Solar panel unfolding structure of long-endurance aerostat and aerostat

Abstract

The invention relates to the technical field of aerostat equipment, and provides a long-endurance aerostat solar panel unfolding structure and an aerostat, the long-endurance aerostat solar panel unfolding structure comprises a pod body, an unfolding mechanism, a first solar panel, a second solar panel and a third solar panel, and the three solar panels are all connected with the unfolding mechanism; the unfolding mechanism comprises a linear driving device and an execution unit, the execution unit comprises a driving connecting rod, a parallelogram connecting rod assembly and a rising connecting rod, the first solar panel and the second solar panel are both hinged to the pod body, and one end of the rising connecting rod is hinged to the third solar panel; one end of the driving connecting rod is hinged to the linear driving device, and the other end of the driving connecting rod is hinged to the parallelogram connecting rod assembly. In the launching and lift-off process, the solar panel is in a contraction state, the collision risk is reduced, the lift-off additional resistance is reduced, and the structural safety is higher.

Description

Technical Field

[0001] The present invention relates to the technical field of aerostat equipment, and particularly to a long-endurance aerostat solar panel deployment structure and an aerostat. Background Art

[0002] A long-endurance aerostat is an aircraft that uses the principle of buoyancy-weight balance to stay in the air for a long time to complete a given task. Typical long-endurance aerostats include airships, high-altitude balloons, and superpressure balloons. During the long-endurance flight, the energy system of the aerostat needs to achieve energy balance to ensure that each device receives sufficient energy supply to maintain normal operation. Currently, in the energy system solutions of long-endurance aerostats, a technical solution of energy storage battery + solar cell is adopted. During the flight period with sunlight, the solar cell converts light energy into electrical energy to supply each system, and the excess electrical energy is stored in the energy storage battery; during the flight period without sunlight, the energy storage battery directly powers each system, and this cycle repeats. Solar cells are of great significance for the long-term flight of aerostats, especially for cross-day-and-night flights. However, the solar cell body is often relatively fragile. To prevent damage or failure of the solar cell structure, a solar panel is actually used to protect its structure.

[0003] In the related technical solutions, the solar panels used in long-endurance aerostats are installed on the outer side wall of the gondola in a fixed structure form. The plane of the panel is perpendicular to the side wall of the gondola, and the solar panel array faces directly upward to obtain sunlight. During the entire test process of the aerostat taking off from the ground, ascending, flying horizontally, descending, and landing, its external structure remains unchanged. This technical solution has the following deficiencies during the flight test of long-endurance aerostats: First, during the ground release process of the aerostat, a technical solution of using a release vehicle to hang and release is adopted. The extended solar panels expand the envelope range of the flight system, increasing the risk of collision with the lifting arm of the release vehicle during the initial stage of release and ascent, and there are potential safety hazards; Second, during the ascent process, the horizontally installed solar panels become a resistance surface, which not only adds additional ascent resistance to the aerostat system, but also the resistance directly acts on the body structure of the solar panels, and there is a risk of structural damage; Third, during the landing process of the aerostat, the gondola will randomly overturn after landing, and the deployed solar panels will be structurally damaged after overturning and cannot be reused. Summary of the Invention

[0004] The present invention provides a long-endurance aerostat solar panel deployment structure and an aerostat, aiming to solve the defects in the prior art that fixed solar panels bring resistance to the ascent and descent of aerostats, and the fixed solar panels are prone to being damaged during the landing process.

[0005] In a first aspect of the present invention, a solar panel deployment structure for a long-endurance aerostat is provided, comprising: a gondola body, a deployment mechanism, a first solar panel, a second solar panel, and a third solar panel. The deployment mechanism is provided on the gondola body, and the first solar panel, the second solar panel, and the third solar panel are all connected to the deployment mechanism. The deployment mechanism includes a linear drive device and actuator units arranged on both sides of the linear drive device. The actuator units on both sides are hinged to the linear drive device, and the actuator unit on one side is hinged to the first solar panel, and the actuator unit on the other side is hinged to the second solar panel. The actuator units on both sides are hinged to the third solar panel. Wherein, the actuator unit includes a drive link, a parallelogram link assembly, and a rising link. The first solar panel and the second solar panel are both hinged to the gondola body through the parallelogram link assembly. One end of the rising link is hinged to the third solar panel, and the other end of the rising link is hinged to the parallelogram link assembly. One end of the drive link is hinged to the linear drive device, and the other end of the drive link is hinged to the parallelogram link assembly. An arc-shaped sliding groove is formed on the gondola body, and the hinge point between the drive link and the parallelogram link assembly is located in the sliding groove. The linear drive device is configured to drive the actuator units on both sides to act simultaneously, so that the first solar panel, the second solar panel, and the third solar panel are in the same plane when in the deployed position.

[0006] According to the solar panel deployment structure for a long-endurance aerostat provided by the present invention, the areas of the first solar panel and the second solar panel are both smaller than the area of the third solar panel.

[0007] According to the solar panel deployment structure for a long-endurance aerostat provided by the present invention, the first solar panel, the second solar panel, and the third solar panel are all rectangular plate structures, and the first solar panel and the second solar panel are located above the third solar panel and can cover the third solar panel when in the folded position.

[0008] According to the solar panel deployment structure for a long-endurance aerostat provided by the present invention, the parallelogram link assembly includes a first link and a second link. The first link and the second link are arranged in parallel. One end of the first link is hinged to the first solar panel or the second solar panel, and the other end of the first link is hinged to the gondola body. One end of the second link is hinged to the first solar panel or the second solar panel, and the other end of the second link is hinged to the gondola body. The drive link and the rising link are both hinged to the rod body of the first link.

[0009] According to the long-endurance aerostat solar panel deployment structure provided by the present invention, the rod body of the first connecting rod is provided with a hinge portion, and both the driving connecting rod and the rising connecting rod are hinged to the hinge portion.

[0010] According to the long-endurance aerostat solar panel deployment structure provided by the present invention, the rising connecting rod is located inside the pod body, and the driving connecting rod and the parallelogram connecting rod assembly are located outside the pod body.

[0011] According to the long-endurance aerostat solar panel deployment structure provided by the present invention, the pod body includes a box body and a connecting frame, the connecting frame is connected to the box body, and a connecting end for connecting the airbag is provided at the top of the connecting frame.

[0012] According to the long-endurance aerostat solar panel deployment structure provided by the present invention, the deployment mechanisms are provided on both opposite side plates of the box body.

[0013] According to the long-endurance aerostat solar panel deployment structure provided by the present invention, the linear driving device includes a linear motor, and the output end of the linear motor is hinged to the driving connecting rod.

[0014] In a second aspect of the present invention, an aerostat includes: a floating airbag; the long-endurance aerostat solar panel deployment structure as described in any one of the above, and the floating airbag is connected to the pod body.

[0015] The present invention provides a long-endurance aerostat solar panel deployment structure and an aerostat. During the ground release and liftoff process of the aerostat, the solar panels are in a contracted state, causing the first solar panel and the second solar panel to fold up, reducing the risk of collision with the lifting arm of the release vehicle during the release process, decreasing the additional resistance during liftoff, and protecting the safety of the structure of the solar panel body; after reaching the predetermined altitude and entering the level flight state, the execution unit and the linear driving device are used in cooperation to drive the solar panels to deploy from the contracted state to normal operation, providing cyclic energy for the aerostat system. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0017] Figure 1 It is an overall structural schematic diagram of the long-endurance aerostat solar panel deployment structure provided by the present invention in the folded state.

[0018] Figure 2It is a front view structural schematic diagram of the solar panel deployment structure of the long-endurance aerostat provided by the present invention in the folded state.

[0019] Figure 3 It is an overall structural schematic diagram of the solar panel deployment structure of the long-endurance aerostat provided by the present invention in the deployed state.

[0020] Figure 4 It is a front view structural schematic diagram of the solar panel deployment structure of the long-endurance aerostat provided by the present invention in the deployed state.

[0021] Figure 5 It is an overall structural schematic diagram of the aerostat in different stages provided by the present invention.

[0022] Reference numerals: 1. Pod body; 11. Box body; 12. Connecting frame; 13. Connecting end; 2. First solar panel; 3. Second solar panel; 4. Third solar panel; 5. Deployment mechanism; 51. Linear driving device; 52. Execution unit; 521. Driving link; 522. First link; 523. Second link; 524. Sliding groove; 525. Rising link. Specific embodiments

[0023] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the present invention. Apparently, the described embodiments are some but not all of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present invention without making creative efforts fall within the scope of protection of the present invention.

[0024] In the description of the embodiments of the present invention, it should be noted that the orientation or positional relationships indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are based on the orientation or positional relationships shown in the drawings, and are only for the convenience of clarifying the embodiments of the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be construed as a limitation on the embodiments of the present invention. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0025] In the description of the embodiments of the present invention, it should be noted that, unless otherwise clearly defined and limited, the terms "connected" and "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present invention can be understood according to specific circumstances.

[0026] In the embodiments of the present invention, unless otherwise clearly defined and limited, the first feature being "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may be that the first feature is directly above or obliquely above the second feature, or merely means that the first feature has a higher horizontal height than the second feature. The first feature being "under", "below" and "beneath" the second feature may be that the first feature is directly below or obliquely below the second feature, or merely means that the first feature has a lower horizontal height than the second feature.

[0027] In the description of this specification, the descriptions with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the embodiments of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0028] The following is combined with Figures 1-4Describe a long-endurance aerostat solar panel deployment structure of the present invention, which includes a gondola body 1, a deployment mechanism 5, a first solar panel 2, a second solar panel 3, and a third solar panel 4. The deployment mechanism 5 is arranged on the gondola body 1, and the first solar panel 2, the second solar panel 3, and the third solar panel 4 are all connected to the deployment mechanism 5. The deployment mechanism 5 includes a linear drive device 51 and actuator units 52 arranged on both sides of the linear drive device 51. The actuator units 52 on both sides are hinged to the linear drive device 51, and the actuator unit 52 on one side is hinged to the first solar panel 2, and the actuator unit 52 on the other side is hinged to the second solar panel 3. The actuator units 52 on both sides are both hinged to the third solar panel 4. Among them, the actuator unit 52 includes a drive link 521, a parallelogram link assembly, and a lifting link 525. The first solar panel 2 and the second solar panel 3 are both hinged to the gondola body 1 through the parallelogram link assembly. One end of the lifting link 525 is hinged to the third solar panel 4, and the other end of the lifting link 525 is hinged to the parallelogram link assembly. One end of the drive link 521 is hinged to the linear drive device 51, and the other end of the drive link 521 is hinged to the parallelogram link assembly. An arc-shaped sliding groove 524 is formed on the gondola body 1, and the hinge point of the drive link 521 and the parallelogram link assembly is located in the sliding groove 524. The linear drive device 51 is used to drive the actuator units 52 on both sides to act simultaneously, so that the first solar panel 2, the second solar panel 3, and the third solar panel 4 are in the same plane when in the deployed position. A long-endurance aerostat needs to be powered by solar panels to maintain long-term navigation. In this embodiment, through the setting of the deployment mechanism 5, the first solar panel 2, the second solar panel 3, and the third solar panel 4 can be deployed when needed, and the linkage operation of the three solar panels is realized by a single linear drive device 51, shortening the deployment response time, and enabling the three solar panels to be in the same plane, increasing the contact area with sunlight, and improving the utilization rate of solar energy.

[0029] Specifically, the gondola body 1 is a gondola structure in conventional technology. By arranging the deployment mechanism 5 on the gondola body 1, it can provide electrical energy for the aerostat after it operates stably, so as to meet the needs of long-term navigation. The deployment mechanism 5 is connected to the three solar panels, so that the deployment mechanism 5 can simultaneously realize the deployment and folding of the three solar panels, improving its response speed.

[0030] Among them, the surfaces of the first solar panel 2, the second solar panel 3, and the third solar panel 4 are provided with solar panels for converting solar energy into electrical energy. The linear drive device 51 is connected to the actuator unit 52 and can drive the actuator units 52 on both sides to act simultaneously, so as to realize the deployment or folding of the three solar panels.

[0031] Such asFigure 2 As shown in the figure, an arc-shaped sliding groove 524 is formed on the wall surface of the nacelle body 1. The arc-shaped sliding groove 524 can guide the movement of the parallelogram link assembly and enable the above-mentioned link to move, so as to realize the raising or lowering of the third solar panel 4. Specifically, the limit position of the sliding groove 524 close to the linear driving device 51 is the folding position, and the limit position far from the linear driving device 51 is the unfolding position. The height of the folding position in the vertical direction is lower than that of the unfolding position, and the highest point position of the arc-shaped sliding groove 524 is higher than the folding position and lower than the unfolding position, so that the three solar panels can be in the same plane after being fully unfolded, thus avoiding occlusion and increasing the contact area with sunlight.

[0032] When specifically arranged, execution units 52 are provided on both sides of the linear driving device 51. Each execution unit 52 includes a rising link 525. The rising links 525 on both sides are hinged to the third solar panel 4, and the rising links 525 on both sides are correspondingly arranged on both sides of the third solar panel, so as to provide more stable force bearing and make the force on the third solar panel 4 more uniform.

[0033] It can be understood that when the solar panel is in the folded state, it is necessary to minimize its occupied space as much as possible to reduce the risk of damage, and when unfolded, it needs to have a large area so as to increase the illumination area as much as possible. In this embodiment, the solar panel can reduce the overall occupied area when in the folded position, and can make the three solar panels in the same plane after being unfolded, increasing the illumination area and avoiding the occlusion of the solar panels.

[0034] Specifically, during the unfolding process, as Figure 1 Figure 3 shown in the figure, the output end of the linear driving device 51 is located at the lower position, and driving links 521 are hinged on both sides of the output end. When unfolding, the linear driving device 51 retracts to drive one end of the driving link 521 to move upward. The other end of the driving link 521 slides along the sliding groove 524 from the folding position and drives the parallelogram link assembly to move. At the same time, the rising link 525 moves to realize the upward movement of the third solar panel 4. As the linear driving device 51 continues to move, the other end of the driving link 521 finally reaches the unfolding position along the sliding groove 524. At this time, the three panels are in the same plane state.

[0035] In specific applications, the linear driving device 51 includes a linear motor, and the output end of the linear motor is hinged to the driving link 521. The linear driving motor is easy to control, has a fast response speed, and runs stably, and can realize the stable driving of the driving link 521.

[0036] In some embodiments, the areas of the first solar panel 2 and the second solar panel 3 are both smaller than the area of the third solar panel 4. The first solar panel 2 and the second solar panel 3 need to be deployed and retracted under the action of the execution units 52 on both sides. In this embodiment, by limiting the areas of the first solar panel 2 and the second solar panel 3, it is beneficial to reduce the overall space occupied during folding.

[0037] Specifically, the first solar panel 2 and the second solar panel 3 have the same area, and both are retracted and deployed through the execution unit 52. The same area method is beneficial to the preparation of solar panels and enables mutual replacement.

[0038] Combined with the above embodiments, as Figure 3 shown, the first solar panel 2, the second solar panel 3, and the third solar panel 4 are all rectangular plate structures, and the first solar panel 2 and the second solar panel 3 are located above the third solar panel 4 in the retracted position and can cover the third solar panel 4. The three solar panels can make full use of solar energy, and by arranging the first solar panel 2 and the second solar panel 3 above the third solar panel 4, the occupied space during folding is reduced, and the safety of the solar panel is improved.

[0039] Specifically, as Figure 2 shown, the first solar panel and the second solar panel are connected when in the retracted state, and the combined area of the two is slightly larger than the area of the third solar panel, so as to achieve coverage of the third solar panel.

[0040] In some embodiments provided by the present invention, the parallelogram link assembly includes a first link 522 and a second link 523. The first link 522 and the second link 523 are arranged in parallel. One end of the first link 522 is hinged to the first solar panel 2 or the second solar panel 3, and the other end of the first link 522 is hinged to the pod body 1. One end of the second link 523 is hinged to the first solar panel 2 or the second solar panel 3, and the other end of the second link 523 is hinged to the pod body 1. The drive link 521 and the lifting link 525 are both hinged to the rod body of the first link 522. The first solar panel 2 and the second solar panel 3 are both connected by the parallelogram link assembly, so that they can both be retracted and deployed under the drive of the drive link 521. In this embodiment, the first link 522 and the second link 523 are provided in the execution units 52 on both sides, which can achieve stable support for the first solar panel 2 and the second solar panel 3 and improve the stability of their support.

[0041] In combination with the above embodiment, the rod body of the first connecting rod 522 has a hinged portion, and the driving connecting rod 521 and the rising connecting rod 525 are both hinged to the hinged portion. When driving, it is necessary to keep the three solar panels linked to each other to expand or contract, so as to reduce the difficulty of operation. In this embodiment, the driving connecting rod 521 and the rising connecting rod 525 are both hinged to the hinged portion, and slide along the sliding groove 524, so as to achieve the synchronous movement of the three solar panels and reduce the difficulty of operation.

[0042] Specifically, the first connecting rod 522 is close to the linear drive device 51, and the second connecting rod 523 is far away from the linear drive device 51. A hinge portion is provided on the rod body of the first connecting rod 522. When specifically connected, a hinge shaft is provided at the hinge portion, and the rising connecting rod 525 and the driving connecting rod 521 are both hinged to the same hinge shaft, thereby realizing synchronous driving and realizing synchronous movement of the three solar panels.

[0043] In a specific embodiment, the rising link 525 is located inside the pod body 1, and the driving link 521 and the parallelogram link assembly are located outside the pod body 1. This arrangement can make the overall structure more compact and facilitate the arrangement of the parallelogram link assembly.

[0044] Specifically, the structure of the parallelogram connecting rod assembly is relatively complex, and by arranging it on the outside of the pod body 1, it is convenient for installation and connection.

[0045] According to some embodiments provided by the present invention, the pod body 1 includes a box body 11 and a connecting frame 12, the connecting frame 12 is connected to the box body 11, and a connecting end 13 for connecting to an airbag is provided on the top of the connecting frame 12. The pod body 1 is used to carry equipment such as meteorological collection components, and the connection frame 12 and the connecting end 13 are provided to facilitate connection with the floating airbag, thereby improving the convenience of its connection.

[0046] In combination with the above embodiment, two opposite side panels of the box body 11 are provided with an unfolding mechanism 5. The arrangement of the unfolding mechanism 5 on both sides can improve the stability of the solar panel support.

[0047] Specifically, the three solar panels have a certain weight and occupy a certain area. In this embodiment, the unfolding mechanisms 5 on both sides can achieve uniform support on both sides of the solar panels, thereby making the support stability of the solar panels higher.

[0048] like Figure 5 As shown, in the second aspect of the present invention, an aerostat comprises: an air bag; a long-endurance aerostat solar panel deployment structure as provided in any of the above embodiments, wherein the air bag is connected to a pod body 1 .

[0049] Specifically, Figure 5As shown, during the launching and ascending stage of the aerostat, the first solar panel 2, the second solar panel 3, and the third solar panel 4 are in a folded state. After flying steadily in level flight, the first solar panel 2, the second solar panel 3, and the third solar panel 4 are deployed to be in the deployed stage, and they are folded again during the preparation for landing and the landing stage. This improves the protection of the solar panels.

[0050] Through the description of the above embodiments, those skilled in the art can clearly understand that in each embodiment, through the setting of the deployment mechanism 5, during the ground launching and ascending process of the aerostat, the solar panels are in a contracted state, causing the first solar panel 2 and the second solar panel 3 to be folded, reducing the risk of collision with the boom of the launching vehicle during the launching process and the additional resistance during ascending, and protecting the safety of the main structure of the solar panels. After reaching the predetermined altitude and entering the level flight state, the execution unit 52 and the linear drive device 51 cooperate to drive the solar panels to unfold from the contracted state to work normally, providing cyclic energy for the aerostat system. Further, through the limitation of the three solar panels, the space occupied when they are in the folded state is smaller, which is beneficial to the ascending and descending of the aerostat.

[0051] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments or perform equivalent replacements for some of the technical features. However, such modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A long-endurance aerostat solar panel deployment structure, characterized in that: include: A pod body, a deployment mechanism, a first solar panel, a second solar panel and a third solar panel, wherein the deployment mechanism is arranged on the pod body, and the first solar panel, the second solar panel and the third solar panel are all connected to the deployment mechanism; The deployment mechanism includes a linear drive device and execution units arranged on both sides of the linear drive device, the execution units on both sides are hinged to the linear drive device, and the execution unit on one side is hinged to the first solar sail panel, the execution unit on the other side is hinged to the second solar sail panel, and the execution units on both sides are hinged to the third solar sail panel; Wherein, the execution unit includes a driving link, a parallelogram linkage assembly and a rising link, the first solar panel and the second solar panel are both hinged to the nacelle body through the parallelogram linkage assembly, one end of the rising link is hinged to the third solar panel, the other end of the rising link is hinged to the parallelogram linkage assembly, one end of the driving link is hinged to the linear driving device, and the other end of the driving link is hinged to the parallelogram linkage assembly; an arc-shaped sliding groove is provided on the nacelle body, and the hinge point of the driving link and the parallelogram linkage assembly is located in the sliding groove, and the linear driving device is used to drive the execution units on both sides to act simultaneously, so that the first solar panel, the second solar panel and the third solar panel are in the same plane when in the unfolded position.

2. The long-endurance aerostat solar panel deployment structure according to claim 1, characterized in that: The areas of the first solar panel and the second solar panel are both smaller than the area of ​​the third solar panel.

3. The long-endurance aerostat solar panel deployment structure according to claim 2, characterized in that: The first solar panel, the second solar panel and the third solar panel are all rectangular panel structures, and the first solar panel and the second solar panel are located above the third solar panel when in the folded position and can cover the third solar panel.

4. The long-endurance aerostat solar panel deployment structure according to claim 1, characterized in that: The parallelogram linkage assembly includes a first linkage and a second linkage, the first linkage is arranged in parallel with the second linkage, one end of the first linkage is hinged to the first solar panel or the second solar panel, the other end of the first linkage is hinged to the pod body, one end of the second linkage is hinged to the first solar panel or the second solar panel, the other end of the second linkage is hinged to the pod body, and the driving linkage and the rising linkage are both hinged to the rod body of the first linkage.

5. The long-endurance aerostat solar panel deployment structure according to claim 4, characterized in that: The rod body of the first connecting rod is provided with a hinged portion, and the driving connecting rod and the rising connecting rod are both hinged to the hinged portion.

6. The long-endurance aerostat solar panel deployment structure according to claim 1, characterized in that: The rising link is located inside the pod body, and the driving link and the parallelogram link assembly are located outside the pod body.

7. The long-endurance aerostat solar panel deployment structure according to claim 1, characterized in that: The pod body comprises a box body and a connecting frame, the connecting frame is connected to the box body, and a connecting end for connecting an airbag is provided on the top of the connecting frame.

8. The long-endurance aerostat solar panel deployment structure according to claim 7, characterized in that: The unfolding mechanism is disposed on two opposite side panels of the box body.

9. The long-endurance aerostat solar panel deployment structure according to claim 1, characterized in that: The linear drive device comprises a linear motor, and an output end of the linear motor is hinged to the driving connecting rod.

10. An aerostat, characterized in that: include: floating air bag; According to the long-endurance aerostat solar panel deployment structure as described in any one of claims 1 to 9, the air buoyancy bag is connected to the pod body.

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