Reusable multifunctional cabin section structure of aircraft

Abstract

The invention relates to the technical field of space flight and aviation, in particular to a reusable aircraft multifunctional cabin section structure which comprises an arc top cover assembly, an upper end frame, an upper cylinder section, a lower cylinder section, a lower end frame, two groups of ring frames and a plurality of longitudinal bars. The lower end of the upper cylinder section is welded with the upper end of the lower cylinder section; the upper end of the upper cylinder section is welded with the lower end of the upper end frame; the lower end of the lower cylinder section is welded with the upper end of the lower end frame; the edge position of the arc top cover assembly is connected with the upper end of the upper end frame through bolts. One group of ring frames are circumferentially connected to the inner side of the welding joint of the upper cylinder section and the lower cylinder section, and the other group of ring frames are circumferentially connected to the inner side of the position, close to the lower end frame, of the lower cylinder section; and all the longitudinal ribs are axially connected to the inner sides of the upper cylinder section and the lower cylinder section. The reusable aircraft multifunctional cabin section structure is formed by welding stainless steel, the main force bearing component is located on the inner side of the cabin body, and the reusable aircraft multifunctional cabin section structure has the advantages of being mature in process, high in structural integrity, good in aerodynamic shape, high in bearing capacity and the like.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to a multi-functional compartment structure for a reusable aircraft. Background Technology

[0002] Currently, the main structural forms of launch vehicle modules include skin-reinforced structures, monocoque structures, semi-monocoque structures, integral panel structures, and composite material structures. Skin-reinforced structures consist of a thin skin and regularly distributed reinforcing ribs, joined by welding or riveting. Monocoque structures consist of a relatively thick skin and densely distributed bulkheads, with the skin being the primary load-bearing component. Semi-monocoque structures are a compromise between skin-reinforced and monocoque structures, with the skin, bulkheads, and reinforcing ribs sharing the load. Integral panel structures are grid-reinforced structures produced by mechanical milling or chemical milling. Composite material structures are made from fiber-reinforced resin-based composite materials such as carbon fiber, through processes such as winding and laying.

[0003] Among them, the skin-reinforced structure involves a large amount of riveting work, with a large number of rivets and difficulty in controlling the consistency of the process; the partition of the rigid shell structure only serves to maintain the shape and disperse concentrated forces, and is not a main load-bearing structure, resulting in low material utilization; the semi-rigid shell structure combines the structural advantages of the former two, with high load-bearing efficiency and strong load-bearing capacity, but the structure is more complex; the integral wall panel structure requires integrated processing, which has a long processing time, high manufacturing cost, and limited applicable size; composite material structures have problems such as difficulty in quality control and sensitivity to the environment.

[0004] Therefore, how to make the manufacturing process of the compartment mature, the structure of the compartment simple and highly complete, the aerodynamic shape of the compartment good, and the load-bearing capacity of the compartment strong are technical problems that urgently need to be solved by those skilled in the art. Summary of the Invention

[0005] This application provides a multi-functional cabin structure for a reusable aircraft. Its main structure is formed by welding stainless steel, and the main load-bearing components are located inside the cabin. It has the advantages of mature technology, high structural integrity, good aerodynamic shape, and strong load-bearing capacity.

[0006] To solve the above-mentioned technical problems, this application provides the following technical solution:

[0007] A reusable aircraft multi-functional compartment structure includes: an arc-shaped dome assembly, an upper frame, an upper cylindrical section, a lower cylindrical section, a lower frame, two sets of ring frames, and multiple longitudinal ribs; wherein, the lower end of the upper cylindrical section is welded to the upper end of the lower cylindrical section, the upper end of the upper cylindrical section is welded to the lower end of the upper frame, and the lower end of the lower cylindrical section is welded to the upper end of the lower frame; the edge of the arc-shaped dome assembly is bolted to the upper end of the upper frame; one set of ring frames is circumferentially connected to the inner side of the welded connection between the upper and lower cylindrical sections, and another set of ring frames is circumferentially connected to the inner side of the lower cylindrical section near the lower frame; all longitudinal ribs are axially connected to the inner sides of the upper and lower cylindrical sections.

[0008] In the reusable aircraft multi-functional compartment structure described above, preferably, multiple through-hole nozzle mounting holes are provided on the upper cylinder section near the upper end frame, and all nozzle mounting holes are evenly distributed on the same circumference; a nozzle mounting seat is connected near each nozzle mounting hole on the inner side of the upper cylinder section for mounting the nozzle on the nozzle mounting seat, and the nozzle extends outward from the nozzle mounting hole.

[0009] In the reusable aircraft multi-functional compartment structure described above, preferably, an instrument mounting plate is circumferentially connected to the middle part of the inner side of the upper cylinder section; multiple solenoid valve mounting seats are connected to the inner side of the upper cylinder section, all solenoid valve mounting seats are evenly distributed on the same circumference, and all solenoid valve mounting seats are located between the nozzle mounting hole and the instrument mounting plate.

[0010] In the reusable aircraft multi-functional compartment structure described above, preferably, four sets of antenna mounting brackets and antenna protective covers are connected to the outer side of the upper tube section. Each antenna protective cover surrounds an antenna mounting bracket above and to the side, and all antenna protective covers and all antenna mounting brackets are located between the instrument mounting plate and the lower end of the upper tube section.

[0011] In the reusable aircraft multi-functional compartment structure described above, preferably, multiple gas cylinder supports are connected to the inner sides of both the upper and lower cylinder sections; wherein, all gas cylinder supports on the inner side of the upper cylinder section are evenly distributed on the same circumference, and the lower ends of all gas cylinder supports on the inner side of the upper cylinder section are located at the upper end of the ring frame at the connection between the upper and lower cylinder sections; all gas cylinder supports on the inner side of the lower cylinder section are evenly distributed on the same circumference, and the upper ends of all gas cylinder supports on the inner side of the lower cylinder section are located at the lower end of the ring frame on the inner side of the lower cylinder section.

[0012] The reusable aircraft multi-functional compartment structure described above preferably includes an arc-shaped dome assembly comprising an arc-shaped dome body and a connecting wing plate; wherein the connecting wing plate is connected to the edge of the arc-shaped dome body and has multiple connecting holes for connecting to the upper end of the upper frame via bolts.

[0013] In the reusable aircraft multi-functional compartment structure described above, preferably, an arc-shaped operating port is provided on the arc-shaped dome body, and an arc-shaped operating port cover is connected to the outside of the arc-shaped dome body to close the arc-shaped operating port; an arc-shaped operating port frame is connected to the inside of the arc-shaped dome body, and the arc-shaped operating port frame is located around the arc-shaped operating port.

[0014] In the reusable aircraft multi-functional compartment structure described above, preferably, the dome body has a separation and disengagement port, and a separation and disengagement port cover is connected to the outside of the dome body to close the separation and disengagement port; wherein, the upper edge of the separation and disengagement port cover is hinged to the dome body through a hinge mechanism, and the left and right sides of the separation and disengagement port cover are locked to the dome body through a locking mechanism.

[0015] The reusable aircraft multi-functional compartment structure described above preferably includes a hinge mechanism comprising: a hinge support, a torsion spring, a pin, and a limiting sleeve; wherein the hinge support is connected to the dome cover body, the pin passes through the hinge support and the upper edge of the separation / disconnection port cover, the separation / disconnection port cover is rotatable about the pin, the torsion spring and the limiting sleeve are mounted on the pin to provide preload to the separation / disconnection port cover via the torsion spring, and the limiting sleeve prevents axial sliding and radial displacement of the torsion spring.

[0016] The reusable aircraft multi-functional compartment structure described above preferably includes a hinge mechanism and a locking mechanism, comprising: a release mounting base, a locking tongue, a compression spring, a pull-out rod, and a baffle; wherein the release mounting base is connected to the dome cover body and has a through release hole; the left and right sides of the release cover have insertion holes, the locking tongue is inserted into the release hole, and its front end can extend out of the release hole and be inserted into the insertion hole; the compression spring is located in the release hole and is sleeved on the rear section of the locking tongue; the baffle has a through insertion hole, the baffle is fixedly connected to the release mounting base, and prevents the compression spring from disengaging from the release hole; the front section of the pull-out rod passes through the insertion hole and is inserted into the release hole to connect with the rear section of the locking tongue, and the rear section of the pull-out rod is located externally.

[0017] The beneficial effects of this application are:

[0018] 1. The compartment structure adopts stainless steel welding, which is a mature process with low material cost and wide material adaptability. By selecting appropriate welding parameters, the adverse effects on the performance of the base material can be minimized, and a large amount of riveting work is avoided, resulting in high integrity of the compartment structure, smooth and continuous force transmission, and high load-bearing capacity.

[0019] 2. The longitudinal ribs and other reinforcing components are located on the inside of the compartment, which reduces the flight drag of the rocket body in the atmosphere.

[0020] 3. An arc-shaped top cover assembly is provided at the upper frame, which can maintain good aerodynamic characteristics during the return phase. The separation and insertion port cover on the arc-shaped top cover can automatically lock after separation to prevent airflow from entering the cabin and damaging the insertion / disconnection and instruments and equipment.

[0021] 4. The compartment structure has instrument mounting plates and gas cylinder brackets, which can integrate the avionics system and the air-cooled attitude control system into one compartment, making the structure compact and the space utilization rate high. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0023] Figure 1 This is a schematic diagram of the reusable aircraft multi-functional compartment structure provided in the embodiments of this application;

[0024] Figure 2 This is a cross-sectional view of the reusable aircraft multi-functional compartment structure provided in the embodiments of this application;

[0025] Figure 3 This is a top view of the reusable aircraft multi-functional compartment structure provided in the embodiments of this application;

[0026] Figure 4 This is a partial view of the reusable aircraft multi-functional compartment structure provided in the embodiments of this application. Detailed Implementation

[0027] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0028] Figure 1 and Figure 2 As shown, this application provides a reusable aircraft multi-functional compartment structure, including: an arc-shaped dome assembly 10, an upper frame 20, an upper cylindrical section 30, a lower cylindrical section 40, a lower frame 50, two sets of ring frames 60, and multiple longitudinal ribs 70.

[0029] The lower end of the upper cylinder section 30 is welded to the upper end of the lower cylinder section 40, the upper end of the upper cylinder section 30 is welded to the lower end of the upper end frame 20, and the lower end of the lower cylinder section 40 is welded to the upper end of the lower end frame 50; the edge of the arc top cover assembly 10 is connected to the upper end of the upper end frame 20 by bolts; a set of ring frames 60 are circumferentially connected to the inner side of the welded connection between the upper cylinder section 30 and the lower cylinder section 40, and another set of ring frames 60 are circumferentially connected to the inner side of the lower cylinder section 40 near the lower end frame 50; all longitudinal ribs 70 are axially connected to the inner side of the upper cylinder section 30 and the lower cylinder section 40.

[0030] Optionally, the lower end of the upper cylinder section 30 and the upper end of the lower cylinder section 40 are connected together by laser welding, and the upper end of the upper cylinder section 30 and the lower end of the upper frame 20, as well as the lower end of the lower cylinder section 40 and the upper end of the lower frame 50, are connected together by laser welding. Alternatively, the cross-sectional shape of the ring frame 60 and the longitudinal rib 70 is a "U" shape. Still optional, the ring frame 60 and the longitudinal rib 70 are connected to the inner sides of the upper cylinder section 30 and the lower cylinder section 40 by riveting or welding. Again optional, the arc-shaped dome assembly 10, the upper frame 20, the upper cylinder section 30, the lower cylinder section 40, the lower frame 50, the ring frame 60, and the longitudinal rib 70 are all made of stainless steel.

[0031] Multiple through-holes 31 for nozzle mounting are provided on the upper cylinder section 30 near the upper frame 20. All nozzle mounting holes 31 are evenly distributed on the same circumference. A nozzle mounting seat 80 is connected near each nozzle mounting hole 31 on the inner side of the upper cylinder section 30 for mounting the nozzle on the nozzle mounting seat 80, with the nozzle extending outward from the nozzle mounting hole 31. Optionally, all nozzle mounting seats 80 are located on the same circumference. Alternatively, all nozzle mounting seats 80 and all nozzle mounting holes 31 are located on the same circumference.

[0032] Additionally, an instrument mounting plate 100 is circumferentially connected to the middle inner side of the upper cylinder section 30 for mounting various avionics instruments and equipment. Multiple solenoid valve mounting seats 90 are connected to the inner side of the upper cylinder section 30, all evenly distributed on the same circumference, and all located between the nozzle mounting hole 31 and the instrument mounting plate 100. Optionally, the instrument mounting plate 100 is divided into an upper plate and a lower plate, with an I-beam 110 connecting the upper and lower plates for support. Again, optionally, the I-beams 110 intersect to form a grid-like support beam.

[0033] In addition, four sets of antenna mounting brackets 130 and antenna protective covers 120 are connected to the outer side of the upper cylindrical section 30. Each antenna protective cover 120 surrounds the top and side of an antenna mounting bracket 130. The antenna mounting brackets 130 are used to mount different types of antennas, and the antenna protective covers 120 are used to prevent the antennas mounted on the antenna mounting brackets 130 from being eroded by airflow. All antenna protective covers 120 and all antenna mounting brackets 130 are located between the instrument mounting plate 100 and the lower end of the upper cylindrical section 30. Optionally, the outer surface of the antenna protective cover 120 is streamlined to facilitate airflow.

[0034] In addition, multiple gas cylinder supports 140 are connected to the inner sides of the upper cylinder section 30 and the lower cylinder section 40 for installing gas cylinders. Among them, all the gas cylinder supports 140 on the inner side of the upper cylinder section 30 are evenly distributed on the same circumference, and the lower ends of all the gas cylinder supports 140 on the inner side of the upper cylinder section 30 are located at the upper end of the ring frame 60 at the connection between the upper cylinder section 30 and the lower cylinder section 40. All the gas cylinder supports 140 on the inner side of the lower cylinder section 40 are evenly distributed on the same circumference, and the upper ends of all the gas cylinder supports 140 on the inner side of the lower cylinder section 40 are located at the lower end of the ring frame 60 on the inner side of the lower cylinder section 40.

[0035] Based on the above, a cylinder support reinforcing rib 150 is connected between the lower end of all cylinder supports 140 inside the upper cylinder section 30 and the lower end of the ring frame 60 located at the connection between the upper cylinder section 30 and the lower cylinder section 40, and a cylinder support reinforcing rib 150 is connected between the upper end of all cylinder supports 140 inside the lower cylinder section 40 and the upper end of the ring frame 60 located in the lower cylinder section 40, thereby enhancing the strength of the cylinder supports 140 through the cylinder support reinforcing ribs 150. Optionally, four sets of cylinder supports 140 are distributed inside the upper cylinder section 30, and four sets of cylinder supports 140 are distributed inside the lower cylinder section 40.

[0036] Because the diameter of the compartment is small, multiple operating ports are provided on the lower cylinder section 40. The operating ports are located between two ring frames 60 and are used to apply tightening torque and insert or remove instrument and equipment connectors. An operating port cover 160 is connected to the outside of the lower cylinder section 40 to close the operating port. A port frame 170 is connected to the inside of the lower cylinder section 40 and is located around the operating port to strengthen the strength of the operating port.

[0037] Additionally, a lifting point support plate 180, a multi-port bracket 190, and pipe clamps 200 are installed on the inner side of the lower cylinder section 40 near the lower end frame 50. The lifting point support plate 180 is used for lifting the entire rocket; the multi-port bracket 190 provides load-bearing support and connection for multi-channel media diversion, convergence, or reversal; and the pipe clamps 200 are used for fixing and connecting various pipes. Multiple wire clamps 210 are connected to the longitudinal ribs 70 for fixing various lines.

[0038] In addition, multiple explosive bolt buffer pads 220 are provided on the inner side of the upper frame 20, and all explosive bolt buffer pads 220 are evenly distributed on the same circumference to buffer the explosive impact of the explosive bolts. In order to facilitate the installation of the explosive bolt buffer pads 220 on the inner side of the upper frame 20, multiple mounting ports are provided on the upper frame 20, and the mounting ports are opposite to the explosive bolt buffer pads 220. Furthermore, mounting port covers are connected to the outer side of the upper frame 20 to close the mounting ports.

[0039] like Figure 3 As shown, the arc-shaped dome assembly 10 includes an arc-shaped dome body 11 and a connecting wing plate 12. The arc-shaped dome body 11 is an arc-shaped metal shell used to maintain a good aerodynamic shape during the return phase after separation and to prevent airflow from entering the cabin and damaging instruments and equipment. The connecting wing plate 12 is connected to the edge of the arc-shaped dome body 11 and has multiple connecting holes 121 for connecting to the upper end of the upper frame 20 via bolts. Optionally, all connecting holes 121 are evenly distributed circumferentially on the connecting wing plate 12. Alternatively, multiple grooves 122 penetrating the edge of the connecting wing plate 12 are also provided on the connecting wing plate 12, all grooves 122 being evenly distributed circumferentially on the connecting wing plate 12 to ensure that the connecting wing plate 12 remains flush with the upper surface of the upper frame 20 when it overlaps the upper frame 20.

[0040] In addition, an arc-shaped operating port is provided on the arc-shaped cover body 11 for operating instruments and equipment. An arc-shaped operating port cover 111 is connected to the outside of the arc-shaped cover body 11 to close the arc-shaped operating port. An arc-shaped operating port frame is connected to the inside of the arc-shaped cover body 11, and the arc-shaped operating port frame is located around the arc-shaped operating port to enhance the strength of the arc-shaped cover body 11.

[0041] In addition, four sets of separation spring ball sockets 112 are provided on the arc-shaped cover body 11 near the connecting wing plate 12 to accommodate the separation spring push rod and prevent the separation spring from moving. Optionally, the four sets of separation spring ball sockets 112 are evenly distributed on the same circumference.

[0042] Based on the above, a separation and disengagement port is also provided on the arc-shaped top cover body 11. The separation and disengagement port is located near the arc-shaped top operating port. A separation and disengagement port cover 113 is connected to the outside of the arc-shaped top cover body 11 to close the separation and disengagement port. The upper edge of the separation and disengagement port cover 113 is hinged to the arc-shaped top cover body 11 via a hinge mechanism 114, and the left and right sides of the separation and disengagement port cover 113 are locked to the arc-shaped top cover body 11 via a locking mechanism 115.

[0043] like Figure 4As shown, the hinge mechanism 114 includes: a hinge support 1141, a torsion spring 1142, a pin 1143, and a limiting sleeve 1144; wherein, the hinge support 1141 is connected to the arc-shaped top cover body 11, the pin 1143 passes through the hinge support 1141 and the upper edge of the separation and disengagement cover 113, so that the separation and disengagement cover 113 can rotate around the pin 1143, the torsion spring 1142 and the limiting sleeve 1144 are mounted on the pin 1143, so that the torsion spring 1142 provides preload to the separation and disengagement cover 113, and the limiting sleeve 1144 prevents the torsion spring 1142 from sliding axially and deviating radially.

[0044] The locking mechanism 115 includes: a release mounting base 1151, a locking tongue 1152, a compression spring 1153, a pull rod 1154, and a baffle 1155. The release mounting base 1151 is connected to the arc-shaped top cover body 11 and has a through release hole. The left and right sides of the release cover 113 have insertion holes. The locking tongue 1152 is inserted into the release hole, and its front end can extend out of the release hole and be inserted into the insertion hole. The compression spring 1153 is located in the release hole and is sleeved on the rear section of the locking tongue 1152. The baffle 1155 has a through insertion hole and is fixedly connected to the release mounting base 1151, preventing the compression spring 1153 from disengaging from the release hole. The front section of the pull rod 1154 passes through the insertion hole and is inserted into the release hole, connecting with the rear section of the locking tongue 1152. The rear section of the pull rod 1154 is located externally.

[0045] Before separation, the disconnector cover 113 is in the open state and rests against the disconnect cable. After separation, the disconnector cover 113 rotates in the closing direction under the action of the torsion spring 1142. The side of the disconnector cover 113 contacts and presses the locking tongue 1152, causing the locking tongue 1152 to move horizontally. The compression spring 1153 is compressed. When the disconnector cover 113 is rotated to the closed position, the locking tongue 1152 is inserted into the insertion hole on the side of the disconnector cover 1133 under the elastic force of the compression spring 1153, thereby achieving locking. The pull rod 1154 is used to pull the locking tongue 1152 out of the insertion hole to achieve unlocking. The unlocking operation is only used for ground testing.

[0046] The beneficial effects of this application are:

[0047] 1. The compartment structure adopts stainless steel welding, which is a mature process with low material cost and wide material adaptability. By selecting appropriate welding parameters, the adverse effects on the performance of the base material can be minimized, and a large amount of riveting work is avoided, resulting in high integrity of the compartment structure, smooth and continuous force transmission, and high load-bearing capacity.

[0048] 2. The longitudinal ribs and other reinforcing components are located on the inside of the compartment, which reduces the flight drag of the rocket body in the atmosphere.

[0049] 3. An arc-shaped top cover assembly is provided at the upper frame, which can maintain good aerodynamic characteristics during the return phase. The separation and insertion port cover on the arc-shaped top cover can automatically lock after separation to prevent airflow from entering the cabin and damaging the insertion / disconnection and instruments and equipment.

[0050] 4. The compartment structure has instrument mounting plates and gas cylinder brackets, which can integrate the avionics system and the air-cooled attitude control system into one compartment, making the structure compact and the space utilization rate high.

[0051] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0052] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A reusable aircraft multi-functional compartment structure, characterized in that, include: The components include an arc-shaped roof assembly, an upper frame, an upper cylindrical section, a lower cylindrical section, a lower frame, two sets of ring frames, and multiple longitudinal ribs. The lower end of the upper cylinder section is welded to the upper end of the lower cylinder section, and the upper end of the upper cylinder section is welded to the lower end of the upper frame, and the lower end of the lower cylinder section is welded to the upper end of the lower frame. The edge of the arched top cover assembly is connected to the upper end of the upper frame by bolts; One set of ring frames is circumferentially connected to the inner side of the welded connection between the upper and lower cylinder sections, and another set of ring frames is circumferentially connected to the inner side of the lower cylinder section near the lower end frame. All longitudinal reinforcement bars are axially connected to the inner sides of the upper and lower cylinder sections.

2. The reusable aircraft multi-functional compartment structure according to claim 1, characterized in that, Multiple nozzle mounting holes that penetrate the inside and outside are provided on the upper cylinder section near the upper end frame, and all nozzle mounting holes are evenly distributed on the same circumference. Near each nozzle mounting hole on the inner side of the upper cylinder section, there is a nozzle mounting seat for mounting the nozzle on the nozzle mounting seat, with the nozzle extending outward from the nozzle mounting hole.

3. The reusable aircraft multi-functional compartment structure according to claim 2, characterized in that, An instrument mounting plate is connected circumferentially to the middle part of the inner side of the upper cylinder section; multiple solenoid valve mounting seats are connected to the inner side of the upper cylinder section, all of which are evenly distributed on the same circumference and are located between the nozzle mounting hole and the instrument mounting plate.

4. The reusable aircraft multi-functional compartment structure according to claim 3, characterized in that, Four sets of antenna mounting brackets and antenna protective covers are connected to the outer side of the upper cylinder section; each antenna protective cover surrounds the top and side of an antenna mounting bracket, and all antenna protective covers and all antenna mounting brackets are located between the instrument mounting plate and the lower end of the upper cylinder section.

5. The reusable aircraft multi-functional compartment structure according to any one of claims 1 to 4, characterized in that, Multiple gas cylinder supports are connected to the inner side of both the upper and lower cylinder sections; Among them, all the gas cylinder supports inside the upper cylinder section are evenly distributed on the same circumference, and the lower ends of all the gas cylinder supports inside the upper cylinder section are located at the upper end of the ring frame at the connection between the upper cylinder section and the lower cylinder section. All the gas cylinder supports inside the lower cylinder section are evenly distributed on the same circumference, and the upper ends of all the gas cylinder supports inside the lower cylinder section are located at the lower end of the ring frame inside the lower cylinder section.

6. The reusable aircraft multi-functional compartment structure according to any one of claims 1 to 4, characterized in that, The dome assembly includes: the dome body and the connecting wing plate; The connecting wing plate is connected to the edge of the arc-shaped cover body, and multiple connecting holes are provided on the connecting wing plate for connecting to the upper end of the upper frame by bolts.

7. The reusable aircraft multi-functional compartment structure according to claim 6, characterized in that, An arc-shaped operating port is provided on the main body of the arc-shaped cover, and an arc-shaped operating port cover is connected to the outside of the main body of the arc-shaped cover to close the arc-shaped operating port. An arc-shaped operating frame is connected to the inner side of the arc-shaped cover body, and the arc-shaped operating frame is located around the arc-shaped operating port.

8. The reusable aircraft multi-functional compartment structure according to claim 6, characterized in that, The arc-shaped top cover body has a separation and disengagement port, and a separation and disengagement port cover is connected to the outside of the arc-shaped top cover body to close the separation and disengagement port. The upper edge of the detachable spigot cover is hinged to the arc-shaped top cover body via a hinge mechanism, and the left and right sides of the detachable spigot cover are locked to the arc-shaped top cover body via a locking mechanism.

9. The reusable aircraft multi-functional compartment structure according to claim 8, characterized in that, The articulation mechanism includes: an articulation support, a torsion spring, a pin, and a limiting sleeve; The hinged support is connected to the arc-shaped cover body, and the pin passes through the upper edge of the hinged support and the separation and disengagement cover. The separation and disengagement cover can rotate around the pin. The torsion spring and the limiting sleeve are installed on the pin to provide preload to the separation and disengagement cover through the torsion spring and to prevent axial sliding and radial displacement of the torsion spring through the limiting sleeve.

10. The reusable aircraft multi-functional compartment structure according to claim 8, characterized in that, The hinge mechanism and locking mechanism include: a release mounting base, a locking tongue, a compression spring, a pull rod, and a baffle. The release mounting base is connected to the arc-shaped top cover body and has a through release hole. The left and right sides of the release cover have insertion holes, and the locking tongue is inserted into the release hole, with its front end extending out of the release hole and inserted into the insertion hole. The compression spring is located in the release hole and is sleeved on the rear section of the locking tongue. A through insertion hole is provided on the baffle, which is fixedly connected to the release mounting base and prevents the compression spring from coming out of the release hole. The front section of the pull rod passes through the insertion hole and is inserted into the release hole to connect with the rear section of the locking tongue, with the rear section of the pull rod located on the outside.

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