Energy cabin frame, energy cabin system and near space aerostat with energy cabin system

Abstract

The invention discloses an energy cabin frame, an energy cabin system and a near space aerostat with the energy cabin frame, the energy cabin frame is used for the near space aerostat and comprises a transition frame, the transition frame is arranged on a sphere of the near space aerostat, the transition frame is located on the side, in the first direction, of the sphere, and the transition frame comprises a plurality of first pipes; and the main body is arranged on the side, away from the sphere, of the transition frame, the main body comprises a plurality of second pipes, the first pipes and the second pipes are three-dimensional multidirectional braided pipes, and the three-dimensional multidirectional braided pipes are formed by braiding and curing carbon fiber composite materials. According to the energy cabin frame, the mechanical performance and functional performance of the transition frame and the main body can be optimized, the structural efficiency of the transition frame and the main body is improved, the stress level of the transition frame and the main body is improved, the reliability and safety of the energy cabin frame are improved, and the weight of the transition frame and the main body can be reduced; and the lightweight design of the energy cabin frame is facilitated.

Description

Technical Field

[0001] The present invention relates to the technical field of near-space aerostats, and in particular to an energy cabin frame, an energy cabin system and a near-space aerostat having the same. Background Art

[0002] In addition to carrying the payloads and structures that maintain the platform's functionality, near-space aerostats can also be equipped with various types of surveillance and detection equipment, including electronic communications equipment, infrared cameras, and early warning radars, to facilitate communication relay, Earth observation, and reconnaissance and early warning. The energy capsule system of a near-space aerostat provides a platform for the normal operation of the energy payload, protecting the onboard equipment and energy payload from the low temperature and low pressure environment during flight.

[0003] In the existing technology, since the flight altitude of near-space aerostats is generally between 20-40km and the flight conditions are in extreme environmental conditions (-90℃), considering the large load of near-space aerostats, the lightweighting problem of the energy cabin system needs to be solved urgently. Summary of the Invention

[0004] The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, the present invention proposes an energy cabin frame that optimizes the mechanical and functional properties of the transition frame and the main body, reduces the weight of the transition frame and the main body, and facilitates the lightweight design of the energy cabin frame.

[0005] The present invention also proposes an energy cabin system, which includes the above-mentioned energy cabin frame.

[0006] The present invention also provides a near-space aerostat, which includes the above-mentioned energy cabin system.

[0007] According to an embodiment of the present invention, the energy cabin frame is used for a near-space airship and includes: a transition frame, which is arranged on the sphere of the near-space airship and is located on one side of the sphere along a first direction, and the transition frame includes a plurality of first tubes; a main body, which is arranged on the side of the transition frame away from the sphere, and the main body includes a plurality of second tubes, and the first tubes and the second tubes are both three-dimensional multi-directional braided tubes, and the three-dimensional multi-directional braided tubes are woven and cured from carbon fiber composite materials.

[0008] According to the energy cabin frame of the embodiment of the present invention, the transition frame includes multiple first tubes, and the main body includes multiple second tubes. The first tubes and the second tubes are both three-dimensional multi-directional braided tubes. The three-dimensional multi-directional braided tubes are braided and cured from carbon fiber composite materials, so that the first tubes and the second tubes can evenly bear the load when subjected to force, which can optimize the mechanical properties and functional performance of the transition frame and the main body, increase the structural efficiency of the transition frame and the main body, improve the stress level of the transition frame and the main body, improve the reliability and safety of the energy cabin frame, and reduce the weight of the transition frame and the main body, which is conducive to the lightweight design of the energy cabin frame, provides additional redundant space for the energy payload to be carried on the near-space aerostat platform, and can leave the weight saved by the energy cabin frame to the energy, thereby indirectly increasing the endurance of the near-space aerostat.

[0009] In addition, the energy cabin frame according to the present invention may also have the following additional technical features:

[0010] In some embodiments, the plurality of second tubes include a main load-bearing tube group and a plurality of secondary load-bearing tube groups, the main load-bearing tube group includes a plurality of main load-bearing tubes extending along the first direction, the plurality of main load-bearing tubes are spaced apart along the circumferential direction of the main body, the plurality of secondary load-bearing tube groups are arranged and spaced apart along the first direction, and the plurality of secondary load-bearing tube groups are all connected to the main load-bearing tube group.

[0011] In some embodiments, at least part of the multiple secondary load-bearing pipe groups are first pipe groups, each of the main load-bearing pipes is connected to the first pipe group, the first pipe group includes multiple first sub-pipes and multiple second sub-pipes, multiple first sub-pipes all extend along the second direction and are spaced apart in the third direction, multiple second sub-pipes all extend along the third direction and are spaced apart in the second direction, multiple first sub-pipes and multiple second sub-pipes are staggered, and the first direction, the second direction and the third direction are perpendicular to each other.

[0012] In some embodiments, part of the multiple secondary load-bearing pipe groups is a second pipe group, the second pipe group is connected to part of the main load-bearing pipes, and the second pipe group is separated from the main load-bearing pipes at one end of the multiple main load-bearing pipes in the second direction, and the second direction is perpendicular to the first direction.

[0013] In some embodiments, the plurality of second tubes further include a third tube group, the third tube group including a plurality of third sub-tubes extending along the first direction, the third sub-tubes being spaced apart from the main load-bearing tubes and used to connect two adjacent secondary load-bearing tube groups.

[0014] In some embodiments, the main load-bearing tube is a three-dimensional five-way braided tube; and / or the second tube of the secondary load-bearing tube group is a three-dimensional four-way braided tube.

[0015] In some embodiments, both ends of the main load-bearing tube along the first direction are provided with licker-in joints, the licker-in joints are embedded in the main load-bearing tube, and the licker-in joints and the main load-bearing tube are an integral part.

[0016] In some embodiments, the energy cabin frame also includes: a first joint, the first joint having a threaded section and a plurality of first interface sections, the threaded section being used to be threadedly connected to the end of the main load-bearing pipe facing away from the transition frame, the first interface section being used to be connected to the second pipe of the secondary load-bearing pipe group; a second joint, the second joint being spaced apart from the first joint, the second joint having a plurality of second interface sections, the second interface section being used to be connected to the second pipe.

[0017] In some embodiments, the first joint and / or the second joint is a titanium alloy part.

[0018] In some embodiments, the energy cabin frame further includes: a mounting plate, and the mounting plate is provided on at least part of the secondary load-bearing pipe group.

[0019] According to an embodiment of the present invention, the energy cabin system includes: the above-mentioned energy cabin frame; a protective plate, which covers the main body to define a cavity, and the protective plate is detachably connected to the main body; a battery and a power supply device, and the battery and the power supply device are both arranged in the cavity.

[0020] According to the energy cabin system of an embodiment of the present invention, the energy cabin frame is provided with the above-mentioned energy cabin frame, the transition frame includes multiple first tubes, the main body includes multiple second tubes, and the first tubes and the second tubes are both three-dimensional multi-directional braided tubes. The three-dimensional multi-directional braided tubes are braided and solidified from carbon fiber composite materials, so that the first tubes and the second tubes can evenly bear the load when subjected to force, and can optimize the mechanical properties and functional performance of the transition frame and the main body, increase the structural efficiency of the transition frame and the main body, improve the stress level of the transition frame and the main body, improve the reliability and safety of the energy cabin frame, and can reduce the weight of the transition frame and the main body, which is conducive to the lightweight design of the energy cabin frame, provides additional redundant space for the energy payload to be carried on the near-space aerostat platform, and can leave the weight saved by the energy cabin frame to the energy, thereby indirectly increasing the endurance of the near-space aerostat.

[0021] In addition, the energy cabin system according to the present invention may also have the following additional technical features:

[0022] In some embodiments, the cavity includes a first cavity and a second cavity arranged in a second direction, the battery is located in the first cavity, the inner wall of the first cavity is provided with a shielding film, the power supply device is located in the second cavity, and the second direction is perpendicular to the first direction.

[0023] In some embodiments, a side wall of the protective plate defining the second cavity has a first opening, and a protective film is attached to the first opening.

[0024] In some embodiments, the shielding film is an aluminum film or a copper foil.

[0025] In some embodiments, a second opening is provided on the inner wall of the protective plate that defines the second cavity and faces away from the transition frame, and the power supply device is disposed opposite to the second opening.

[0026] In some embodiments, the protective plate is a plastic part.

[0027] In some embodiments, the energy cabin system further includes: a carbon strip, wherein the carbon strip is provided on the outer wall surface of the protective plate, and the carbon strip is detachably connected to the protective plate.

[0028] The present invention also provides a near-space aerostat having the above embodiment.

[0029] According to an embodiment of the present invention, the near-space aerostat is provided with the above-mentioned energy cabin system, wherein the transition frame includes a plurality of first tubes, and the main body includes a plurality of second tubes, and the first tubes and the second tubes are both three-dimensional multi-directional braided tubes, which are braided and solidified from carbon fiber composite materials, so that the first tubes and the second tubes can evenly bear the load when subjected to force, thereby optimizing the mechanical properties and functional performance of the transition frame and the main body, increasing the structural efficiency of the transition frame and the main body, improving the stress levels of the transition frame and the main body, improving the reliability and safety of the energy cabin frame, and reducing the weight of the transition frame and the main body, which is conducive to the lightweight design of the energy cabin frame, providing additional redundant space for the energy payload to be carried on the near-space aerostat platform, and leaving the weight saved by the energy cabin frame for energy, thereby indirectly increasing the endurance of the near-space aerostat.

[0030] Additional aspects and advantages of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description which follows, or may be learned by practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the following description of the embodiments with reference to the accompanying drawings, in which:

[0032] Figure 1 is a perspective view of an energy cabin system according to an embodiment of the present invention;

[0033] Figure 2 is a top view of an energy cabin system according to an embodiment of the present invention, wherein transition frames, protective plates, and carbon strips are not shown;

[0034] Figure 3is a perspective view of an energy cabin frame according to an embodiment of the present invention;

[0035] Figure 4 yes Figure 3 Enlarged view of point A in the middle;

[0036] Figure 5 is a top view of an energy cabin frame according to an embodiment of the present invention;

[0037] Figure 6 is a front view of an energy cabin frame according to an embodiment of the present invention;

[0038] Figure 7 is a left side view of an energy cabin frame according to an embodiment of the present invention;

[0039] Figure 8 It is a cross-sectional view of the main load-bearing tube of the energy cabin frame according to an embodiment of the present invention.

[0040] Reference numerals:

[0041] 100. Energy cabin system;

[0042] 10. Energy cabin frame;

[0043] 1. Transition frame; 11. First pipe; 12. Connecting portion; 121. Lifting lug; 122. Stud;

[0044] 2. Main body; 21. Second tube; 22. Main load-bearing tube group; 220. Main load-bearing tube; 221. Taker-in joint; 222. Foam core shaft; 23. Secondary load-bearing tube group; 231. First tube group; 2311. First sub-tube; 2312. Second sub-tube; 232. Second tube group; 2321. Fourth sub-tube; 2322. Fifth sub-tube; 24. Third tube group; 241. Third sub-tube;

[0045] 3. First joint;

[0046] 4. Second joint;

[0047] 5. Mounting plate; 51. Buckle; 52. Weight reduction hole;

[0048] 20. Protective plate; 201. Cavity; 202. First cavity; 203. Second cavity; 204. First opening; 205. Protective film; 206. Wire outlet hole; 207. U-shaped member;

[0049] 30. Battery;

[0050] 40. Power supply equipment;

[0051] 50. Carbon rod. DETAILED DESCRIPTION

[0052] The following describes embodiments of the present invention in detail. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended only to explain the present invention and are not to be construed as limiting the present invention.

[0053] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing 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 therefore should not be understood as limiting the present invention.

[0054] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature identified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0055] In the present invention, unless otherwise expressly specified or limited, terms such as "mounted," "connected," "connect," and "fixed" should be understood broadly. For example, they may refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0056] The energy cabin frame 10 according to an embodiment of the present invention will be described below with reference to the accompanying drawings.

[0057] like Figure 3 、 Figure 6 and Figure 7 As shown, the energy cabin frame 10 according to an embodiment of the present invention is used for a near-space aerostat and includes a transition frame 1 and a main body 2.

[0058] Specifically, refer to the attached Figure 3 and attached Figure 7 As shown, the transition frame 1 is provided on the sphere of the near-space aerostat, and the transition frame 1 is located on the sphere along the first direction (such as Figure 3As shown in FIG), the transition frame 1 includes a plurality of first tubes 11, and the transition frame 1 is connected to the spherical pull tab by a rope. During the connection process, the pull tab should be uniformly stressed to avoid excessive stress on the root of the local pull tab. Figure 3 As shown, the main body 2 is arranged on the side of the transition frame 1 away from the sphere. The main body 2 includes multiple second tubes 21. The first tube 11 and the second tube 21 are both three-dimensional multi-directional braided tubes, which are braided and cured from carbon fiber composite materials.

[0059] It is understandable that carbon fiber composites are inorganic high-performance fibers with a carbon content of more than 90% that are converted from organic fibers through a series of heat treatments. They have the inherent characteristics of carbon materials and the softness and processability of textile fibers. Carbon fibers can be compounded with resin matrices to make structural materials. The use of a three-dimensional multi-directional (3DnD) weaving method to weave carbon fiber composites just makes up for the shortcomings of two-dimensional (2D) composites, such as poor out-of-plane performance, severe stratification under thermal / mechanical cycles, and fragile microscopic interfaces under harsh low-temperature environments in near-space (5KPa, below -90°C). Compared with two-dimensional composites, three-dimensional woven composites have a completely integrated, non-layered structure. They have high specific strength and specific modulus, excellent mechanical properties and functional properties, and can be used to manufacture structural parts and high-function parts.

[0060] By making the multiple first tubes 11 of the transition frame 1 and the multiple second tubes 21 of the main body 2 all three-dimensional multi-directional braided tubes, the first tubes 11 and the second tubes 21 can evenly bear the load when subjected to force, thereby optimizing the mechanical properties and functional performance of the transition frame 1 and the main body 2, increasing the structural efficiency of the transition frame 1 and the main body 2, improving the stress level of the transition frame 1 and the main body 2, improving the reliability and safety of the energy cabin frame 10, and reducing the weight of the transition frame 1 and the main body 2, which is beneficial to the lightweight design of the energy cabin frame 10, providing additional redundant space for the energy payload to be carried on the near-space aerostat platform, and leaving the weight saved by the energy cabin frame 10 for energy, thereby indirectly increasing the endurance of the near-space aerostat.

[0061] It should be noted that if Figure 3 and Figure 4 As shown, the main body 2 and the transition frame 1 are connected by a connecting portion 12, and the connecting portion 12 includes a lifting ear 121 and a stud 122. The lifting ear 121 is sleeved on the first tube 11 of the transition frame 1, and the stud 122 extends into the second tube 21 of the main body 2 and is threadedly connected to the second tube 21. The lifting ear 121 and the stud 122 are connected by a pin, thereby realizing the connection between the main body 2 and the transition frame 1. In addition, the connecting portion 12 can be a plurality of portions spaced apart along the circumferential direction of the main body 2, and the main body 2 and the transition frame 1 can be connected from multiple locations to ensure the reliability of the connection between the main body 2 and the transition frame 1.

[0062] According to the energy cabin frame 10 of the embodiment of the present invention, the transition frame 1 includes multiple first tubes 11, and the main body 2 includes multiple second tubes 21. The first tubes 11 and the second tubes 21 are both three-dimensional multi-directional braided tubes. The three-dimensional multi-directional braided tubes are woven and solidified from carbon fiber composite materials, so that the first tubes 11 and the second tubes 21 can evenly bear the load when subjected to force, and can optimize the mechanical properties and functional performances of the transition frame 1 and the main body 2, increase the structural efficiency of the transition frame 1 and the main body 2, improve the stress level of the transition frame 1 and the main body 2, improve the reliability and safety of the energy cabin frame 10, and can reduce the weight of the transition frame 1 and the main body 2, which is conducive to the lightweight design of the energy cabin frame 10, and provides additional redundant space for the energy payload to be carried on the near-space aerostat platform. The weight saved by the energy cabin frame 10 can be left to the energy, thereby indirectly increasing the endurance of the near-space aerostat.

[0063] In some embodiments of the present invention, Figure 3 As shown, the multiple second tubes 21 include a main load-bearing tube group 22 and multiple secondary load-bearing tube groups 23. The main load-bearing tube group 22 includes multiple main load-bearing tubes 220 extending along the first direction. The multiple main load-bearing tubes 220 are arranged at intervals along the circumferential direction of the main body 2. The multiple secondary load-bearing tube groups 23 are arranged and spaced apart along the first direction. The multiple secondary load-bearing tube groups 23 are all connected to the main load-bearing tube group 22.

[0064] It can be understood that the main load-bearing pipe group 22 is mainly used for bearing load. The setting of multiple main load-bearing pipes 220 can increase the load-bearing effect of the main load-bearing pipe group 22 and ensure the stability of the energy cabin frame 10. The secondary load-bearing pipe group 23 is mainly used for transmitting force. Multiple secondary load-bearing pipe groups 23 are arranged at intervals in the first direction, which can improve the connection reliability between multiple main load-bearing pipes 220, further ensure the reliability of the connection of the energy cabin frame 10, and ensure the stability of the energy cabin frame 10.

[0065] In a specific example, see the attached Figure 3 As shown, the multiple second tubes 21 include a main load-bearing tube group 22 and three secondary load-bearing tube groups 23. The main load-bearing tube group 22 includes ten main load-bearing tubes 220 arranged at intervals along the circumferential direction of the main body 2. Each main load-bearing tube 220 extends along the first direction. The three secondary load-bearing tube groups 23 are respectively connected to the two ends and the middle area of ​​the main load-bearing tube group 22 along the first direction, which can ensure the connection reliability between the main load-bearing tube group 22 and the secondary load-bearing tube group 23, ensure the force transmission performance of the energy cabin frame 10, and improve the stability and reliability of the energy cabin frame 10.

[0066] In some embodiments of the present invention, Figure 3As shown, at least part of the multiple secondary load-bearing pipe groups 23 is a first pipe group 231. Each main load-bearing pipe 220 is connected to the first pipe group 231. The first pipe group 231 includes multiple first sub-pipes 2311 and multiple second sub-pipes 2312. The multiple first sub-pipes 2311 are all along the second direction (such as Figure 3 ) and extends in a third direction (as shown Figure 3 As shown in the figure, the plurality of second sub-tubes 2312 are arranged at intervals on the third direction, and the plurality of first sub-tubes 2311 and the plurality of second sub-tubes 2312 are arranged in a staggered manner, and the first direction, the second direction and the third direction are perpendicular to each other, thereby forming a staggered grid structure, improving the structural strength of the first tube group 231, ensuring the force transmission performance of the first tube group 231, and improving the stability and reliability of the energy cabin frame 10.

[0067] In a specific example, see the attached Figure 3 As shown, multiple secondary load-bearing pipe groups 23 include two first pipe groups 231, and the two first pipe groups 231 are respectively connected to the two ends of the main load-bearing pipe group 22 along the first direction. Each first pipe group 231 includes three first sub-pipes 2311 and six second sub-pipes 2312. The three first sub-pipes 2311 all extend along the second direction and are spaced apart in the third direction. The six second sub-pipes 2312 all extend along the third direction and are spaced apart in the second direction, thereby forming an interlaced grid structure, improving the structural strength of the first pipe group 231, ensuring the force transmission performance of the first pipe group 231, and improving the stability and reliability of the energy cabin frame 10.

[0068] In some embodiments of the present invention, Figure 3 As shown, part of the multiple secondary load-bearing pipe groups 23 is the second pipe group 232, the second pipe group 232 is connected to part of the main load-bearing pipes 220, and the second pipe group 232 is separated from the main load-bearing pipes 220 at one end of the multiple main load-bearing pipes 220 in the second direction, and the second direction is perpendicular to the first direction. On the one hand, the setting of the second pipe group 232 can improve the structural strength of the secondary load-bearing pipe group 23 and ensure the force transmission performance of the secondary load-bearing pipe group 23. On the other hand, a part of the space can be reserved in the second direction to form an independent compartment for placing the power supply equipment 40 that requires separate electromagnetic shielding, so that it has good electromagnetic shielding performance and temperature control isolation performance.

[0069] Further, refer to the attached Figure 3As shown, the second tube group 232 includes a plurality of fourth sub-tubes 2321 and a plurality of fifth sub-tubes 2322, the plurality of fourth sub-tubes 2321 all extend along the second direction and are spaced apart in the third direction, the plurality of fifth sub-tubes 2322 all extend along the third direction and are spaced apart in the second direction, the plurality of first sub-tubes 2311 and the plurality of second sub-tubes 2312 are staggered, thereby forming a staggered grid structure, improving the structural strength of the second tube group 232, ensuring the force transmission performance of the second tube group 232, and improving the stability and reliability of the energy cabin frame 10.

[0070] In a specific example, see the attached Figure 3 As shown, multiple secondary load-bearing pipe groups 23 include two first pipe groups 231 and one second pipe group 232. The two first pipe groups 231 are respectively connected to the two ends of the main load-bearing pipe group 22 along the first direction, and the second pipe group 232 is connected to the middle area of ​​the main load-bearing pipe group 22 along the first direction. The second pipe group 232 is connected to eight of the ten main load-bearing pipes 220 and is separated from the remaining two.

[0071] In some embodiments of the present invention, Figure 3 As shown, the multiple second tubes 21 also include a third tube group 24, and the third tube group 24 includes multiple third sub-tubes 241 extending along the first direction. The third sub-tubes 241 are separated from the main load-bearing tubes 220 and are used to connect two adjacent secondary load-bearing tube groups 23. The setting of the third sub-tubes 241 can play a supporting role together with the main load-bearing tubes 220, further improving the connection reliability between the two adjacent secondary load-bearing tube groups 23, and ensuring the connection reliability and stability of the entire energy cabin frame 10.

[0072] In some embodiments of the present invention, the main load-bearing tube 220 is a three-dimensional five-directional braided tube, which can improve the axial bearing performance of the main load-bearing tube 220 and improve the strength and stiffness of the main load-bearing tube 220; and / or, the second tube 21 of the secondary load-bearing tube group 23 is a three-dimensional four-directional braided tube, which can improve the torsional resistance of the second tube 21 of the secondary load-bearing tube group 23 and enhance the strength and stiffness of the second tube 21 of the secondary load-bearing tube group 23 in the circumferential direction.

[0073] Preferably, each second tube 21 of the secondary load-bearing tube group 23 is a thin-walled circular tube structure with uniform cross-section, and the fiber volume fraction is not less than 50%, which can ensure uniform force on a single second tube 21, ensure the structural reliability of the second tube 21, and avoid the second tube 21 of the secondary load-bearing tube group 23 from being too heavy.

[0074] It should be noted that on the basis of the three-dimensional four-directional braided structure, reinforcing fibers can be considered in the x, y or z direction as needed to form three-dimensional five-directional, three-dimensional six-directional, three-dimensional seven-directional and other structures. The fibers are not only intertwined and crossed with each other in the plane, but also intertwined and crossed with each other in the three-dimensional space through the thickness direction, forming a non-layered overall structure, which improves the axial, circumferential and radial mechanical properties of the material to varying degrees, maintaining the integrity of the composite material structure in bearing deformation.

[0075] In some embodiments of the present invention, Figure 8 As shown, both ends of the main load-bearing tube 220 along the first direction are provided with a licker-in joint 221, and the licker-in joint 221 is embedded in the main load-bearing tube 220. The licker-in joint 221 and the main load-bearing tube 220 are an integral part, and the outer surface of the licker-in joint 221 is matched with the inner surface of the main load-bearing tube 220. The outer surface of the licker-in joint 221 is provided with a plurality of sharp needles, which are embedded in the main load-bearing tube 220 along the radial direction of the main load-bearing tube 220, and the outer diameter of the circle where the sharp points of the sharp needles are located is smaller than the outer diameter of the main load-bearing tube 220, which can convert the in-plane shear failure in the traditional connection method into a combined shear and bending failure, improve the fatigue failure resistance, minimize the influence of the interface on the failure behavior, and effectively avoid the stress concentration phenomenon that is prone to occur in traditional connections, so that the bearing capacity is greatly enhanced. Therefore, the integrated component formed by the combination of the roller joint 221 and the main load-bearing tube 220 has excellent mechanical properties. It can greatly improve the stiffness and axial bearing strength of the main load-bearing tube 220 while reducing the weight of the structure, overcome the delamination damage weakness in traditional connection technology, and meet the application requirements of heavy-load connection structures of near-space airships.

[0076] It should be noted that the licker-in joint 221 is made of TC4 titanium alloy, which can reduce the possibility of electrochemical corrosion between the licker-in joint 221 and the main load-bearing tube 220, ensure the safety and reliability of the main load-bearing tube 220 and the licker-in joint 221, extend the service life of the energy cabin frame 10, and ensure the safety of the near-space aerostat.

[0077] Preferably, the fiber volume content of the main load-bearing tube 220 is not less than 55%, the length of the licker-in joint 221 in the first direction is less than or equal to 50 mm, and the outer diameter of the main load-bearing tube 220 is less than or equal to 30 mm, which can ensure the overall structural strength and reliability of the main load-bearing tube 220 and the licker-in joint 221, ensure that the main load-bearing tube 220 and the licker-in joint 221 are sufficient to carry the weight of the energy cabin system 100, and ensure the reliability and stability of the energy cabin system 100.

[0078] It should be noted that the main load-bearing tube 220 and the licker-in joint 221 are integrally solidified and molded through RTM (Resin Transfer Molding), which can improve the molding efficiency of the main load-bearing tube 220 and the licker-in joint 221, improve the production and processing efficiency of the energy cabin frame 10, and reduce the consumption of raw materials and energy during the processing, thereby reducing the production and processing costs of the main load-bearing tube 220 and the licker-in joint 221.

[0079] Further, refer to the attached Figure 8 As shown, the integral part formed by the main load-bearing tube 220 and the lancet joint 221 adopts a hollow design, which is beneficial to the weight reduction of the energy cabin frame 10 and can improve the structural efficiency and stress level. A foam core shaft 222 is inserted into the interior of the main load-bearing tube 220. The foam core shaft 222 is located between the two lancet joints 221. It can reduce the impact on the weight of the main load-bearing tube group 22 as much as possible on the basis of ensuring the rigidity of the main load-bearing tube 220, thereby ensuring the lightweight of the energy cabin frame 10. Specifically, the foam core shaft 222 can be made of a hard foam plastic material, such as polymethacrylimide (PMI) foam plastic, hard polyurethane foam plastic, hard polyvinyl chloride foam plastic, etc. This embodiment is described by taking the foam core shaft 222 using PMI foam plastic as an example.

[0080] It should be noted that the two licker-in joints 221 at both ends of the main load-bearing pipe 220 along the first direction are respectively used to connect with the transition frame 1 and the second pipe 21 of the secondary load-bearing pipe group 23, and the inner walls of the two licker-in joints 221 are provided with internal threads. The one of the two licker-in joints 221 close to the transition frame 1 is threadedly connected to the stud 122 of the connecting part 12, and the other is threadedly connected to the threaded section of the first joint 3.

[0081] In some embodiments of the present invention, Figure 3As shown, the energy cabin frame 10 also includes a first joint 3 and a second joint 4. The first joint 3 has a threaded section and multiple first interface sections. The threaded section is used to be threadedly connected to the end of the main load-bearing pipe 220 that is away from the transition frame 1, and the first interface section is used to be connected to the second pipe 21 of the secondary load-bearing pipe group 23. It can be understood that the threaded section is threadedly connected to the end of the main load-bearing pipe 220 that is away from the transition frame 1, which can facilitate the assembly and disassembly between the first joint 3 and the main load-bearing pipe 220, improve the connection strength between the first joint 3 and the main load-bearing pipe 220, improve the connection reliability between the first joint 3 and the main load-bearing pipe 220, meet the load-bearing requirements of the main load-bearing pipe 220, and ensure the structural reliability and stability of the energy cabin frame 10. A first joint 3 is provided with multiple first interface sections, which can connect a main load-bearing pipe 220 to the second pipes 21 of multiple secondary load-bearing pipe groups 23 at the same time, so that a first joint 3 can be connected to multiple second pipes 21 at the same time, reducing the number of components of the energy cabin frame 10 and ensuring the integrity and stability of the energy cabin frame 10.

[0082] For example, the number of first interface sections of the first joint 3 can be two or three, so that one first joint 3 can simultaneously connect the main load-bearing pipe 220 and the second pipes 21 of two secondary load-bearing pipe groups 23, or, one first joint 3 can simultaneously connect the main load-bearing pipe 220 and the second pipes 21 of three secondary load-bearing pipe groups 23.

[0083] For example, the first interface section and the second tube 21 of the secondary load-bearing pipe group 23 can be connected by gluing. Since the secondary load-bearing pipe group 23 mainly bears the role of force transmission, the requirements for connection reliability are relatively low. The first joint 3 is connected to the second tube 21 of the secondary load-bearing pipe group 23 by gluing. There is no need to additionally process threads on the first joint 3 and the second tube 21 of the secondary load-bearing pipe group 23. The design flexibility of the first joint 3 and the second tube 21 of the secondary load-bearing pipe group 23 can be improved, and the load can be dispersed to avoid stress concentration problems.

[0084] Preferably, after the first interface section is glued to the second tube 21 of the secondary load-bearing pipe group 23, secondary gluing is performed through a three-dimensional woven short sleeve, which can protect the connection position between the first interface section and the second tube 21 of the secondary load-bearing pipe group 23 and further improve the overall bonding strength of the energy cabin frame 10.

[0085] Further, refer to the attached Figure 3 As shown, the second joint 4 is separated from the first joint 3, and the second joint 4 has multiple second interface sections, which are used to connect to the second tube 21. It can realize that one second joint 4 is connected to multiple second tubes 21 at the same time, reducing the number of components of the energy cabin frame 10 and ensuring the integrity and stability of the energy cabin frame 10.

[0086] For example, the second joint 4 may have three or four second interface sections, so that the second joint 4 can simultaneously connect the second pipes 21 of three secondary load-bearing pipe groups 23 or the second pipes 21 of four secondary load-bearing pipe groups 23 .

[0087] For example, the second interface section and the second pipe 21 can be connected by gluing. Since the parts of the main load-bearing pipe 220 except the end away from the transition frame 1 and the secondary load-bearing pipe group 23 are mainly responsible for transmitting force, the requirements for connection reliability are relatively low. The second joint 4 and the second pipe 21 are connected by gluing, and there is no need to additionally process threads on the second joint 4 and the second pipe 21. The flexibility of the design of the second joint 4 and the second pipe 21 can be improved, and the load can be dispersed to avoid stress concentration problems.

[0088] It should be noted that the bonding gap between the first interface section and the second tube 21 of the secondary load-bearing pipe group 23 is 0.1mm-0.15mm, which can ensure the bonding strength between the first interface section and the second tube 21 of the secondary load-bearing pipe group 23, and ensure the connection reliability between the first joint 3 and the second tube 21 of the secondary load-bearing pipe group 23. The bonding gap between the second interface section and the second tube 21 is 0.1mm-0.15mm, which can ensure the bonding strength between the second interface section and the second tube 21, and ensure the connection reliability between the second joint 4 and the second tube 21.

[0089] In a further embodiment of the present invention, the first joint 3 and / or the second joint 4 is a titanium alloy part. It can be understood that, considering the electrochemical effect of carbon fiber and metal, by making the first joint 3 and / or the second joint 4 a titanium alloy part, the possibility of electrochemical corrosion can be reduced, the safety and reliability of the second tube 21, the first joint 3 and / or the second joint 4 can be ensured, the service life of the energy cabin frame 10 can be extended, and the safety of the near-space airship can be ensured.

[0090] It is understandable that only the first joint 3 may be a titanium alloy part and the second joint 4 may not be a titanium alloy part; only the second joint 4 may be a titanium alloy part and the first joint 3 may not be a titanium alloy part; or both the first joint 3 and the second joint 4 may be titanium alloy parts.

[0091] In some embodiments of the present invention, Figure 3 and attached Figure 5 As shown, the energy cabin frame 10 also includes a mounting plate 5. At least part of the secondary load-bearing pipe group 23 is provided with a mounting plate 5. The mounting plate 5 is made of carbon fiber material. According to the installation requirements of the internal equipment of the energy cabin system 100, holes are punched on the mounting plate 5 to install equipment such as batteries 30. Figure 4As shown, the mounting plate 5 and the secondary load-bearing pipe group 23 are detachably connected by a buckle 51, which can meet the reuse of the main structural parts of the energy cabin system 100 after the energy cabin system 100 is completely recovered when different load requirements are close.

[0092] It should be noted that, refer to the attached Figure 3 As shown, mounting plates 5 are placed on all secondary load-bearing pipe groups 23 except the secondary load-bearing pipe group 23 closest to the transition frame 1, thereby realizing a multi-layer design of the battery 30 and making full use of the space of the energy cabin frame 10 in the first direction.

[0093] For example, Figure 3 As shown, there are three secondary load-bearing pipe groups 23, and the three secondary load-bearing pipe groups 23 include two first pipe groups 231 and one second pipe group 232. The two first pipe groups 231 are respectively connected to the two ends of the main load-bearing pipe group 22 along the first direction, and the second pipe group 232 is connected to the middle area of ​​the main load-bearing pipe group 22 along the first direction. The second pipe group 232 is connected to eight of the ten main load-bearing pipes 220 and is spaced apart from the remaining two. A mounting plate 5 is placed on the one of the two first pipe groups 231 away from the transition frame 1 and the second pipe group 232. The area opposite to 32 and the area on the second tube group 232 can be used to place the battery 30, and the area on the one of the two first tube groups 231 away from the transition frame 1 that is not opposite to the second tube group 232 is used to place the power supply equipment 40, so that on the basis of ensuring that the placement space of the power supply equipment 40 is relatively independent, the double-layer design of the energy cabin frame 10 can be realized, so that the space of the energy cabin frame 10 in the first direction can be fully utilized, the occupied space of the energy cabin frame 10 in the plane perpendicular to the first direction can be reduced, and the energy cabin frame 10 can be reasonably arranged, which is beneficial to the force and force transmission of the energy cabin frame 10.

[0094] Preferably, if Figure 3 and Figure 5 As shown, the mounting plate 5 has weight-reducing holes 52 , which can reduce the weight of the mounting plate 5 as much as possible while ensuring the normal installation of the battery 30 , thereby facilitating the lightweight design of the energy cabin frame 10 .

[0095] The present invention also provides an energy cabin system 100 having the energy cabin frame 10 of the above embodiment.

[0096] like Figure 1 and Figure 2 As shown, the energy cabin system 100 according to an embodiment of the present invention includes the above-mentioned energy cabin frame 10, protective plate 20, battery 30 and power supply equipment 40.

[0097] Specifically, refer to the attached Figure 1 and attached Figure 2As shown, combined with the reference Figure 3 The energy cabin frame 10 serves as the core structure of the energy cabin system 100, responsible for bearing and transmitting force. The protective plate 20 covers the main body 2 to define a cavity 201. The battery 30 and power supply device 40 are both located in the cavity 201. The protective plate 20 is assembled into a closed body, which can protect the battery 30, power supply device 40 and other components located in the cavity 201. It can also perform passive thermal insulation control, so that the battery 30, power supply device 40 and other components located in the cavity 201 are kept in a suitable temperature environment. At the same time, the protective plate 20 can provide electromagnetic shielding. At the same time, it can achieve modularization and functional integration of the energy cabin system 100.

[0098] Further, refer to the attached Figure 1 As shown, the protective plate 20 is detachably connected to the main body 2, which can facilitate the assembly and disassembly of the protective plate 20, thereby facilitating the assembly and maintenance of the energy cabin system 100, reducing the assembly cost and maintenance cost of the energy cabin system 100, and improving the assembly efficiency and maintenance efficiency of the energy cabin system 100.

[0099] For details, please refer to the attached Figure 1 As shown, there are multiple protective plates 20 corresponding one-to-one to the side walls of the main body 2. Each protective plate 20 is provided with multiple U-shaped members 207 on its circumferential wall. The multiple U-shaped members 207 on the same protective plate 20 are spaced apart in the circumferential direction of the protective plate 20. The protective plate 20 is clamped within the U-shaped members 207. Fasteners pass through the U-shaped members 207 and the protective plate 20 to achieve a fixed connection between the U-shaped members 207 and the protective plate 20. Two adjacent protective plates 20 are indirectly connected via the U-shaped members 207, thereby forming a closed, integrated structure. The multiple protective plates 20 protect the main body 2 and define the cavity 201. Furthermore, the provision of the U-shaped members 207 ensures the strength, connection rigidity, and integrity of the protective plate 20, thereby improving the reliability of the protective plate 20.

[0100] According to the energy cabin system 100 of the embodiment of the present invention, the energy cabin frame 10 is provided with the above-mentioned energy cabin frame 10, the transition frame 1 includes multiple first tubes 11, and the main body 2 includes multiple second tubes 21. The first tubes 11 and the second tubes 21 are both three-dimensional multi-directional braided tubes. The three-dimensional multi-directional braided tubes are braided and solidified with carbon fiber composite materials, so that the first tubes 11 and the second tubes 21 can evenly bear the load when subjected to force, and can optimize the mechanical properties and functional performance of the transition frame 1 and the main body 2, increase the structural efficiency of the transition frame 1 and the main body 2, improve the stress level of the transition frame 1 and the main body 2, improve the reliability and safety of the energy cabin frame 10, and can reduce the weight of the transition frame 1 and the main body 2, which is conducive to the lightweight design of the energy cabin frame 10, and provides additional redundant space for the energy payload to be carried on the near-space aerostat platform. The weight saved by the energy cabin frame 10 can be left to the energy, thereby indirectly increasing the endurance of the near-space aerostat.

[0101] In some embodiments of the present invention, Figure 2 As shown, the cavity 201 includes a first cavity 202 and a second cavity 203 arranged in the second direction. The battery 30 is located in the first cavity 202. The inner wall of the first cavity 202 is affixed with a shielding film. The second direction is perpendicular to the first direction. The setting of the shielding film can enhance the effectiveness of electromagnetic shielding and improve the working stability of the equipment in the first cavity 202 in extreme environments (5KPa, -90°C).

[0102] Further, refer to the attached Figure 2 As shown, the power supply device 40 is arranged in the second cavity 203. The second cavity 203 is a relatively independent compartment, which can separate the power supply device 40 from other components in the energy cabin system 100, avoid mutual interference between the power supply device 40 and other components in the energy cabin system 100, improve the electromagnetic shielding performance of the second cavity 203, and enable the second cavity 203 to have temperature control isolation performance.

[0103] Furthermore, in conjunction with the reference Figure 1 and attached Figure 2 The protective plate 20 has a wire outlet hole 206 on the inner wall of the inner wall defining the second cavity 203 on the side facing the transition frame 1. The wire outlet hole 206 is arranged opposite to the power supply device 40, and can allow the connecting cable of the power supply device 40 to pass through the energy cabin system 100 to be connected to other structures of the nearby space airship.

[0104] In a specific example, with reference to the attached Figure 1 and attached Figure 2Two power supply devices 40 are placed in the second cavity 203, and the two power supply devices 40 are spaced apart in the third direction. The inner wall of the protective plate 20 that defines the second cavity 203 and faces the transition frame 1 has two wire outlet holes 206. In the first direction, the two wire outlet holes 206 correspond one-to-one to the two power supply devices 40, which can relatively reduce the required length of the connection cable of the power supply device 40.

[0105] In a further embodiment of the present invention, referring to the attached Figure 1 As shown, the side wall of the protective plate 20 that defines the second cavity 203 has a first opening 204, and a protective film 205 is attached to the first opening 204. The protective film 205 is a flexible film. Specifically, the protective film 205 is a composite material. The setting of the protective film 205 can block the first opening 204. When working at night, the semi-enclosed body formed by the side sac can achieve passive thermal insulation protection, thereby achieving thermal insulation for the power supply equipment 40 in the second cavity 203 at night.

[0106] In a further embodiment of the present invention, the shielding membrane is an aluminum film or a copper foil. When the shielding membrane is an aluminum film, the weight of the shielding membrane can be reduced, which is beneficial to the lightweight design of the energy cabin system 100, can facilitate the production and processing of the shielding membrane, reduce the production and processing cost of the shielding membrane, and improve the production efficiency of the shielding membrane; when the shielding membrane is a copper foil, since copper has extremely high conductivity, it can effectively reflect electromagnetic waves and reduce the penetration of electromagnetic waves, thereby improving the shielding effectiveness of the shielding membrane, and can improve the structural strength of the shielding membrane to ensure the integrity and reliability of the shielding membrane.

[0107] In a further embodiment of the present invention, a second opening is provided on the inner wall of the protective plate 20 that defines the second cavity 203 and is away from the transition rack 1. The power supply device 40 is arranged opposite to the second opening, so that the heat dissipation fins at the bottom of the power supply device 40 can be exposed to the environment, ensuring that the power supply device 40 can quickly dissipate heat when working during the day.

[0108] In some embodiments of the present invention, the protective plate 20 is a plastic part, which can reduce the weight of the protective plate 20 and is conducive to the lightweight design of the energy cabin system 100. The plastic part has strong corrosion resistance, which can ensure the reliability of the protective plate 20 and extend the service life of the energy cabin system 100. In addition, the plastic parts have various processing methods and fast molding speed, which can reduce the production and processing costs of the protective plate 20.

[0109] Specifically, the protective plate 20 is a PMI (polymethyl methacrylate) foam board or a polytetrafluoroethylene board. When the protective plate 20 is a PMI foam board, since the PMI foam board has the characteristics of light weight, high temperature resistance, and easy processing, the weight of the protective plate 20 can be reduced, which is beneficial to the lightweight design of the energy cabin system 100, and can facilitate the production and processing of the protective plate 20, reduce the production and processing costs of the energy cabin system 100, and ensure the stability and reliability of the protective plate 20. In addition, the PMI foam board has good waterproof and moisture-proof properties, and can effectively prevent moisture and water from penetrating into the cavity 201, thereby preventing water from entering the energy cabin system 100; when the protective plate 20 is a polytetrafluoroethylene board, the polytetrafluoroethylene board has the advantages of high temperature resistance, low temperature resistance, corrosion resistance, and weather resistance, which can ensure the stability and reliability of the protective plate 20 and extend the service life of the protective plate 20.

[0110] In some embodiments of the present invention, Figure 1 As shown, the energy cabin system 100 also includes a carbon strip 50, which is arranged on the outer wall surface of the protective plate 20. The carbon strip 50 can divide the protective plate 20 into multiple small areas, improve the structural strength of the protective plate 20, and play a role in transmitting force.

[0111] Furthermore, the carbon strip 50 is detachably connected to the protective plate 20, which can facilitate the assembly and disassembly of the carbon strip 50, thereby facilitating the assembly and maintenance of the energy cabin system 100, reducing the assembly cost and maintenance cost of the energy cabin system 100, and improving the assembly efficiency and maintenance efficiency of the energy cabin system 100.

[0112] For details, please refer to the attached Figure 1 As shown, there are multiple protective plates 20 corresponding one to one with the side walls of the main body 2, and multiple U-shaped parts 207 are provided on the peripheral wall of each protective plate 20. The multiple U-shaped parts 207 on the same protective plate 20 are arranged at intervals in the circumferential direction of the protective plate 20. Carbon strips 50 are provided on the outer wall surfaces of at least part of the protective plates 20. The protective plates 20, the carbon strips 50 and the U-shaped parts 207 are fixedly connected by fasteners, so that under the joint action of the protective plates 20, the carbon strips 50 and the U-shaped parts 207, a cavity 201 is formed, and the carbon strips 50 can ensure the connection strength between the protective plates 20.

[0113] The present invention also provides a near-space aerostat having the energy cabin system 100 of the above embodiment.

[0114] According to an embodiment of the present invention, the near-space aerostat is provided with the above-mentioned energy cabin system 100. The transition frame 1 includes a plurality of first tubes 11, and the main body 2 includes a plurality of second tubes 21. The first tubes 11 and the second tubes 21 are both three-dimensional multi-directional braided tubes. The three-dimensional multi-directional braided tubes are braided and solidified from carbon fiber composite materials, so that the first tubes 11 and the second tubes 21 can evenly bear the load when subjected to force, thereby optimizing the mechanical properties and functional performance of the transition frame 1 and the main body 2, increasing the structural efficiency of the transition frame 1 and the main body 2, improving the stress levels of the transition frame 1 and the main body 2, and improving the reliability and safety of the energy cabin frame 10. The weight of the transition frame 1 and the main body 2 can be reduced, which is conducive to the lightweight design of the energy cabin frame 10, providing additional redundant space for the energy payload to be carried on the near-space aerostat platform, and the weight saved by the energy cabin frame 10 can be reserved for energy, thereby indirectly increasing the endurance of the near-space aerostat.

[0115] Other structures and operations of the energy capsule frame 10, the energy capsule system 100 and the near-space aerostat according to the embodiment of the present invention are well known to those skilled in the art and will not be described in detail here.

[0116] In the description of this specification, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example 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 can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0117] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to the embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the claims and their equivalents.

Claims

1. An energy cabin frame, characterized in that: For use with near-space aerostats and comprising: a transition frame, the transition frame being installed on the sphere of the near-space aerostat and located on one side of the sphere along a first direction, the transition frame comprising a plurality of first tubes; The main body is arranged on the side of the transition frame away from the sphere, and the main body includes a plurality of second tubes, the first tubes and the second tubes are both three-dimensional multi-directional braided tubes, and the three-dimensional multi-directional braided tubes are braided and cured from carbon fiber composite materials.

2. The energy cabin frame according to claim 1, characterized in that: The multiple second tubes include a main load-bearing tube group and multiple secondary load-bearing tube groups. The main load-bearing tube group includes multiple main load-bearing tubes extending along the first direction. The multiple main load-bearing tubes are arranged at intervals along the circumferential direction of the main body. The multiple secondary load-bearing tube groups are arranged and spaced apart along the first direction. The multiple secondary load-bearing tube groups are all connected to the main load-bearing tube group.

3. The energy cabin frame according to claim 2, characterized in that: At least part of the multiple secondary load-bearing pipe groups is a first pipe group, each of the main load-bearing pipes is connected to the first pipe group, the first pipe group includes multiple first sub-pipes and multiple second sub-pipes, the multiple first sub-pipes all extend along the second direction and are spaced apart in the third direction, the multiple second sub-pipes all extend along the third direction and are spaced apart in the second direction, the multiple first sub-pipes and the multiple second sub-pipes are staggered, and the first direction, the second direction and the third direction are perpendicular to each other.

4. The energy cabin frame according to claim 2, characterized in that: Part of the multiple secondary load-bearing pipe groups is a second pipe group, the second pipe group is connected to part of the main load-bearing pipes, and the second pipe group is separated from the main load-bearing pipes at one end of the multiple main load-bearing pipes in the second direction, and the second direction is perpendicular to the first direction.

5. The energy cabin frame according to claim 2, characterized in that: The plurality of second tubes further include a third tube group, which includes a plurality of third sub-tubes extending along the first direction. The third sub-tubes are spaced apart from the main load-bearing tubes and are used to connect two adjacent secondary load-bearing tube groups.

6. The energy cabin frame according to any one of claims 2 to 5, characterized in that: The main load-bearing pipe is a three-dimensional five-directional braided pipe; and / or the second pipe of the secondary load-bearing pipe group is a three-dimensional four-directional braided pipe.

7. The energy cabin frame according to claim 2, characterized in that: Both ends of the main load-bearing pipe along the first direction are provided with licker-in joints, the licker-in joints are embedded in the main load-bearing pipe, and the licker-in joints and the main load-bearing pipe are an integrated piece.

8. The energy cabin frame according to claim 2, characterized in that: The energy cabin frame also includes: a first joint, the first joint comprising a threaded section and a plurality of first interface sections, the threaded section being used for threaded connection with an end of the primary load-bearing pipe facing away from the transition frame, and the first interface section being used for connection with the second pipe of the secondary load-bearing pipe group; A second joint is spaced apart from the first joint, and has a plurality of second interface sections, wherein the second interface sections are used to be connected to the second pipe.

9. The energy cabin frame according to claim 8, characterized in that: The first joint and / or the second joint are / is made of titanium alloy.

10. The energy cabin frame according to claim 2, characterized in that: The energy cabin frame also includes: A mounting plate is provided on at least part of the secondary load-bearing pipe group.

11. An energy cabin system, characterized in that: include: The energy cabin frame according to any one of claims 1 to 10; a protective plate, the protective plate covering the main body to define a cavity, the protective plate being detachably connected to the main body; A battery and a power supply device, wherein the battery and the power supply device are both arranged in the cavity.

12. The energy cabin system according to claim 11, characterized in that: The cavity includes a first cavity and a second cavity arranged in a second direction, the battery is located in the first cavity, the inner wall of the first cavity is provided with a shielding film, the power supply device is located in the second cavity, and the second direction is perpendicular to the first direction.

13. The energy cabin system according to claim 12, characterized in that: A first opening is formed on a side wall of the protective plate that defines the second cavity, and a protective film is attached to the first opening.

14. The energy cabin system according to claim 12, characterized in that: The shielding film is an aluminum film or a copper foil.

15. The energy cabin system according to claim 12, characterized in that: A second opening is provided on the inner wall of the protective plate on the side facing away from the transition frame in the inner wall defining the second cavity, and the power supply device is arranged opposite to the second opening.

16. The energy cabin system according to claim 11, characterized in that: The protective plate is a plastic part.

17. The energy cabin system according to claim 11, characterized in that: Also includes: A carbon strip is provided on the outer wall surface of the protective plate, and the carbon strip is detachably connected to the protective plate.

18. A near-space aerostat, characterized in that: Comprising an energy cabin system according to any one of claims 11-17.

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