to the top surface of the horizontal frame plate 22, a limiting frame 29 is embedded in the sliding frame 28, a positioning pulley 30 is installed in the limiting frame 29, a traction rope 26 is embedded in the limiting frame 29 through the inside of a transmission roller 23, the traction rope 26 is embedded between the limiting frame 29 and the positioning pulley 30, and one side wall of the traction rope 26 is attached to the surface of the positioning pulley 30. In the deployment of the sailboard body 15, the sailboard body 15 is deployed under the traction of the traction rope 26, in the operation, the rotation of the driving motor 25 drives the rotation of the transmission roller 23, when the transmission roller 23 rotates, the traction rope 26 embedded in the inside of the transmission roller 23 will advance with the rotation of the transmission roller 23, the other end of the traction rope 26 is connected to the top surface of the sailboard body 15, and the deployment of the sailboard body 15 is driven by pulling the traction rope 26. In order to realize simulation of different states, pressure test is conducted on the connecting point, and the complex space environment is simulated through the pressure test. In the pressure test, the connecting point of the sailboard body 15 and the satellite body 16 is stressed through traction at different angles.

[0035] Firstly, the position of the sliding frame 28 is adjusted through an electric control device, the position of the sliding frame 28 at the upper end of the horizontal frame plate 22 can be driven by the electric control device or adjusted manually, the position of the sliding frame 28 is adjusted, the traction rope 26 is embedded in different sections of the limiting roller 27, at this time, the direction of force changes, and the connecting point is tested through traction in different directions.

[0036] When the traction rope 26 is adjusted to the position of the limiting roller 27 embedded between the two groups of limiting rollers 27 at the top end of the cross beam plate 22, the direction of the applied force changes, and the traction is adjusted at different angles, the pressure test range is improved, the outer wall of the upper cover plate 13 is provided with the traction assembly 2, the outer wall of the upper cover plate 13 is provided with the traction bin 21, the outer wall of the traction bin 21 is provided with the driving motor 25, the output end of the driving motor 25 is connected with the transmission roller 23, the transmission roller 23 is embedded in the inside of the traction bin 21, the other side of the transmission roller 23 is connected with the gear set 24, the inside of the transmission roller 23 is embedded with the traction rope 26, one side of the traction rope 26 is connected with the sail plate body 15, the inside of the experimental rack 11 is provided with the satellite body 16, the top end of the satellite body 16 is connected with the sail plate body 15, the traction rope 26 is connected with the sail plate body 15;

[0037] The inner wall of the experimental rack 11 is connected with the simulation assembly 3, the simulation assembly 3 comprises a mounting frame 31, the inner wall of the experimental rack 11 is connected with the mounting frame 31, the bottom end of the mounting frame 31 is fixedly connected with a support support 38, the satellite body 16 is horizontally slidably connected between the mounting frame 31, one side of the bottom surface of the satellite body 16 is located on the top surface of the support frame 32 and slides on the surface of the support frame 32, the inside of the mounting frame 31 is embedded with the support frame 32, the bottom end of the satellite body 16 is placed on the top surface of the support frame 32, the bottom end of the satellite body 16 is embedded in the inside of the mounting frame 31, the top surface of the mounting frame 31 is provided with a through slot, the through slot is provided with a booster ball 33, the booster ball 33 is attached to one side of the bottom end of the satellite body 16, the bottom end of the support frame 32 is fixedly connected with a fixed frame 37, one side of the fixed frame 37 is provided with a propelling roller 36, the propelling roller 36 is driven by a motor, the outer surface of the propelling roller 36 is sleeved with an engaging propelling belt 35, the top end of the engaging propelling belt 35 is engaged with a propelling tooth 34, the middle position of the support frame 32 is provided with an opening, the engaging propelling belt 35 is embedded in the opening and located directly below the propelling tooth 34, the bottom end of the satellite body 16 is fixedly connected with the propelling tooth 34, in the simulation environment, the satellite body 16 is in a motion state by acceleration, and then the state of the sail plate body 15 is monitored, the test is carried out in the state of acceleration, when the motor drives the engaging propelling belt 35 to rotate, the engaging propelling belt 35 and the propelling tooth 34 are engaged with each other, when the engaging propelling belt 35 moves, the propelling tooth 34 is driven to move, the movement of the propelling tooth 34 drives the satellite body 16 to slide in the inside of the mounting frame 31, and also slides on the upper surface of the support frame 32 and the bottom surface of the booster ball 33, the booster ball 33 is used to drive the satellite body 16 to move by reciprocating movement of the engaging propelling belt 35, the sail plate body 15 is unfolded or unfolded and the state of the sail plate body 15 is tested in the motion state;

[0038] The state of the satellite body 16 movement is simulated by acceleration, and the simulation effect is more excellent. In addition, the experimental test in different states is realized by adjusting the angles of the satellite body 16 and the sailboard body 15.

[0039] The inner wall of the experimental frame 11 is provided with an adjusting experimental assembly 4. The adjusting experimental assembly 4 comprises a positioning strip 41, the inner wall of the experimental frame 11 is provided with the positioning strip 41, the inner part of the positioning strip 41 is provided with a positioning groove 43, the inner part of the positioning groove 43 is embedded with a positioning rod 42, one side of the positioning rod 42 is fixedly connected to the side wall of the mounting frame 31, the positioning rod 42 slides in the inner part of the positioning groove 43, the positioning strip 41 is provided in a circular arc shape, the center of the circular arc of the positioning strip 41 is consistent with the center of the deflection of the mounting frame 31, the inner wall of the experimental frame 11 is fixedly connected with a motor set 44, the output end of the motor set 44 is connected with a rotating disc 45, one side of the rotating disc 45 is fixedly connected to the side wall of the mounting frame 31, the center of the rotating disc 45 is consistent with the center of the positioning strip 41. When the angles of the sailboard body 15 and the satellite body 16 are adjusted, the experiment is carried out in different states by inclining the satellite body 16 downward or upward, and the normal opening of the sailboard body 15 is ensured through the experimental test in different states.

[0040] When adjusting, the rotating disc 45 is driven to rotate by the motor set 44, so that the mounting frame 31 is deflected in angle, and after deflection, the sailboard body 15 and the satellite body 16 are adjusted to different states. In order to improve the stability of the mounting frame 31, the positioning rod 42 and the positioning groove 43 are arranged to ensure the stability during the adjustment process.

[0041] A testing method of a spacecraft multi-fold sailboard unfolding experimental testing device. The satellite body 16 is installed to the upper end of the support frame 32, and the traction rope 26 is connected between the sailboard body 15. After connection, the rotation of the transmission roller 23 pulls the traction rope 26, which drives the sailboard body 15 to unfold. The unfolding of the sailboard body 15 drives the motor to rotate the propulsion belt 35, which drives the satellite body 16 to move forward after rotation. After moving to the top end of the support frame 32, the motor drives the satellite body 16 to move in the opposite direction.

[0042] It should be noted that, in the present document, relational terms such as first and second and the like can be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0043] While embodiments of the application have been shown and described, it is to be understood that the application is not limited to the details of the embodiments described, since numerous changes, modifications, substitutions and variations can be made thereto without departing from the spirit and scope of the application as defined by the appended claims and their equivalents.

Claims

1. A test device for the deployment of multi-fold sails for spacecraft, comprising a simulation component (1), characterized in that: The simulation component (1) includes an experimental frame (11), in which a glass plate (12) is embedded, a top cover plate (13) is installed at the top of the experimental frame (11), and a bottom plate (14) is connected to the bottom of the experimental frame (11). The experimental frame (11), the glass plate (12), the top cover plate (13) and the bottom plate (14) form a sealed frame structure. A traction assembly (2) is installed on the outer wall of the upper cover plate (13). A traction chamber (21) is installed on the outer wall of the upper cover plate (13). A drive motor (25) is installed on the outer wall of the traction chamber (21). A transmission roller (23) is connected to the output end of the drive motor (25). The transmission roller (23) is embedded inside the traction chamber (21). A gear set (24) is connected to the other side of the transmission roller (23). A traction rope (26) is embedded inside the transmission roller (23). A sailboard body (15) is connected to one side of the traction rope (26). A satellite body (16) is set inside the experimental frame (11). The top of the satellite body (16) is connected to the sailboard body (15). The traction rope (26) is connected to the sailboard body (15). A simulation component (3) is connected to the inner wall of the experimental frame (11). The simulation component (3) includes a mounting frame (31). The mounting frame (31) is connected to the inner wall of the experimental frame (11). A support bracket (38) is fixedly connected to the bottom end of the mounting frame (31). A support frame (32) is embedded inside the mounting frame (31). The bottom end of the satellite body (16) is placed on the top surface of the support frame (32). The bottom end of the satellite body (16) is embedded inside the mounting frame (31). A through groove is provided on the top surface of the mounting frame (31). A booster ball (33) is installed in the through groove. The booster ball (33) is attached to one side of the bottom end of the satellite body (16). A fixed frame (37) is fixedly connected to the bottom end of the support frame (32). A pusher roller (36) is installed on one side of the fixed frame (37). The pusher roller (36) is driven by a motor. A meshing pusher belt (35) is sleeved on the outer surface of the pusher roller (36). A pusher tooth (34) is meshed at the top end of the meshing pusher belt (35). A pusher tooth (34) is fixedly connected to the bottom end of the satellite body (16). The experimental setup (11) is equipped with an adjustment component (4) on its inner wall.

2. The experimental testing device for deploying multi-fold sails for spacecraft according to claim 1, characterized in that: The top of the experimental frame (11) is provided with a horizontal frame plate (22), and a limiting roller (27) is embedded inside the horizontal frame plate (22). A slide (28) is slidably connected to the top surface of the horizontal frame plate (22), and a limiting frame (29) is embedded inside the slide (28). A positioning pulley (30) is installed inside the limiting frame (29). The traction rope (26) passes through the inside of the transmission roller (23) and is embedded inside the limiting frame (29).

3. The experimental testing device for deploying multi-fold sails for spacecraft according to claim 2, characterized in that: The traction rope (26) is embedded between the limiting frame (29) and the positioning pulley (30), and one side wall of the traction rope (26) is attached to the surface of the positioning pulley (30).

4. The experimental testing device for deploying multi-fold sails for spacecraft according to claim 1, characterized in that: The satellite body (16) is horizontally slidably connected to the mounting frame (31), and one side of the bottom surface of the satellite body (16) is located on the top surface of the support frame (32) and slides on the surface of the support frame (32).

5. The experimental testing device for deploying multi-fold sails for spacecraft according to claim 1, characterized in that: The support frame (32) has an opening in the middle, and the engagement push belt (35) is embedded in the opening and located directly below the push tooth (34).

6. The experimental testing device for deploying multi-fold sails for spacecraft according to claim 1, characterized in that: The adjustment experimental component (4) includes a positioning strip (41). The positioning strip (41) is installed on the inner wall of the experimental frame (11). The positioning strip (41) has a positioning groove (43) inside. A positioning rod (42) is embedded in the positioning groove (43). One side of the positioning rod (42) is fixedly connected to the side wall of the mounting frame (31). The positioning rod (42) slides inside the positioning groove (43).

7. The experimental testing device for deploying multi-fold sails for spacecraft according to claim 6, characterized in that: The positioning strip (41) is set in an arc shape, and the center of the arc of the positioning strip (41) is consistent with the deflection center of the mounting bracket (31).

8. The experimental testing device for deploying multi-fold sails for spacecraft according to claim 7, characterized in that: A motor assembly (44) is fixedly connected to the inner wall of the experimental frame (11). The output end of the motor assembly (44) is connected to a turntable (45). One side of the turntable (45) is fixedly connected to the side wall of the mounting frame (31). The center of the turntable (45) is consistent with the center of the positioning strip (41).

9. The test method for a spacecraft multi-fold sail deployment experimental test device according to any one of claims 1-8, characterized in that: After the satellite body (16) is installed on the upper end of the support frame (32) and the traction rope (26) is connected to the sail body (15), the rotation of the transmission roller (23) after connection pulls the traction rope (26), which in turn drives the sail body (15) to unfold.

10. The testing method for a spacecraft multi-fold sail deployment experimental testing device according to claim 9, characterized in that: When the sail body (15) unfolds, the motor drives the engagement propulsion belt (35) to rotate. After rotating, it pushes the satellite body (16) forward. After moving to the top of the support frame (32), the motor drives the reverse rotation to push the satellite body (16) to move in the opposite direction.

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