Inflatable solar wing capable of being unfolded twice in two directions and using method thereof

Abstract

The invention provides a secondary two-way unfolding inflatable solar wing and a using method thereof, and belongs to the technical field of space product structure and mechanism design. The problem that an existing secondary two-way unfolding structure is complex is solved. The solar cell panel comprises two inflation frames, a fixed front plate, a fixed rear plate and a cell panel body, the two inflation frames are symmetrically installed between the fixed front plate and the fixed rear plate, each inflation frame comprises a plurality of inflation pipes communicated with one another, the inflation pipes comprise the longitudinal inflation pipes, the transverse inflation pipes and the auxiliary inflation pipes, and the longitudinal inflation pipes are communicated with the transverse inflation pipes. The side faces of the two ends of the longitudinal inflation tube are connected with transverse inflation tubes respectively, a plurality of auxiliary inflation tubes are connected between the two transverse inflation tubes, air pressure valves are arranged at the joints of the longitudinal inflation tube and the transverse inflation tubes, and a plurality of cell panel arrays are installed between the adjacent inflation tubes. The device is mainly used for secondary two-way unfolding of the solar wing.

Description

Technical Field

[0001] The present invention belongs to the technical field of space product structure and mechanism design, and in particular relates to a secondary bidirectionally unfoldable inflatable solar wing and a method of using the same. Background Art

[0002] In recent years, with the continuous increase in satellite power demand, the area of ​​solar panels has also been increasing. Among them, communication satellites and synthetic aperture radar satellites are the most prominent. The area of ​​solar panels is often several times or even dozens of times the area of ​​the satellite cabin. This feature has caused certain challenges to the folding, in-orbit deployment and in-orbit control of solar panels.

[0003] At present, the solar wings commonly used for high-power satellites are flexible deployable solar wings, which have the advantages of light weight and small folding envelope. However, they also have the disadvantages of complex deployment mechanism, low reliability, and high flexibility after deployment in orbit, which need to be further optimized. At the same time, traditional flexible solar wings often adopt a one-way deployment method. Limited by the size of the solar wing installation cabin, the non-deployment direction of the solar wing is short, while the deployment direction is extremely long. Long and narrow solar wings have many defects, including: First, the moment of inertia of the entire satellite is too large after the solar wing is deployed, and the torque requirements for the solar wing drive mechanism and flywheel are too large, and it may even be impossible to select; second, the long and narrow flexible solar wings are highly flexible, and the increase in length will reduce the stability of the entire satellite, making attitude control difficult; third, the longer the size of the solar wing, the longer the solar wing power line, the greater the power loss and the waste of weight resources of the entire satellite.

[0004] The solar wing adopts a two-way deployment method to effectively improve the above defects, that is, the solar wing not only deploys in the length direction, but also in the width direction, and is square after deployment, thereby effectively reducing the inertia and flexibility after deployment and shortening the power line length of the solar wing. However, using the traditional solar wing design concept, the two-way deployment is difficult to achieve, and the mechanism is too complicated, which will cause a large cost and waste of the weight resources of the entire satellite, and further reduce the reliability of the solar wing. Summary of the invention

[0005] In view of this, the present invention aims to provide a secondary bidirectional unfolding inflatable solar wing and a method of using the same, so as to solve the problem of the complex structure of the existing secondary bidirectional unfolding.

[0006] To achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a secondary bidirectionally unfolded inflatable solar wing, which includes an inflatable frame, a fixed front plate, a fixed rear plate and a solar panel, the number of the inflatable frames is two, and the two inflatable frames are symmetrically installed between the fixed front plate and the fixed rear plate, the inflatable frame includes a plurality of inflatable tubes that are interconnected, the inflatable tubes include a longitudinal inflatable tube, a transverse inflatable tube and an auxiliary inflatable tube, the two end sides of the longitudinal inflatable tube are respectively connected to the transverse inflatable tubes, and several auxiliary inflatable tubes are connected between the two transverse inflatable tubes, an air pressure valve is provided at the interface between the longitudinal inflatable tube and the transverse inflatable tube, an exhaust port is provided at the end of the transverse inflatable tube, an inflation port is provided on the fixed front plate, and the inflation port is connected to the longitudinal inflatable tube, the number of the solar panels is multiple, and a plurality of solar panel arrays are installed between adjacent inflatable tubes, and are spaced apart between adjacent solar panels in the longitudinal direction.

[0007] Furthermore, the air pressure valve includes a shell, a spring, an upper cover and a sealing ring. The bottom of the shell is connected to the longitudinal inflation tube, the sealing ring is covered on the top and outside of the shell, and the upper cover is connected to the bottom of the shell through a spring. In the initial state, the spring is in a stretched state, providing a pre-tightening force for the upper cover so that the upper cover is close to the sealing ring.

[0008] Furthermore, the solar panel includes a flexible substrate and a solar cell sheet, the solar cell sheet is mounted on the surface of the flexible substrate, and the flexible substrate is connected to the inflation tube and is spaced apart between adjacent flexible substrates in the longitudinal direction.

[0009] Furthermore, the inflatable tube is made of a flexible fiber composite material.

[0010] Furthermore, the inflatable solar wing is provided with a folding locking mechanism on the outside after being folded, and the folding locking mechanism is connected to the unlocking mechanism.

[0011] Furthermore, the folding and locking mechanism is a fixed rope, and the unlocking mechanism is a hot knife assembly. The fixed rope is wrapped around the outside of the folded inflatable solar wing, and the hot knife assembly is arranged on a fixed front plate, and the fixed rope passes through the cutting hole inside the hot knife assembly.

[0012] Furthermore, the upper and lower parts of the fixed rear plate are both provided with rope recovery mechanisms, and vortex springs are provided in the rope recovery mechanisms. The two ends of the fixed rope are respectively connected to the vortex springs in the upper and lower rope recovery mechanisms.

[0013] Furthermore, two fixed protrusions are provided on the fixed front plate and the fixed rear plate, the fixed protrusions are connected to the longitudinal inflation tube, and the inflation and exhaust ports are opened on the inner sides of the fixed protrusions.

[0014] Furthermore, the inflation and exhaust port is connected to the inflation and exhaust connecting pipe, and a connecting rod is provided on the fixed front plate, and the connecting rod is connected to the solar wing driving mechanism, the solar wing lifting mechanism or the satellite body.

[0015] The present invention also provides a method for using a secondary bidirectionally unfolded inflatable solar wing, the method comprising a folding process and an unfolding process; The folding process is as follows: use an air pump to evacuate the gas inside the inflatable frame through the exhaust port and the charging and exhaust port to make the inflatable tube in a flat state, then install the battery panel on the inflatable tube, then fold the inflatable frame horizontally according to the size of the battery panel, bend the horizontal inflatable tube, fold the battery panel horizontally, fold the inflatable frame longitudinally according to the size of the battery panel, bend the longitudinal inflatable tube and the auxiliary inflatable tube, fold the battery panel longitudinally, and the solar wing is folded; The unfolding process is as follows: inflate the longitudinal inflation tube through the inflation and exhaust port. Since the air pressure has not reached the air pressure valve threshold, the air pressure valve is in a closed state. At this time, under the action of the gas, the longitudinal inflation tube unfolds longitudinally from a flat folded state to a tubular straight state. After the longitudinal unfolding is completed, continue to inflate the longitudinal inflation tube. After the air pressure reaches the air pressure valve threshold, the air pressure valve opens, and the gas enters the transverse inflation tube. Under the action of the gas, the transverse inflation tube unfolds transversely from a flat folded state to a tubular straight state. While the transverse inflation tube unfolds, the gas enters the auxiliary inflation tube from the connected interface until all transverse inflation tubes and auxiliary inflation tubes are filled with gas and are in a tubular straight state, and the solar wing is fully unfolded.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows: the present invention provides a secondary bidirectionally unfolded inflatable solar wing and a method of using the same, so as to reduce the inertia and flexibility of a large-size solar wing after unfolding, reduce the difficulty of on-orbit control of the entire satellite and the configuration requirements of the controller, and at the same time simplify the entire unfolding method of the solar wing, thereby further improving the reliability of the solar wing.

[0017] The specific advantages are as follows: (1) The present invention uses an inflation method to achieve the deployment of the solar wing, and the mechanism design is simple and the reliability is high.

[0018] (2) The present invention adopts a bidirectional expansion method to expand the traditional long and narrow solar wing into a square solar wing, thereby reducing the rotational inertia of the entire satellite and lowering the torque requirements for the solar wing drive mechanism and flywheel.

[0019] (3) The present invention forms a mesh structure through longitudinal inflatable tubes, transverse inflatable tubes and auxiliary inflatable tubes, thereby improving the overall rigidity of the solar wing and reducing the difficulty of attitude control of the entire satellite.

[0020] (4) The present invention adopts a bidirectional unfolding method to expand the traditional long and narrow solar wing into a square solar wing, thereby shortening the overall power line length, reducing the power loss caused by the power line length and the waste of weight resources of the entire satellite.

[0021] (5) The present invention adopts a two-step deployment method to avoid hooking or friction damage to components caused by simultaneous deployment in both directions.

[0022] (6) The present invention uses a hot knife to melt the fixing rope to unlock the solar wing, which has low cost and small release impact, and has little impact on the satellite and on-board equipment.

[0023] (7) The components of the present invention are simple in design and have low precision requirements, which can reduce processing costs and shorten processing cycles. All parts can be reused, which reduces the cost of ground tests. Hot knife unlocking is used to reduce the requirements for ground test manufacturers. Each part is independent of each other and can be redesigned / selected according to the specific needs of the satellite, and the device has strong adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings: Figure 1 This is a schematic diagram of the structure of a secondary bidirectionally deployed inflatable solar wing according to the present invention; Figure 2 This is a schematic diagram of the inflatable frame structure of the present invention; Figure 3 It is a schematic diagram of the cross-sectional structure of the connection portion between the longitudinal inflation tube and the transverse inflation tube according to the present invention; Figure 4 It is a schematic diagram of the cross-sectional structure of the air pressure valve according to the present invention; Figure 5 This is a schematic diagram of the structure of the connection portion between the transverse inflation tube and the auxiliary inflation tube according to the present invention; Figure 6 This is a schematic diagram of the fixed front plate connection structure of the present invention; Figure 7 This is a schematic diagram of the front structure of the fixed front plate of the present invention; Figure 8 This is a schematic diagram of the back structure of the fixed front plate according to the present invention; Fig. 9 This is a schematic diagram of the fixed rear plate connection structure of the present invention; Fig.10 This is a schematic diagram of the front structure of the fixed rear plate of the present invention; Fig.11 This is a schematic diagram of the back structure of the fixed rear plate of the present invention; Fig.12 A schematic diagram of the assembly process of a secondary bidirectionally deployed inflatable solar wing according to the present invention Figure 1 ; Fig.13 A schematic diagram of the assembly process of a secondary bidirectionally deployed inflatable solar wing according to the present invention Figure 2 ; Fig.14 A schematic diagram of the assembly process of a secondary bidirectionally deployed inflatable solar wing according to the present invention Figure 3 ; Fig.15 The schematic diagram of the folding process of the inflatable solar wing with two-way deployment described in the present invention is as follows Figure 1 ; Fig.16 The schematic diagram of the folding process of the inflatable solar wing with two-way deployment described in the present invention is as follows Figure 2 ; Fig.17 The schematic diagram of the folding process of the inflatable solar wing with two-way deployment described in the present invention is as follows Figure 3 ; Fig.18 The schematic diagram of the folding process of the inflatable solar wing with two-way deployment described in the present invention is as follows Figure 4 ; Fig.19 A schematic diagram of the locked state of a secondary bidirectionally deployed inflatable solar wing according to the present invention Figure 1 ; Fig. 20 A schematic diagram of the locked state of a secondary bidirectionally deployed inflatable solar wing according to the present invention Figure 2 ; Fig.21 It is a longitudinal schematic diagram of a secondary bidirectionally unfolded inflatable solar wing according to the present invention; Fig. 22 It is a horizontal schematic diagram of a secondary bidirectionally unfolded inflatable solar wing according to the present invention.

[0025] In the figure: 1-inflatable frame, 2-fixed front plate, 3-fixed rear plate, 4-flexible substrate, 5-solar cell sheet, 6-longitudinal inflatable tube, 7-lateral inflatable tube, 8-auxiliary inflatable tube, 9-exhaust port, 10-air pressure valve, 11-housing, 12-spring, 13-upper cover, 14-sealing ring, 15-connecting rod, 16-inflatable and exhaust port, 17-fixed protrusion, 18-hot knife assembly, 19-inflatable and exhaust connecting tube, 20-rope recovery mechanism, 21-fixed rope. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely explain the technical solutions in the embodiments of the present invention. It should be noted that the embodiments of the present invention and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only part of the embodiments of the present invention, not all of the embodiments.

[0027] See also Figure 1-22 The present embodiment is described as a secondary bidirectionally unfolded inflatable solar wing, which comprises an inflatable frame 1, a fixed front plate 2, a fixed rear plate 3 and a solar panel. The number of the inflatable frames 1 is two, and the two inflatable frames 1 are symmetrically installed between the fixed front plate 2 and the fixed rear plate 3. The inflatable frame 1 comprises a plurality of inflatable tubes that are interconnected, and the inflatable tubes comprise a longitudinal inflatable tube 6, a transverse inflatable tube 7 and an auxiliary inflatable tube 8. The side surfaces of both ends of the longitudinal inflatable tube 6 are respectively connected to the transverse inflatable tube 7, and a plurality of auxiliary inflatable tubes 8 are connected between the two transverse inflatable tubes 7. An air pressure valve 10 is provided at the interface between the longitudinal inflatable tube 6 and the transverse inflatable tube 7, and an exhaust port 9 is provided at the end of the transverse inflatable tube 7. The fixed front plate 2 is provided with an inflatable and exhaust port 16, and the inflatable and exhaust port 16 is connected to the longitudinal inflatable tube 6. The number of the solar panels is multiple, and a plurality of solar panel arrays are installed between adjacent inflatable tubes, and are spaced apart between adjacent solar panels in the longitudinal direction.

[0028] The folding process of this embodiment is as follows: use an air pump to evacuate the gas inside the inflatable frame 1 through the exhaust port 9 and the charging and exhaust port 16, so that the inflatable tube is in a flat state, and then install the battery panel on the inflatable tube, and then fold the inflatable frame 1 in the horizontal direction according to the size of the battery panel, bend the horizontal inflatable tube 7, and fold the battery panel in the horizontal direction, and fold the inflatable frame 1 in the longitudinal direction according to the size of the battery panel, bend the longitudinal inflatable tube 6 and the auxiliary inflatable tube 8, and fold the battery panel in the longitudinal direction, and the solar wing is folded; The unfolding process is as follows: inflate the longitudinal inflation tube 6 through the inflation and exhaust port 16. Since the air pressure has not reached the threshold of the air pressure valve 10, the air pressure valve 10 is in a closed state. At this time, under the action of the gas, the longitudinal inflation tube 6 is longitudinally unfolded from a flat folded state to a tubular straight state. After the longitudinal unfolding is completed, continue to inflate the longitudinal inflation tube 6. After the air pressure reaches the threshold of the air pressure valve 10, the air pressure valve 10 opens, and the gas enters the transverse inflation tube 7. Under the action of the gas, the transverse inflation tube 7 is transversely unfolded from a flat folded state to a tubular straight state. While the transverse inflation tube 7 is unfolding, the gas enters the auxiliary inflation tube 8 from the connected interface until all the transverse inflation tubes 7 and the auxiliary inflation tubes 8 are filled with gas and are in a tubular straight state, and the solar wing is unfolded.

[0029] The present embodiment will be described in detail below with reference to the accompanying drawings: like Figure 1As shown, a secondary bidirectionally unfolded inflatable solar wing comprises an inflatable frame 1, a fixed front plate 2, a fixed rear plate 3 and a solar panel. The number of the inflatable frames 1 is two, and the two inflatable frames 1 are symmetrically installed between the fixed front plate 2 and the fixed rear plate 3. The number of the solar panels is multiple, and multiple solar panel arrays are installed between adjacent inflatable tubes. The solar panel comprises a flexible substrate 4 and a solar cell sheet 5. The solar cell sheet 5 is installed on the surface of the flexible substrate 4. The flexible substrate 4 is connected to the inflatable tube and is spaced apart between adjacent flexible substrates 4 in the longitudinal direction.

[0030] like Figure 2 As shown, the inflatable frame 1 includes a plurality of interconnected inflatable tubes, the inflatable tubes including a longitudinal inflatable tube 6, a transverse inflatable tube 7 and an auxiliary inflatable tube 8. The two end sides of the longitudinal inflatable tube 6 are respectively connected with the transverse inflatable tube 7, and a plurality of auxiliary inflatable tubes 8 are connected between the two transverse inflatable tubes 7. The inflatable tube is made of a flexible fiber composite material, and the material is preferably a polyimide film with added reinforcing fibers, and its characteristics are: it can be flattened and flexibly folded before being inflated, and it is tubular and has a certain rigidity after being inflated and unfolded, and the longitudinal inflatable tube 6 has a larger outer diameter and a thicker tube wall, and has a higher ability to resist air pressure.

[0031] like Figure 3 As shown, the connection between the longitudinal inflatable tube 6 and the transverse inflatable tube 7 is sealed by pasting with a flexible wrapping tape, and an air pressure valve 10 is provided at the two interfaces between the longitudinal inflatable tube 6 and the transverse inflatable tube 7. The air pressure valve 10 has a set air pressure threshold. When the air pressure in the longitudinal inflatable tube 6 does not reach the set air pressure threshold, the air pressure valve 10 is in a closed state, and when the air pressure in the longitudinal inflatable tube 6 reaches the set air pressure threshold, the air pressure valve 10 is in an open state.

[0032] like Figure 4 As shown, the air pressure valve 10 includes a housing 11, a spring 12, an upper cover 13 and a sealing ring 14. The bottom of the housing 11 is connected to the longitudinal air-filling tube 6. The sealing ring 14 is covered on the top and outside of the housing 11. The upper cover 13 is connected to the bottom of the housing 11 through the spring 12. In the initial state, the spring 12 is in a stretched state, providing a pre-tightening force for the upper cover 13, so that the upper cover 13 is close to the sealing ring 14 to achieve a sealing effect. Before the air pressure in the longitudinal air-filling tube 6 reaches the set air pressure threshold of the air pressure valve 10, the air pressure valve 10 is in a closed state, and the gas is only filled into the longitudinal air-filling tube 6; when the air pressure in the longitudinal air-filling tube 6 reaches the set air pressure threshold of the air pressure valve 10, the gas in the longitudinal air-filling tube 6 pushes the upper cover 13 to lift, the air pressure valve 10 is in an open state, and the gas is filled from the longitudinal air-filling tube 6 into the transverse air-filling tube 7.

[0033] like Figure 5As shown, the connection between the transverse inflatable tube 7 and the auxiliary inflatable tube 8 is sealed by gluing with a flexible tape, and the interfaces are all connected, so that the gas can flow freely. An exhaust port 9 is provided at the end of the transverse inflatable tube 7. Before the solar wing is folded, an air pump can be used to extract the gas in the transverse inflatable tube 7 and the auxiliary inflatable tube 8 through the exhaust port 9, so as to facilitate the folding of the inflatable tube. During the ground test stage, after the air is pumped out, the exhaust port 9 is blocked by a plug for subsequent ground deployment tests; when the solar wing is folded for the last time in the launch state, after the air is pumped out, the exhaust port 9 is cut short and sealed by gluing with a flexible tape.

[0034] like Figure 6-8 As shown, the fixed front plate 2 is provided with an air-inflating and exhausting port 16, which is communicated with the longitudinal air-inflating tube 6, and the air-inflating and exhausting port 16 is connected to the air-inflating and exhausting connecting tube 19. The fixed front plate 2 is provided with two fixed protrusions 17, which are connected with the longitudinal air-inflating tube 6. The air-inflating and exhausting port 16 is opened inside the fixed protrusions 17, and the longitudinal air-inflating tube 6 is sealed by being sleeved on the outside of the fixed protrusions 17 and pasted with a flexible wrapping tape. The fixed front plate 2 is provided with a connecting rod 15, which is connected to the solar wing driving mechanism, the solar wing lifting mechanism or the satellite body.

[0035] like Figure 9-11 As shown, two fixing protrusions 17 are provided on the fixed rear plate 3, and the fixing protrusions 17 are connected to the longitudinal air-filling tube 6. The longitudinal air-filling tube 6 is sealed by being sleeved on the outside of the fixing protrusions 17 and pasted with a flexible wrapping tape.

[0036] The inflatable solar wing described in the above embodiment is provided with a folding locking mechanism on the outside after being folded, and the folding locking mechanism is connected to an unlocking mechanism. The folding locking mechanism is used to lock the inflatable solar wing after folding, and the unlocking mechanism is used to release the folding locking mechanism from locking the inflatable solar wing before the inflatable solar wing is unfolded.

[0037] like Figure 6-11As shown, the folding and locking mechanism is a fixing rope 21, and the unlocking mechanism is a hot knife assembly 18. The fixing rope 21 is wound around the outside of the folded inflatable solar wing, and the fixing rope 21 locks the inflatable solar wing. The fixing rope 21 is cut by the hot knife assembly 18, and the inflatable solar wing loses the restraint of the fixing rope 21, and the unlocking is completed. The fixed front plate 2 is provided with four hot knife interfaces, and each hot knife interface is provided with a hot knife assembly 18. The upper and lower parts of the fixed rear plate 3 are provided with eight recovery mechanism interfaces, and each hot knife interface is provided with a rope recovery mechanism 20. The rope recovery mechanisms 20 are arranged in groups of two, corresponding to the positions of the four hot knife assemblies 18, respectively. The rope recovery mechanism 20 is provided with a vortex spring, and the fixing rope 21 passes through the cutting hole inside the hot knife assembly 18. The two ends of the fixing rope 21 are respectively connected to the vortex springs in the upper and lower rope recovery mechanisms 20. After the fixing rope 21 is melted, it is recovered to the inside of the rope recovery mechanism 20 under the action of the vortex spring.

[0038] This embodiment specifically describes the process of assembling, folding and locking the inflatable solar wing.

[0039] According to the inflatable solar wing structure described in the above embodiment, the inflatable frame 1, the fixed front plate 2 and the fixed rear plate 3 are installed. Figure 2 , Figure 6 , Fig. 9 shown.

[0040] Two inflatable frames 1 are symmetrically mounted between the fixed front plate 2 and the fixed rear plate 3, and the gas inside the inflatable frames 1 is evacuated through the exhaust port 9 and the inflation / exhaust port 16 using an air pump, so that the inflation tube is in a flat state. Fig.12 shown.

[0041] The solar cell sheet 5 is pasted on the surface of the flexible substrate 4, and the surface wiring of the flexible substrate 4 is completed to form a solar panel, such as Fig.13 shown.

[0042] The solar panels are attached between adjacent inflatable tubes of the inflatable frame 1 by means of flexible wrapping tape. Fig.14 As shown, sufficient gaps are reserved between adjacent flexible substrates 4 in the longitudinal direction to provide bending space for folding, thereby avoiding damage to the solar cell sheet 5 due to folding.

[0043] like Fig.15 As shown, the solar wings on both sides are folded horizontally and folded at the top and bottom respectively. The inflatable frame 1 is folded horizontally according to the size of the solar panel, so that the horizontal inflatable tube 7 is bent, and the solar panel is folded horizontally. After folding, the solar wings are as shown in FIG. Fig.16 shown.

[0044] like Fig.17As shown, the solar wing is folded and stowed longitudinally. The inflatable frame 1 is folded longitudinally according to the size of the solar panel, so that the longitudinal inflatable tube 6 and the auxiliary inflatable tube 8 are bent, and the solar panel is folded longitudinally. After the folding is completed, the solar wing is as shown in FIG. Fig.18 shown.

[0045] like Fig.19 As shown, a fixing rope 21 is used to pass through the cutting hole inside the hot knife assembly 18, pass through the top and bottom of the folded solar wing, and then be fixed to the vortex spring of the rope recovery mechanism 20, as shown in FIG. Fig. 20 As shown. At this time, the vortex spring is in a stretched state and has a large retracting pulling force. After all the fixing ropes 21 are connected, the solar wing is in a folded and locked state.

[0046] This embodiment specifically describes the unlocking and unfolding process of the inflatable solar wing.

[0047] The hot knife assembly 18 is energized, and the hot knife assembly 18 melts the fixing rope 21. Under the action of the vortex spring, the fixing rope 21 is recovered from the upper and lower sides of the folded solar wing and enters the rope recovery mechanism 20, and the solar wing is unlocked.

[0048] The inflation / exhaust connection pipe 19 inflates the longitudinal inflation pipe 6 through the inflation / exhaust port 16, and the longitudinal inflation pipe 6 is expanded longitudinally from a flat folded state to a tubular straight state under the action of the gas. Fig.21 As shown, at this time, since the air pressure in the longitudinal inflation tube 6 has not reached the threshold of the air pressure valve 10, the air pressure valve 10 is in a closed state, and the gas will not enter the transverse inflation tube 7 and the auxiliary inflation tube 8. Therefore, the solar wing is only unfolded longitudinally, thereby avoiding hooking or friction damage to components caused by simultaneous bidirectional unfolding.

[0049] After the longitudinal expansion is completed, the inflation and exhaust connection pipe 19 continues to inflate the longitudinal inflation tube 6 through the inflation and exhaust port 16. After the air pressure reaches the threshold of the air pressure valve 10, the air pressure valve 10 opens and the gas enters the transverse inflation tube 7. Under the action of the gas, the transverse inflation tube 7 expands horizontally from a flat folded state to a tubular straight state. While the transverse inflation tube 7 is expanding, the gas enters the auxiliary inflation tube 8 from the connected interface until all the transverse inflation tubes 7 and the auxiliary inflation tubes 8 are filled with gas and are in a tubular straight state, and the solar wing is fully expanded. Fig. 22 shown.

[0050] In the above embodiment, after the solar wing is inflated and unfolded, all the inflation tubes are tubular and have a certain rigidity. The longitudinal inflation tubes 6, the transverse inflation tubes 7 and the auxiliary inflation tubes 8 are combined to form a network to further enhance the rigidity of the solar wing as a whole, thereby reducing the difficulty of controlling the attitude of the entire satellite. After being unfolded in orbit, the inflatable frame 1 can achieve the locking effect of the entire solar wing under the maintenance of the filled gas.

[0051] The embodiments of the present invention disclosed above are only used to help illustrate the present invention. The embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods described. According to the content of this specification, many modifications and changes can be made. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well.

Claims

1. A secondary bidirectionally deployable inflatable solar wing, characterized in that: It comprises an inflatable frame (1), a fixed front plate (2), a fixed rear plate (3) and a battery plate. The inflatable frame (1) is two in number and the two inflatable frames (1) are symmetrically installed between the fixed front plate (2) and the fixed rear plate (3). The inflatable frame (1) comprises a plurality of inflatable pipes that are interconnected. The inflatable pipes comprise a longitudinal inflatable pipe (6), a transverse inflatable pipe (7) and an auxiliary inflatable pipe (8). The two end sides of the longitudinal inflatable pipe (6) are respectively connected to the transverse inflatable pipe (7). The two transverse inflatable pipes (7) are connected to the auxiliary inflatable pipe (8). A plurality of auxiliary inflatable tubes (8) are connected between the inflatable tubes (7); an air pressure valve (10) is provided at the interface between the longitudinal inflatable tube (6) and the transverse inflatable tube (7); an exhaust port (9) is provided at the end of the transverse inflatable tube (7); an inflatable and exhaust port (16) is provided on the fixed front plate (2); the inflatable and exhaust port (16) is communicated with the longitudinal inflatable tube (6); a plurality of battery panels are provided, and a plurality of battery panel arrays are installed between adjacent inflatable tubes, and adjacent battery panels are arranged at intervals in the longitudinal direction.

2. The inflatable solar wing capable of secondary bidirectional deployment according to claim 1, characterized in that: The air pressure valve (10) comprises a shell (11), a spring (12), an upper cover (13) and a sealing ring (14); the bottom of the shell (11) is connected to the longitudinal inflation tube (6); the sealing ring (14) covers the top and the outer side of the shell (11); the upper cover (13) is connected to the bottom of the shell (11) via the spring (12); in an initial state, the spring (12) is in a stretched state, providing a pre-tightening force for the upper cover (13), so that the upper cover (13) is tightly attached to the sealing ring (14).

3. The inflatable solar wing capable of secondary bidirectional deployment according to claim 1, characterized in that: The solar panel comprises a flexible substrate (4) and a solar cell sheet (5), wherein the solar cell sheet (5) is mounted on the surface of the flexible substrate (4), and the flexible substrate (4) is connected to an inflation tube and is spaced apart between adjacent flexible substrates (4) in the longitudinal direction.

4. The secondary bidirectionally deployable inflatable solar wing according to claim 1, characterized in that: The inflatable tube is made of a flexible fiber composite material.

5. The secondary bidirectionally deployable inflatable solar wing according to claim 1, characterized in that: The inflatable solar wing is provided with a folding locking mechanism on the outside after being folded, and the folding locking mechanism is connected to the unlocking mechanism.

6. The secondary bidirectionally deployable inflatable solar wing according to claim 5, characterized in that: The folding and locking mechanism is a fixing rope (21), and the unlocking mechanism is a hot knife assembly (18). The fixing rope (21) is wound around the outside of the folded inflatable solar wing. The hot knife assembly (18) is arranged on the fixed front plate (2), and the fixing rope (21) passes through the internal cutting hole of the hot knife assembly (18).

7. The secondary bidirectionally deployable inflatable solar wing according to claim 6, characterized in that: The upper and lower parts of the fixed rear plate (3) are both provided with a rope recovery mechanism (20), a vortex spring is provided in the rope recovery mechanism (20), and the two ends of the fixed rope (21) are respectively connected to the vortex springs in the upper and lower rope recovery mechanisms (20).

8. The secondary bidirectionally deployable inflatable solar wing according to claim 1, characterized in that: The fixed front plate (2) and the fixed rear plate (3) are both provided with two fixed protrusions (17), the fixed protrusions (17) are connected to the longitudinal inflation tube (6), and the inflation and exhaust ports (16) are opened on the inner sides of the fixed protrusions (17).

9. The secondary bidirectionally deployable inflatable solar wing according to claim 1, characterized in that: The charging and discharging port (16) is connected to the charging and discharging connecting pipe (19); a connecting rod (15) is provided on the fixed front plate (2); and the connecting rod (15) is connected to a solar wing driving mechanism, a solar wing lifting mechanism or a satellite body.

10. A method for using the secondary bidirectionally deployable inflatable solar wing as claimed in claim 1, characterized in that: The method of use includes a folding process and an unfolding process; The folding process is as follows: using an air pump to evacuate the gas inside the inflatable frame (1) through the exhaust port (9) and the charging and exhaust port (16), so that the inflatable tube is in a flat state, and then the battery panel is installed on the inflatable tube. Thereafter, the inflatable frame (1) is folded in the horizontal direction according to the size of the battery panel, so that the horizontal inflatable tube (7) is bent, and the battery panel is folded in the horizontal direction. The inflatable frame (1) is folded in the longitudinal direction according to the size of the battery panel, so that the longitudinal inflatable tube (6) and the auxiliary inflatable tube (8) are bent, and the battery panel is folded in the longitudinal direction, and the solar wing is folded. The unfolding process is as follows: air is inflated into the longitudinal inflatable tube (6) through the inflating and exhausting ports (16). Since the air pressure does not reach the threshold of the air pressure valve (10), the air pressure valve (10) is in a closed state. At this time, under the action of the gas, the longitudinal inflatable tube (6) is unfolded longitudinally from a flat folded state to a tubular straight state. After the longitudinal unfolding is completed, air is continuously inflated into the longitudinal inflatable tube (6). After the air pressure reaches the threshold of the air pressure valve (10), the air pressure valve (10) opens, and the gas enters the transverse inflatable tube (7). Under the action of the gas, the transverse inflatable tube (7) is unfolded transversely from a flat folded state to a tubular straight state. While the transverse inflatable tube (7) is unfolded, the gas enters the auxiliary inflatable tube (8) from the connected interface until all the transverse inflatable tubes (7) and the auxiliary inflatable tubes (8) are filled with gas and are in a tubular straight state, and the solar wing is unfolded.

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