A suborbital returnable payload capsule structure device

Abstract

This application provides a suborbital reentry payload compartment structure, which adopts a blunt-nosed conical integral configuration. The device includes a nose cap, a main structural conical section, an aerodynamic heat-resistant arc bottom, a parachute structure, a payload mounting disk, and a heat protection system. The nose cap is connected to the top of the main structural conical section, and the aerodynamic heat-resistant arc bottom is connected to the bottom of the main structural conical section. The nose cap is used to adjust the axial center of gravity of the entire compartment and bears the main impact load during landing. The parachute structure is located inside the main structural conical section and is integrated with it. The payload mounting disk is connected to the main structural conical section. The heat protection system is installed on the nose cap, the main structural conical section, the aerodynamic heat-resistant arc bottom, and / or the parachute cover of the parachute structure, and is used to reduce the internal temperature of the compartment. This application has a reasonable structural layout, high structural efficiency, good aerodynamic stability, and partial reusability.

Description

Technical Field

[0001] This application relates to the field of aerospace structural technology, and in particular to a suborbital returnable payload capsule structural device. Background Technology

[0002] Suborbital vehicles typically refer to spacecraft that fly at altitudes exceeding 100 km above the Kármán line but do not reach the first cosmic velocity. The payload bay of such reentry vehicles needs to be capable of atmospheric reentry, withstanding aerodynamic and thermal loads and impacts, and achieving safe recovery. However, existing suborbital payload bays suffer from the following structural design problems:

[0003] Parachute compartments are typically independent structures, occupying ≥15% of the internal space. Reinforcing the structure can increase the system weight by 10%–15%.

[0004] The uncontrolled reentry phase exhibits poor attitude stability and a large landing point dispersion radius (>5 km).

[0005] The main load-bearing structure is prone to plastic deformation (>2%) after reentry. The heat protection layer is mostly a one-time ablation design, which is difficult to reuse and has high mission cost.

[0006] Currently, while the crew module of Blue Origin's New Shepard spacecraft has been successfully recovered, the independent layout of the parachute compartments results in reduced effective volume, low space utilization, and significant structural redundancy, requiring a 10%-15% increase in weight for structural reinforcement. Early sounding rocket return capsules, with their spin-stabilizing mechanisms, experienced attitude divergence due to aerodynamic disturbances during reentry. my country's Shijian-10 return capsule, using a magnesium alloy main frame, suffered severe structural deformation after reentry, rendering it unusable. The main load-bearing frame was also non-reusable, and the thermal protection layer suffered single-ablation, necessitating complete replacement for reuse. China currently lacks a suborbital payload module.

[0007] Therefore, there is an urgent need to develop a load cell structure device with a reasonable structural layout, high structural efficiency, good aerodynamic stability, and partial reusability. Summary of the Invention

[0008] The purpose of this application is to provide a suborbital returnable payload capsule structure device with a reasonable structural layout, high structural efficiency, good aerodynamic stability, and partial reusability.

[0009] To achieve the above objectives, this application provides a suborbital return payload compartment structure, which adopts a blunt-tipped conical integral configuration. The device includes a nose cap, a main structural conical section, an aerodynamic heat-resistant arc bottom, a parachute compartment structure, a payload mounting disk, and a heat protection system. The nose cap is connected to the top of the main structural conical section, and the aerodynamic heat-resistant arc bottom is connected to the bottom of the main structural conical section. The nose cap is used to adjust the axial center of gravity of the entire compartment and bears the main impact load during landing. The parachute compartment structure is located inside the main structural conical section and is integrally formed with it. The payload mounting disk is connected to the main structural conical section. The heat protection system is disposed on the nose cap, the main structural conical section, the aerodynamic heat-resistant arc bottom, and / or the parachute compartment cover of the parachute compartment structure, and is used to reduce the internal temperature of the compartment.

[0010] As described above, in the suborbital return payload capsule structure device, the bottom of the parachute structure is located at the center of the aerodynamic heat-resistant arc bottom; the parachute structure is cylindrical and coaxially arranged with the conical section of the main structure; the parachute structure automatically opens during the device's reentry process.

[0011] The suborbital returnable payload capsule structure device described above includes a payload mounting disk comprising a first payload mounting disk and a second payload mounting disk; the first payload mounting disk and the second payload mounting disk are arranged in parallel within the main structural conical section; one of the payload mounting disks is connected to a crossbeam on the inner wall of the main structural conical section; the other payload mounting disk is connected to the lower end frame of the main structural conical section using corner joints; the first payload mounting disk and the second payload mounting disk are constructed with an aluminum alloy skeleton and aluminum honeycomb carbon fiber panels.

[0012] As described above, in the suborbital return payload capsule structure, the heat protection system includes a multi-layer heat insulation component, an alumina transparent ceramic window, a heat shield, and / or a thermal control coating; the multi-layer heat insulation component is disposed within the end cap; the alumina transparent ceramic window and the heat shield are disposed on the main structural cone section; the thermal control coating is applied to the outer surface of the end cap, the outer surface of the main structural cone section, the outer surface of the aerodynamic heat-resistant arc bottom, and / or the outer surface of the parachute canopy.

[0013] In the suborbital returnable payload cabin structure device described above, the aerodynamic heat-resistant arc bottom is arc-shaped and made of polyimide-based glass fiber composite material. The aerodynamic heat-resistant arc bottom is used to protect the equipment inside the cabin and reduce aerodynamic drag.

[0014] As described above, in the suborbital return payload capsule structure, the first payload mounting disk is equipped with a parachute controller mounting plate, a wire clamp, a test interface support, and / or a pressure sensor support; a separation / de-connection support is installed on the lower surface of the first payload mounting disk; and a radio frequency front-end bracket is installed on the second payload mounting disk.

[0015] The suborbital return payload compartment structure as described above further includes a separation spring top cover, which is mounted on the lower end frame of the main structural cone section and the payload mounting disk.

[0016] The suborbital return payload compartment structure device described above further includes an impact damping device, which is composed of aluminum alloy honeycomb, polytetrafluoroethylene and stainless steel, and is used to attenuate the impact of rocket compartment separation.

[0017] In the suborbital return payload capsule structure device described above, the main structural cone segment is an integrally formed structure of carbon fiber composite material or aluminum alloy thin-walled mesh reinforcement.

[0018] In the suborbital return payload capsule structure described above, the heat shield is made of polyimide-based glass fiber composite material.

[0019] The beneficial effects achieved by this application are as follows:

[0020] (1) The main structure of the load compartment (main structure cone section) and the umbrella compartment structure of this application adopt an integrated design to increase the load volume; the structural weight ratio is reduced and the load-bearing efficiency is significantly improved.

[0021] (2) Based on the aerodynamic spin-stabilized layout of MBSE, this application achieves uncontrolled spin-stabilized reentry through the coordinated design of aerodynamic shape and structure, realizing uncontrolled precise reentry with a landing point accuracy of ≤1000 m, thus reducing search and rescue costs.

[0022] (3) The main structural cone section of this application can be reused, the heat protection system has low maintenance cost, and the cost of a single task is reduced.

[0023] (4) This application sets three sets of reinforcing tie rods to achieve a stable and reliable connection between the first load mounting disk and the second load mounting disk and the main structural cone segment. The three sets of reinforcing tie rods enhance the strength and stiffness of the entire structure.

[0024] (5) This application provides a low-cost, highly reliable, and reusable return structure for suborbital science experiments. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of this application 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 this application. For those skilled in the art, other drawings can be obtained based on these drawings.

[0026] Figure 1 This is a schematic diagram of a suborbital return payload cabin structure according to an embodiment of this application.

[0027] Figure 2 This is a schematic diagram of the internal structure of a suborbital return payload cabin structure according to an embodiment of this application.

[0028] Figure 3 for Figure 1 Sectional view at point AA.

[0029] Figure 4 for Figure 1 Sectional view at point BB.

[0030] Figure 5 This is a schematic diagram of the pneumatic heat-resistant arc bottom of an embodiment of this application.

[0031] Reference numerals: 1-End cap; 2-Main structure conical section; 3-Pneumatic heat-resistant arc bottom; 4-Canopy structure; 5-Reinforcing tie rod; 11-Impact damping sandwich structure; 12-Heat insulation pad; 21-Canopy door; 22-Heat shield; 23-Impact damping device; 24-First load mounting disc; 25-Second load mounting disc; 26-Camera heat shield; 31-Separation and disconnection support; 32-Separation spring top cover; 41-Canopy cover; 241-Canopy controller mounting plate; 242-Wire clip; 243-Test interface support; 244-Pressure sensor support; 251-RF front-end bracket. Detailed Implementation

[0032] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0033] like Figure 1 As shown, this application provides a suborbital return payload capsule structure device, which includes a nose cap 1, a main structural cone section 2, an aerodynamic heat-resistant arc bottom 3, a parachute structure 4, a payload mounting disk, and a heat protection system. The device uses a nose cap 1 for landing and a parachute opening at the bottom. The nose cap 1 is connected to the top of the main structural cone section 2, and the aerodynamic heat-resistant arc bottom 3 is connected to the bottom of the main structural cone section 2. The nose cap 1 is used to adjust the axial center of gravity of the entire capsule and bears the main impact load during landing. The parachute structure 4 is located inside the main structural cone section 2 and is integrated with it. The payload mounting disk is connected to the main structural cone section 2. The heat protection system is installed on the parachute cover 41 of the nose cap 1, the main structural cone section 2, the aerodynamic heat-resistant arc bottom 3, and / or the parachute structure 4, and is used to reduce the internal temperature of the capsule.

[0034] Preferably, the suborbital reentry payload bay structure of this application adopts a blunt-nosed conical integral configuration. The advantages of the blunt-nosed conical integral configuration include: enhanced dynamic stability, which can effectively suppress pitch oscillations and maintain flight stability; larger internal volume, which provides more internal space for installing various payload equipment, such as sensors, controllers, and testing instruments, and facilitates integrated payload design and improves space utilization; and good thermal protection performance, which, due to its blunt nose, can generate a strong detachment shock wave at the front end during reentry, helping to remove most of the heat and reduce the heat entering the spacecraft, thereby reducing the burden on the thermal protection system and improving the safety of the spacecraft.

[0035] like Figure 2 As shown, the bottom of the parachute compartment structure 4 is located in the center of the aerodynamic heat shield arc base 3. The parachute compartment structure 4 is cylindrical, with a simple and symmetrical structure, which facilitates processing and sealing. The parachute compartment structure 4 is coaxially arranged with the main structure cone section 2, that is, the cylindrical axis coincides with the payload compartment axis. The parachute compartment is centered, and no eccentric moment is generated when the parachute is deployed, avoiding the aircraft from rolling or becoming unstable, and ensuring aerodynamic symmetry and deployment stability. During the reentry of the suborbital return payload compartment structure device, the parachute compartment structure 4 automatically opens, releasing the recovery parachute system to achieve deceleration and landing recovery of the payload compartment. Integrating the parachute compartment structure 4 into the center of the aerodynamic heat shield arc base 3, it shares force with the payload mounting disk and the main structure cone section 2, eliminating the independent parachute compartment structure 4, improving space utilization and overall rigidity.

[0036] As a specific embodiment of the present invention, the parachute compartment structure 4 requires a heat-protected unlocking mechanism (such as shape memory alloy, hot melt bolt, pyrotechnics + heat insulation cover, etc.) when the parachute is opened to ensure reliable operation at high temperatures.

[0037] In a preferred embodiment of the present invention, the parachute structure 4 is integrated with the payload compartment and its payload mounting disk, increasing overall rigidity and strength while saving more space for the payload. This achieves the shortest force transmission path, maximizes space utilization, and maximizes global structural rigidity, resulting in a highly integrated, lightweight, and highly reliable recovery suborbital return payload compartment structure.

[0038] like Figure 1 As shown, a hatch 21 is provided on the main structural cone section 2. Preferably, there are two hatches 21, but the number of hatches 21 is not limited here and can be other numbers. The hatches 21 provide a critical passage for equipment maintenance, payload loading, and ground testing of the suborbital payload module.

[0039] As a specific embodiment of the present invention, the main structural cone section 2 is also provided with an operating cover. In addition to the hatch 21 (large size, low frequency opening), an operating cover is added to the main structural cone section 2 for high frequency, small diameter ground operations. The operating cover is, for example, a cable cover, a pneumatic cover, a pyrotechnics cover, etc. There are 6 operating covers, but the number of operating covers is not limited here and can be other numbers.

[0040] like Figure 1 and 2 As shown, the end cap 1 is hemispherical; preferably, the end cap 1 is made of stainless steel. An impact-damping sandwich structure 11 is provided at the top of the interior of the end cap 1, which acts as a damping layer during landing. The end cap 1 protects the internal payload by isolating it from aerodynamic heat conduction and thermal radiation. The end cap 1 not only isolates aerodynamic heat conduction and thermal radiation but also continuously transmits axial loads, providing a lightweight and reusable front-end thermal protection barrier for the entire suborbital payload bay.

[0041] like Figure 2 As shown, a heat insulation pad 12 is provided inside the end cap 1, and the heat insulation pad 12 is provided on the surface of the impact damping sandwich structure 11.

[0042] like Figure 2 As shown, the load mounting disk includes a first load mounting disk 24 and a second load mounting disk 25; the first load mounting disk 24 and the second load mounting disk 25 are arranged parallel to each other within the main structural cone section 2; the first load mounting disk 24 and the second load mounting disk 25 are distributed vertically, with one load mounting disk (the upper load mounting disk) connected to the inner wall beam of the main structural cone section 2; the other load mounting disk (the lower load mounting disk) is connected to the lower end frame of the main structural cone section 2 using corner joints; the first load mounting disk 24 and the second load mounting disk 25 are made of aluminum alloy frame, aluminum honeycomb, and carbon fiber panels. The first load mounting disk 24 and the second load mounting disk 25 are the main load-bearing structures for the effective load and measurement system equipment.

[0043] like Figure 2-4As shown, the reinforcing tie rods 5 comprise three sets, spaced apart along the circumference of the main structural cone segment 2. The included angle between adjacent sets of reinforcing tie rods 5 is 120 degrees. The three sets of reinforcing tie rods 5 are positioned on the outer periphery of the umbrella-shaped structure 4, between the first load mounting disc 24 and the second load mounting disc 25. One end of each set of reinforcing tie rods 5 is connected to the inner wall of the main structural cone segment 2, and the other end is connected to both the first load mounting disc 24 and the second load mounting disc 25, forming a high-rigidity load-bearing frame. The three sets of reinforcing tie rods 5 ensure a stable and reliable connection between the first load mounting disc 24 and the second load mounting disc 25 and the main structural cone segment 2. The three sets of reinforcing tie rods 5 are used to strengthen and distribute the load-bearing capacity, enhancing the strength and rigidity of the entire structure.

[0044] As a specific embodiment of the present invention, the heat protection system includes a multi-layer heat insulation component, an alumina transparent ceramic window, a heat shield 22, and / or a thermal control coating; the multi-layer heat insulation component is disposed inside the end cap 1; the alumina transparent ceramic window and the heat shield 22 are disposed on the main structural cone section 2; the thermal control coating is applied to the outer surface of the end cap 1, the outer surface of the main structural cone section 2, the outer surface of the aerodynamic heat-resistant arc bottom 3, and / or the outer surface of the parachute canopy 41. By implementing the heat protection system, the internal temperature during reentry is achieved to be ≤50℃.

[0045] As a specific embodiment of the present invention, this application adopts gradient heat protection (multi-layer heat insulation components from the outside to the inside) and impact-resistant design (setting an impact damping sandwich structure 11). Through the combination of materials and structure, thermal-mechanical-functional integration is achieved, ensuring a structural reuse rate of >80%.

[0046] like Figure 1 and 2 As shown, the pneumatic heat-resistant arc bottom 3 has an arc shape and is made of polyimide-based glass fiber composite material. The pneumatic heat-resistant arc bottom 3 is used to protect the equipment inside the cabin and reduce aerodynamic drag.

[0047] As a specific embodiment of the present invention, the aerodynamic heat-resistant arc base 3 combines aerodynamic shape, thermal protection, and wave transmission functions. The aerodynamic shape refers to the geometry of the aircraft's exterior, which determines the aerodynamic characteristics experienced by the aircraft during atmospheric motion, including lift, drag, stability, and heat flow distribution. The aerodynamic shape optimizes airflow, reduces drag, and improves flight efficiency; it controls the heat flow distribution on the aircraft surface, reducing the burden on the thermal protection system; and it maintains flight stability, especially during high-speed or reentry phases. Wave transmission function refers to the material's excellent permeability to electromagnetic waves (especially radar waves and communication signals), i.e., low dielectric constant and low loss factor, without significant reflection or absorption of electromagnetic waves. Wave transmission function ensures the normal operation of electronic equipment such as radar, communication, and navigation devices; and avoids signal attenuation due to material shielding or interference.

[0048] like Figure 3 and4 As shown, the first load mounting disk 24 is a disk-shaped structural component used to support and fix various load devices. The first load mounting disk 24 is equipped with a parachute controller mounting plate 241, a cable clip 242, a test interface support 243, and / or a pressure sensor support 244. A disconnect / remove support 31 is installed on the lower surface of the first load mounting disk 24. When the load compartment is separated, the disconnect / remove support 31 reliably pulls out the power supply / signal / high-frequency connector in one go with a constant pulling force, ensuring that the electrical connection is broken first, without rebound or damage to the cable, while bearing 100% of the pull-out load itself, without transferring it to the arc-bottom composite material. An RF front-end bracket 251 can also be installed on the first load mounting disk 24. The parachute controller mounting plate 241 is used to install the parachute controller (the control unit of the parachute or recovery system). The cable clip 242 is used to organize and fix the cable bundle. The test interface support 243 is used to install test interfaces (such as electrical test ports, data download ports, etc.). Pressure sensor bracket 244 is used to mount pressure sensors (such as air pressure, hydraulic pressure, or environmental pressure monitoring). RF front-end bracket 251 is used to mount RF front-end modules (such as antennas, amplifiers, filters, etc.).

[0049] like Figure 3 and 4 As shown, an RF front-end bracket 251 is mounted on the second load mounting disk 25. The parachute controller mounting plate 241, line clip 242, test interface support 243 and / or pressure sensor support 244 can also be mounted on the second load mounting disk 25.

[0050] As a specific embodiment of the present invention, this application adopts a modular load-bearing interface: providing a standardized installation interface and spatial layout, supporting a payload weight ratio of up to 50%; (the payload ratio of a normal payload compartment is 20%~30%).

[0051] like Figure 5 As shown, the suborbital returnable payload compartment structure also includes a separation spring top cover 32, which is installed on the lower end frame of the main structural cone section 2 and the payload mounting disk. The separation and disengagement support 31 first disconnects the electrical circuit, and then the separation spring top cover 32 provides an outward thrust, ensuring that the compartment separation follows the principle of "electricity disconnection first, force unloading second, and zero collision at the arc bottom." After multiple cycles, the structure remains intact, ensuring the complete recovery of the aerodynamic heat-resistant arc bottom 3.

[0052] like Figure 1 As shown, the suborbital return payload compartment structure also includes an impact damping device 23, which is composed of aluminum alloy honeycomb, polytetrafluoroethylene and stainless steel, and is used to attenuate the impact of the rocket compartment separation.

[0053] In a specific embodiment of the present invention, the impact damping device 23 is an impact damping storage box, which is installed at the connection between the main structural cone section 2 and the aerodynamic heat-resistant arc bottom 3. The impact damping device 23 adopts a combination of aluminum alloy, aluminum alloy honeycomb core, stainless steel and polytetrafluoroethylene to weaken the impact during the separation of the load chamber.

[0054] As a specific embodiment of the present invention, the main structural cone segment 2 is an integrally formed structure of carbon fiber composite material or aluminum alloy thin-walled mesh reinforcement. The main structural cone segment 2 uses carbon fiber reinforced composite material as the main load-bearing frame to achieve high specific stiffness and reusability.

[0055] In a specific embodiment of the present invention, the heat shield 22 is made of polyimide-based glass fiber composite material. The heat shield 22 serves as a heat shield for an antenna or camera, with the antenna or camera housed inside. Preferably, the heat shield 22 comprises four units. The number of heat shields 22 is not limited herein.

[0056] As a specific embodiment of the present invention, the heat shield 22 provides heat insulation while meeting the transmittance requirements of the GNSS antenna. Furthermore, the bottom of the heat shield 22 is made of alumina transparent heat shield, which meets the requirements of high temperature resistance and heat insulation while also meeting the requirement that the visible light transmittance of the camera device is above 85%.

[0057] like Figure 5 As shown, a camera heat shield 26 is provided at the bottom of the heat shield 22. The camera heat shield 26 provides both thermal protection and serves as an optical window, allowing the camera to still capture clear images on a hot surface of 850 ℃ without compromising the aerodynamic and thermal integrity of the heat shield.

[0058] like Figure 5 As shown, the parachute compartment structure 4 has a parachute compartment cover 41, which is located at the center of the aerodynamic heat shield base 3. After reentry, the parachute compartment cover 41 unlocks, flips outward, and remains open for a certain period of time upon command, allowing the parachute system to be pulled out without obstruction. At the same time, it acts as an aerodynamic spoiler to prevent rebound and block the parachute lines. After the parachute is deployed, it still retains a hinged connection with the compartment, thus not forming space debris and meeting the dual requirements of reusability and debris suppression.

[0059] As a specific embodiment of the present invention, this application adopts a spin-stabilized aerodynamic layout: the center of mass and inertia are balanced based on MBSE (model-based systems engineering), ensuring attitude stability during reentry without the need for active control.

[0060] During the separation process, the impact level inside the chamber is ≤1000g, the impact level in critical equipment areas is ≤300g, and the temperature is ≤50℃, ensuring equipment safety and data integrity. It has good thermal protection and impact isolation performance to ensure the safety of equipment inside the chamber.

[0061] The beneficial effects achieved by this application are as follows:

[0062] (1) The main structure of the load compartment (main structure cone section) and the umbrella compartment structure of this application adopt an integrated design to increase the load volume; the structural weight ratio is reduced and the load-bearing efficiency is significantly improved.

[0063] (2) Based on the aerodynamic spin-stabilized layout of MBSE, this application achieves uncontrolled spin-stabilized reentry through the coordinated design of aerodynamic shape and structure, realizing uncontrolled precise reentry with a landing point accuracy of ≤1000 m, thus reducing search and rescue costs.

[0064] (3) The main structural cone section of this application can be reused, the heat protection system has low maintenance cost, and the cost of a single task is reduced.

[0065] (4) This application sets three sets of reinforcing tie rods to achieve a stable and reliable connection between the first load mounting disk and the second load mounting disk and the main structural cone segment. The three sets of reinforcing tie rods enhance the strength and stiffness of the entire structure.

[0066] (5) This application provides a low-cost, highly reliable, and reusable return structure for suborbital science experiments.

[0067] In the description of this application, 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 indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0068] In the description of this application, the word "for example" is used to mean "used as an example, illustration, or description." Any embodiment described as "for example" in this application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is provided to enable any person skilled in the art to make and use the invention. Details are set forth in the following description for purposes of explanation. It should be understood that those skilled in the art will recognize that the invention can be made without using these specific details. In other instances, well-known structures and processes will not be described in detail to avoid obscuring the description of the invention with unnecessary detail. Therefore, the invention is not intended to be limited to the embodiments shown, but is consistent with the broadest scope of the principles and features disclosed in this application.

[0069] The above description is merely an embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of the present invention should be included within the scope of the claims of the present invention.

Claims

1. A suborbital returnable payload capsule structural device, characterized in that, The device adopts a blunt-tipped conical integral configuration, which includes an end cap, a main structural conical section, a pneumatic heat-resistant arc bottom, a parachute structure, a load mounting disk, and a heat protection system. The end cap is connected to the top of the main structural cone section, and the pneumatic heat-resistant arc bottom is connected to the bottom of the main structural cone section; The end cap is used to adjust the axial center of gravity of the entire cabin and bears the main impact load during landing; the top of the end cap is equipped with an impact damping sandwich structure. The parachute structure is located inside the main structural cone section and is an integral part of the main structural cone section; the parachute structure is integrated into the center of the aerodynamic heat-resistant arc bottom and transmits force together with the load mounting disk and the main structural cone section; The load mounting disk is connected to the main structure cone segment; The heat protection system is installed on the end cap, the main structural cone section, the aerodynamic heat-resistant arc bottom, and the canopy cover of the canopy structure. The heat protection system is used to reduce the temperature inside the canopy. The heat protection system includes a multi-layer heat insulation component, an alumina transparent ceramic window, a heat protection cover, and a thermal control coating. The multi-layer heat insulation assembly is disposed inside the end cap; the multi-layer heat insulation assembly adopts gradient heat protection from the outside to the inside; The alumina transparent ceramic window and the heat shield are disposed on the conical section of the main structure; The thermal control coating is applied to the outer surface of the end cap, the outer surface of the main structure cone section, the outer surface of the aerodynamic heat-resistant arc bottom, and the outer surface of the parachute canopy. The suborbital returnable payload capsule structure adopts a spin-stabilized aerodynamic layout and achieves center of mass and inertia balance based on MBSE; The load mounting disk includes: a first load mounting disk and a second load mounting disk; The first load mounting disk and the second load mounting disk are arranged in parallel within the main structure cone section; One of the load mounting discs is connected to the inner wall beam of the main structural cone section; the other load mounting disc is connected to the lower end frame of the main structural cone section using corner joints. The first load mounting disk and the second load mounting disk are made of aluminum alloy frame, aluminum honeycomb carbon fiber panel; Three sets of reinforcing tie rods are installed between the first load mounting disk and the second load mounting disk. The three sets of reinforcing tie rods are spaced apart along the circumference of the main structural cone section, with an included angle of 120 degrees between adjacent sets of reinforcing tie rods, and the three sets of reinforcing tie rods are located on the outer periphery of the umbrella structure. One end of each of the three sets of reinforcing tie rods is connected to the inner wall of the main structural cone section, and the other end is connected to the first load mounting disk and the second load mounting disk, forming a high-rigidity load-bearing frame. The suborbital returnable payload compartment structure also includes a separation spring top cover, which is installed on the lower end frame of the main structure cone section and the payload mounting disk; the separation and disengagement support first disconnects the electrical circuit, and then the separation spring top cover provides an outward pushing impulse; The suborbital returnable payload cabin structure also includes: an impact damping device, which is an impact damping storage box, located at the connection between the main structure cone section and the aerodynamic heat-resistant arc bottom. The main structural cone segment is an integrally formed structure of carbon fiber composite material or aluminum alloy thin-walled mesh reinforcement.

2. The suborbital returnable payload capsule structure device according to claim 1, characterized in that, The bottom of the parachute structure is located in the center of the aerodynamic heat-resistant arc bottom; The parachute compartment structure is cylindrical and is coaxially arranged with the conical section of the main structure. During reentry, the parachute structure automatically opens.

3. The suborbital returnable payload capsule structure device according to claim 1, characterized in that, The pneumatic heat-resistant arc bottom is arc-shaped and made of polyimide-based glass fiber composite material. The pneumatic heat-resistant arc bottom is used to protect the equipment inside the cabin and reduce aerodynamic drag.

4. The suborbital returnable payload capsule structure device according to claim 1, characterized in that, The first load mounting disk is equipped with a parachute controller mounting plate, a wire clamp, a test interface support, and a pressure sensor support. A separation and insertion support is installed on the lower surface of the first load mounting disk; The second load mounting disk is equipped with an RF front-end bracket.

5. The suborbital returnable payload capsule structure device according to claim 1, characterized in that, Also includes: An impact damping device, which is composed of aluminum alloy honeycomb, polytetrafluoroethylene and stainless steel, is used to attenuate the impact of rocket separation.

6. The suborbital returnable payload capsule structure according to claim 1, characterized in that, The heat shield is made of polyimide-based glass fiber composite material.

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