Reentry vehicle shoulder jet heat protection device and control method thereof

Abstract

The embodiment of the application provides a reentry vehicle shoulder jet heat protection device and a control method thereof. The protection device comprises a load cabin and a protection wing arranged around the outer periphery of the load cabin. The protection wing comprises a plurality of unfolding rods, each of which comprises a rod body and a jet device arranged in the rod body. The front end of the rod body is movably connected to the load cabin. The tail end of the rod body is provided with a jet hole. The side wall of the rod body is provided with an unfolding hole. The jet hole and the unfolding hole are respectively communicated with the jet device. When the jet gas sprayed by the jet device is sprayed from the unfolding hole, the protection wing is switched from the folded state to the unfolded state. When the jet gas sprayed by the jet device is sprayed from the jet hole, the jet gas forms heat protection for the tail end of the unfolding rod. The embodiment of the application utilizes the internal space of the unfolding rod to carry medium jet for unfolding the vehicle and heat protection of the whole vehicle, improves the space utilization, and does not affect the original load carrying of the vehicle.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more specifically, to a shoulder jet thermal protection device and its control method for a reentry vehicle. Background Technology

[0002] With the development of the space industry, space transportation and deep space exploration missions will be the focus of future research. Compared with traditional reentry deceleration methods and inflatable reentry vehicles, mechanically deployable reentry vehicles have received widespread attention both domestically and internationally in recent years due to their advantages such as small envelope constraint, high payload efficiency, and good deceleration effect. During the reentry process, the reentry vehicle successively passes through rarefied flow, transitional flow, and continuous flow regions. A large amount of aerodynamic heat is generated during high-speed flight, causing ablation of the vehicle surface and the overall structure. Therefore, how to effectively and reasonably protect the reentry vehicle from thermal damage is one of the urgent problems to be solved.

[0003] In recent years, many scholars both domestically and internationally have proposed various methods for drag reduction and heat protection, such as: reverse jetting, adding drag-reducing rods, adding pneumatic discs, windward concave cavities, energy deposition, and many combinations thereof. For example, related technologies employ drag-reducing rods combined with pneumatic discs for drag reduction and heat protection.

[0004] Existing methods of thermal protection have many problems. If jet thermal protection is used, the propellant it carries occupies a large space inside the spacecraft. If additional devices are installed, the exposed parts of the spacecraft suffer severe ablation and will affect the shape and center of gravity of the reentry vehicle. At the same time, existing thermal protection methods are all aerodynamic thermal protection for the nose of the reentry vehicle, and their overall protection effect on the spacecraft is not good. Summary of the Invention

[0005] The purpose of this application is to provide a shoulder jet thermal protection device and its control method for reentry vehicles, so as to solve the problem of poor protection effect for reentry flights in the prior art.

[0006] This application provides a shoulder jet thermal protection device for a reentry vehicle, comprising: a payload bay; and a protective wing surrounding the outer periphery of the payload bay. The protective wing has a retracted state (folded to the outer periphery of the payload bay) and an extended state (extended outward relative to the outer periphery of the payload bay). The protective wing includes multiple deployable rods, each deployable rod including a rod body and a jet device disposed within the rod body. The front end of the rod body is movably connected to the payload bay, and the rear end of the rod body is provided with a jet hole. The side wall of the rod body is provided with an deployment hole. The jet hole and the deployment hole are respectively connected to the jet device. When the jet gas ejected by the jet device is ejected from the deployment hole, the deployable rod, under the reaction force of the jet gas, causes the protective wing to switch from the retracted state to the extended state. When the jet gas ejected by the jet device is ejected from the jet hole, the jet gas provides thermal protection to the rear end of the deployable rod.

[0007] This embodiment utilizes a jet of medium carried within the deployment rod to deploy the aircraft and provides overall shoulder-mounted jet thermal protection, improving space utilization without affecting the original payload capacity. Furthermore, deployment via jet reduces the need for some motor mechanisms. Compared to traditional drag reduction methods such as drag-reducing rods and pneumatic discs, this thermal protection method is more stable and controllable, eliminating concerns about ablation and alterations to the aircraft's shape and center of gravity. It also provides better thermal protection for the aircraft's shoulder, resulting in more stable reentry.

[0008] In some embodiments, the jet device includes: a gas storage cylinder, a solenoid valve, and a gas collection chamber arranged sequentially from the front end to the rear end of the rod, wherein the solenoid valve is connected between the gas storage cylinder and the gas collection chamber, and the gas collection chamber is connected to the jet hole and the expansion hole.

[0009] In this embodiment, a solenoid valve connects the gas storage cylinder and the gas collection chamber. The opening and closing of the solenoid valve starts and stops the jet, which facilitates reasonable and precise control according to the environment in which the aircraft is located.

[0010] In some embodiments, the gas collection chamber includes a connected cavity, a plurality of axial jet channels and a lateral jet channel, and a plurality of jet holes are provided, each of the plurality of jet holes being connected to a plurality of axial jet channels in a one-to-one correspondence, and the expansion hole being connected to the lateral jet channel.

[0011] In this embodiment, the axial jet channel is multi-channel and the lateral jet channel is single-channel, so that the jet medium in the gas storage cylinder is reasonably distributed, allowing more jets to be ejected through the jet holes, thereby providing better jet thermal protection for the shoulder of the aircraft.

[0012] In some embodiments, the system further includes: a deployment mechanism, the deployment mechanism including a connecting rod and a slider; the front end of the connecting rod is hinged to the load chamber, a slide rail is provided on the connecting rod, one end of the connecting rod is hinged to the load chamber, the other end is connected to the slider, and the slider is slidably connected to the slide rail.

[0013] In this embodiment, when the unfolding rod is subjected to the reaction force of the gas injected from the unfolding hole, the unfolding operation of each unfolding rod is realized through the cooperation of the connecting rod, the slider and the slide rail, and the unfolding process is more stable.

[0014] In some embodiments, the load chamber is provided with a first lifting lug and a second lifting lug arranged at intervals along the axial direction of the load chamber, the front end of the rod is hinged to the load chamber through the first lifting lug, and the connecting rod is hinged to the load chamber through the second lifting lug.

[0015] In this embodiment, the first lifting lug and the second lifting lug are hinged to the unfolding rod and the connecting rod, respectively, so as to avoid interference with the load chamber during the unfolding process of each unfolding rod and facilitate installation.

[0016] In some embodiments, the protective wing further includes a skin attached to each of the deployment rods, the skin covering the head of the payload compartment in an umbrella shape, wherein the skin retracts and expands with the protective wing. The skin includes a heat-resistant surface attached to the front end of each deployment rod and an aerodynamic deceleration surface attached to the front end of each deployment rod and connected to the heat-resistant surface.

[0017] In this embodiment, the umbrella-shaped skin has heat-insulating and aerodynamic deceleration surfaces, which provide heat insulation and protection for the entire aircraft.

[0018] In some embodiments, the deploying rod is a hollow rod, and the deploying hole is disposed on the side wall of the deploying rod near the load chamber.

[0019] In this embodiment, the hollow rod facilitates the internal storage of medium gas while reducing the overall weight. The deployment hole is located on the side wall of the deployment rod near the load chamber so that the reaction force of the gas ejected from the deployment hole acts on the deployment rod to the maximum extent, which facilitates the deployment of each deployment rod.

[0020] This application also provides a control method for a reentry vehicle shoulder jet thermal protection device, applied to the thermal protection device described in any of the above embodiments. The method includes: in response to a reentry and return mission command, controlling the solenoid valve to open, causing the jet gas ejected by the jet device to be ejected from the deployment hole, thereby switching the protective wing from a retracted state to a deployed state; in response to a protective wing deployment completion command, controlling the solenoid valve to close; determining the vehicle position during reentry and return, and when the vehicle is in a first position, controlling the solenoid valve to open again, causing the jet gas ejected by the jet device to be ejected from the jet hole, forming thermal protection for the tail end of the deployment rod; determining the vehicle position and / or the pressure difference between the inside and outside of the jet device during reentry and return, and when the vehicle is in a second position and / or the pressure difference between the inside and outside of the jet device is balanced, controlling the solenoid valve to close.

[0021] In this embodiment, the start and stop of the jet are controlled by switching on and off a solenoid valve, which facilitates reasonable and precise control based on the environment in which the aircraft is located. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments of this application will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 A schematic diagram of the deployed state of a shoulder jet thermal protection device for a reentry vehicle provided in this application embodiment;

[0024] Figure 2 A schematic diagram of the retracted state of a shoulder jet thermal protection device for a reentry vehicle provided in this application embodiment;

[0025] Figure 3 A schematic diagram of the protective wing structure of a shoulder jet thermal protection device for a reentry vehicle provided in this application embodiment;

[0026] Figure 4 Another perspective schematic diagram of a shoulder jet thermal protection device for a reentry vehicle provided in this application embodiment;

[0027] Figure 5 A schematic diagram of the deployed state of the deployment rod of a shoulder jet thermal protection device for a reentry vehicle provided in this application embodiment;

[0028] Figure 6A schematic diagram of the deployed and retracted state of a shoulder jet thermal protection device for a reentry vehicle provided in this application embodiment;

[0029] Figure 7 A schematic diagram of the internal structure of the deployable rod of a shoulder jet thermal protection device for a reentry vehicle provided in this application embodiment;

[0030] Figure 8 A flowchart illustrating a jet thermal protection method for a shoulder jet thermal protection device of a reentry vehicle, provided in this application embodiment;

[0031] Figure 9 A flowchart of a jet thermal protection method for a reentry vehicle shoulder jet thermal protection device, provided as another embodiment of this application;

[0032] Icons: 10-Payment compartment; 20-Protective wing; 21-Deployment rod; 22-Gas cylinder; 23-Solenoid valve; 24-Gas collection chamber; 201-Front end; 202-Tail end (shoulder); 203-Jet hole; 204-Deployment hole; 25-Skin; 251-Heat shield; 252-Aerodynamic deceleration surface. Detailed Implementation

[0033] The technical solutions in the embodiments of this application will now be described with reference to the accompanying drawings.

[0034] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, in the description of this application, terms such as "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0035] Please refer to Figure 1 , Figure 2 and Figure 7 , Figure 1 A schematic diagram of the deployed state of a shoulder jet thermal protection device for a reentry vehicle provided in this application embodiment; Figure 2 A schematic diagram of the retracted state of a shoulder jet thermal protection device for a reentry vehicle provided in this application embodiment; Figure 7 This is a schematic diagram of the internal structure of the deployment rod of a shoulder jet thermal protection device for a reentry vehicle, provided as an embodiment of this application.

[0036] This application provides a shoulder jet thermal protection device for a reentry vehicle, including a payload bay 10 and a protective wing 20.

[0037] The payload compartment 10 provides space for the deployment and retraction of the protective wing 20 and for the payload. The payload compartment 10 may be cylindrical.

[0038] Protective wings 20 are disposed around the outer periphery of the load compartment 10, and the protective wings 20 have a retracted state that is folded into the outer periphery of the load compartment 10. Figure 2 (as shown) and the deployed state with the outer peripheral wall of the relative load compartment 10 extended outwards (as shown) Figure 1 (As shown). The protective wing 20 can be retracted or deployed. During the launch and on-orbit operation of the spacecraft, the protective wing 20 is in the retracted state, and during the reentry process, the protective wing 20 is in the deployed state. In the retracted state, the protective wing 20 and the payload compartment 10 are roughly cylindrical in shape. In the deployed state, the protective wing 20 and the payload compartment 10 are separated and roughly umbrella-shaped.

[0039] Next, refer to Figure 3 , Figure 4 , Figure 5 and Figure 6 , Figure 3 A schematic diagram of the protective wing structure of a shoulder jet thermal protection device for a reentry vehicle provided in this application embodiment; Figure 4 This is a schematic diagram from another perspective of a reentry vehicle shoulder jet thermal protection device provided in an embodiment of this application. Figure 5 A schematic diagram of the deployed state of the deployment rod of a shoulder jet thermal protection device for a reentry vehicle provided in this application embodiment; Figure 6 This is a schematic diagram showing the retracted state of the deployment lever of a shoulder jet thermal protection device for a reentry vehicle, provided as an embodiment of this application. For ease of explanation, [the diagram is omitted here]. Figure 5 and Figure 6 The protective wing in the middle only retains one deployment rod.

[0040] The protective wing 20 includes multiple deployable rods 21, each deployable rod 21 including a rod body and a jetting device disposed within the rod body, the front end 201 of the rod body (see...) Figure 5 The rod is movably connected to the load chamber 10, and the tail end 202 (see...) Figure 5 The rod is provided with a jet hole 203 and an expansion hole 204 on its side wall (see...). Figure 7 The jet orifice 203 and the deployment orifice 204 are respectively connected to the jet device inside the rod body. Understandably, multiple deployment rods 21 can be evenly arranged around the outer periphery of the payload compartment 10. The structure of each deployment rod 21 can be the same, and the front end is movably connected to the outer peripheral wall of the payload compartment 10, while the rear end 202 is a free end. The rear end 202 of the multiple deployment rods 21 forms the shoulder of the aircraft. The inventors have found that for the aircraft, under certain flight conditions, due to the generation of shock waves and flow separation in the shoulder of the aircraft, the most severe thermal environment of the entire aircraft comes from the shoulder of the aircraft.

[0041] When the jet gas ejected from the jet device exits through the deployment hole 204, the protective wings 20 of each deployment rod 21 switch from a retracted state to an deployed state under the reaction force of the jet gas. When the jet gas ejected from the jet device exits through the jet hole 203, the jet gas provides thermal protection to the tail end 202 of the deployment rod 21. Optionally, the deployment rod 21 can be a hollow rod, with the deployment hole 204 located on the side wall of the deployment rod 21 near the load chamber 10. The hollow rod facilitates internal storage of the gas medium while reducing the overall weight. The deployment hole 204 is located on the side wall of the deployment rod 21 near the load chamber 10 to maximize the reaction force of the gas ejected from the deployment hole 204 on the deployment rod 21, facilitating the deployment of each deployment rod 21.

[0042] The reentry vehicle shoulder jet thermal protection device of this application embodiment sprays jet gas through the jet device inside the deployment rod 21 during the reentry process. A portion of the jet gas is ejected from the deployment hole 204 on the side of the deployment rod 21. Each deployment rod 21 is subjected to the reaction force of the jet gas, causing the protective wing 20 to switch from a retracted state to a deployed state. The protective wing 20 is deployed to form an umbrella shape, and the umbrella-shaped surface forms a heat-insulating surface 251 and an aerodynamic deceleration surface 252, which provides thermal insulation protection for the entire vehicle. At the same time, another portion of the jet gas is ejected from the jet hole 203 at the tail end 202 of the deployment rod 21. The jet pushes the shock wave of the vehicle shoulder away from the object surface, reduces the load on the shoulder surface, reduces the shoulder surface temperature, and forms effective thermal protection for the vehicle shoulder (tail end of the deployment rod 21). This reentry vehicle thermal protection device utilizes the internal space of the deployment rod 21 to carry a jet of medium for the deployment of the vehicle and overall thermal protection. This improves space utilization, does not affect the original payload capacity of the vehicle, and the jet-assisted deployment reduces the need for some motor mechanisms. Compared to traditional drag reduction methods such as drag-reducing rods and pneumatic discs, this thermal protection method is more stable and controllable, eliminates the need to consider ablation or changes to the vehicle's shape and center of gravity, is reusable, offers high safety, and provides better thermal protection.

[0043] In some embodiments, refer to Figure 7 Each of the aforementioned deploying rods 21 contains a jetting device comprising: a gas storage cylinder 22, a solenoid valve 23, and a gas collecting chamber 24 arranged sequentially from the front end 201 to the rear end 202 of the rod. The solenoid valve 23 is connected between the gas storage cylinder 22 and the gas collecting chamber 24, and the gas collecting chamber 24 is connected to the jetting hole 203 and the deploying hole 204.

[0044] For example, the gas cylinder 22 can be a cylindrical cylinder that carries a jet of gas with a certain pressure. The gas medium can be nitrogen, oxygen, carbon dioxide, etc. The cylinder pressure and gas storage capacity can be designed and calculated based on flight conditions.

[0045] Solenoid valve 23 can be a DN4 straight-through solenoid valve, which is threadedly connected to gas cylinder 22. The main function of the solenoid valve is to control the circuit to disconnect. It can be a small solenoid valve with wireless or wired control. The solenoid valve is normally closed and opens when it receives a signal.

[0046] The gas collection chamber 24 may include a connected cavity, multiple axial jet channels, and lateral jet channels. Multiple jet holes 203 are provided, each corresponding to one of the multiple axial jet channels. The deployment hole 204 is connected to the lateral jet channels. As an example, the gas collection chamber 24 is threadedly connected to the solenoid valve 23. The gas collection chamber may consist of a small circular cavity and jet channels. The jet channels are divided into axial and lateral groups. The lateral jet channels are single channels, primarily for facilitating the deployment of the reentry vehicle. The axial jet channels are a combination of multiple channels, providing thermal protection for the vehicle through the jet holes. By using multiple axial jet channels and single lateral jet channels, the jet medium within the gas storage cylinder 22 is rationally distributed, allowing more jet to be ejected through the jet holes 203, thus providing better thermal protection for the vehicle.

[0047] Reference Figure 9 As shown, in actual application scenarios, the working process of the aircraft shoulder jet heat protection device is as follows: First, before flight, the built-in gas cylinder 22 is filled with a certain pressure gas. According to the flight conditions, the pressure inside the gas cylinder is ensured to be greater than the external flight pressure. The solenoid valve 23 is in the closed state, and the initial overall aircraft is in the retracted state.

[0048] Next, when the reentry vehicle performs its reentry and return mission at 100km, it needs to switch states from the retracted state to the deployed state to increase the aerodynamic deceleration area. At this time, the solenoid valve 23 is opened, and the high-pressure gas in the gas storage tank 22 is ejected from the jet hole 203 through the gas collection chamber 24. At the same time, the high-pressure gas in the gas collection chamber 24 is ejected from the deployment hole 204 through the lateral jet channel. In the relatively thin atmospheric environment at 100km, the deployment rods 21 slowly unfold due to the reaction force brought by the airflow. After reaching the maximum angle, they are locked by the locking mechanism (not shown in the figure). At this time, the solenoid valve 23 is closed, the jetting ends, and the deployment process is completed.

[0049] Next, the aircraft re-enters while maintaining its deployed state. Ballistic calculations show that the maximum heat flux density on the surface of the aircraft during the return process generally occurs at some point between 40-60 km. Therefore, when the flight condition is at 60 km, the solenoid valve 23 is opened again, and the gas jet in the gas cylinder 22 is ejected through the axial and lateral jet channels to provide thermal protection for the shoulder and the entire aircraft. The main principle is to push the shock wave away from the surface of the object through the jet, thereby reducing the surface load of the aircraft. The cooling medium can reduce the surface temperature on the object through heat transfer.

[0050] Afterwards, when the flight altitude is below 40km or the internal cooling gas pressure is balanced with the external pressure, the solenoid valve 23 is closed, and the jet stops.

[0051] In some embodiments, see Figure 5 and Figure 6 The reentry vehicle shoulder jet thermal protection device also includes: a deployment mechanism, which includes a connecting rod 30 and a slider (not shown in the figure); the front end 201 of the rod is hinged to the payload compartment 10, and a slide rail (not shown in the figure) is provided on the rod; one end of the connecting rod 30 (lower end in the figure) is hinged to the payload compartment 10, and the other end (upper end in the figure) is connected to the slider, and the slider is slidably connected to the slide rail.

[0052] When the unfolding rod 21 is subjected to the reaction force of the gas ejected from the unfolding hole 204, the unfolding operation of each unfolding rod 21 is realized through the cooperation of the connecting rod 30, the slider and the slide rail, and the unfolding process is more stable.

[0053] Optionally, the load chamber 10 is provided with a first lifting lug 11 and a second lifting lug 12 arranged at intervals along the axial direction of the load chamber 10. The front end 201 of the rod is hinged to the load chamber 10 through the first lifting lug 11, and the connecting rod 30 is hinged to the load chamber 10 through the second lifting lug 12. The first lifting lug 11 and the second lifting lug 12 are respectively hinged to the unfolding rod 21 and the connecting rod, so as to avoid interference with the load chamber 10 during the unfolding process of each unfolding rod 21 and facilitate installation.

[0054] In some embodiments, refer to Figure 3 and Figure 4 The protective wing 20 also includes a skin 25 connected to each deployment rod 21. The skin is positioned in an umbrella shape at the head of the payload bay 10, and it retracts and deploys with the protective wing. The skin includes a cone-shaped heat-resistant surface 251 connected to the front end of each deployment rod 21 and an aerodynamic deceleration surface 252 connected to the front and rear ends of each deployment rod 21 and connected to the heat-resistant surface 251. The heat-resistant surface 251 and the aerodynamic deceleration surface 252 provide heat insulation protection for the entire aircraft.

[0055] This application also provides a control method for a shoulder jet thermal protection device for a reentry vehicle, referring to... Figure 8 and Figure 9 The control method is applied to the thermal protection device as described in any of the above embodiments, and the method includes steps S11, S12, S13 and S14.

[0056] In step S11, in response to the aircraft executing the reentry and return mission command, the solenoid valve is opened to allow the jet gas ejected by the jet device to be ejected from the deployment port, so that the protective wing switches from the retracted state to the deployed state.

[0057] In step S12, in response to the command indicating that the protective wing deployment is complete, the solenoid valve is controlled to close.

[0058] As described above, firstly, before flight, the built-in gas cylinder 22 is filled with pressurized gas to ensure that the pressure inside the cylinder is greater than the external flight pressure, and the solenoid valve 23 is closed, initially placing the entire aircraft in a retracted state. Next, when the reentry vehicle performs its reentry and return mission at 100km, a state switch is required, changing from the retracted state to the deployed state to increase the aerodynamic deceleration area. At this time, the solenoid valve 23 is opened, and the high-pressure gas in the gas cylinder 22 is ejected from the jet hole 203 through the gas collection chamber 24. Simultaneously, the high-pressure gas in the gas collection chamber 24 is ejected from the deployment hole 204 through the lateral jet channel. In the relatively thin atmospheric environment at 100km, the deployment rods 21 slowly deploy due to the reaction force from the airflow, reaching their maximum angle and then being locked by a locking mechanism (not shown in the figure). At this point, the solenoid valve 23 is closed, the jetting ends, the deployment process is complete, and the solenoid valve is closed.

[0059] In step S13, the position of the aircraft during the reentry and return process is determined. When the aircraft is in the first position, the solenoid valve is controlled to open again, so that the jet gas ejected by the jet device is ejected from the jet hole to form thermal protection for the tail end of the deployment rod.

[0060] Next, the aircraft re-enters while maintaining its deployed state. Ballistic calculations show that the maximum heat flux density on the surface of the aircraft during the return process generally occurs at some point between 40-60 km. Therefore, when the flight condition is at 60 km, the solenoid valve 23 is opened again, and the gas jet in the gas cylinder 22 is ejected through the axial and lateral jet channels to provide thermal protection for the shoulder of the aircraft (which is also the tail end of each deployment rod) and the entire aircraft. The main principle is to push the shock wave away from the surface of the object through the jet, thereby reducing the surface load of the aircraft. The cooling medium can reduce the surface temperature on the object through heat transfer.

[0061] In step S14, the position of the aircraft and / or the pressure difference between the inside and outside of the jet device are determined during the reentry and return process. When the aircraft is in the second position and / or the pressure difference between the inside and outside of the jet device is balanced, the solenoid valve is controlled to close.

[0062] Afterwards, when the flight altitude is below 40km or the internal cooling gas pressure is balanced with the external pressure, the solenoid valve 23 is closed, and the jet stops.

[0063] In the several embodiments provided in this application, it should be understood that the disclosed apparatus and methods,

[0064] It can also be achieved in other ways. The device embodiments described above are merely illustrative; for example, the flowcharts and block diagrams in the accompanying drawings illustrate devices and methods according to various embodiments of this application.

[0065] The possible architecture, functionality, and operation of legal and computer program products. In this regard, each block in a flowchart or block diagram can represent a module, segment, or portion of code, which contains one or more components for implementing the specified logical functions.

[0066] The executable instructions. It should also be noted that in some alternative implementations, the functions marked 0 in the boxes may occur in a different order than those shown in the figures. For example, two consecutive boxes may actually be executed substantially in parallel, or sometimes in reverse order, depending on the functions involved. It should also be noted that each box in the block diagram and / or flowchart, and combinations of boxes in the block diagram and / or flowchart, can be executed using dedicated instructions to perform the specified functions or actions.

[0067] It can be implemented using a hardware-based system, or it can be implemented using a combination of dedicated hardware and computer instructions. Furthermore, the functional modules in the various embodiments of this application can be integrated together to form an independent part, or each module can exist independently, or two or more modules can be integrated to form an independent part.

[0068] If the aforementioned function is implemented as a software functional module and sold as an independent product, or if...

[0069] When in use, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application.

[0070] The aforementioned storage media include: USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.

[0071] The above description is merely an embodiment of this application and is not intended to limit the scope of protection of this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of protection of this application. It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0072] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

[0073] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

Claims

1. A shoulder jet thermal protection device for a reentry vehicle, characterized in that, include: Payload compartment; as well as Protective wings are arranged around the outer periphery of the load compartment. The protective wings have a retracted state that is folded up against the outer periphery of the load compartment and an extended state that is extended outward relative to the outer periphery of the load compartment. The protective wing includes multiple deployable rods, each rod comprising a rod body and a jetting device disposed within the rod body. The front end of the rod body is movably connected to the load chamber, the rear end of the rod body is provided with a jetting hole, and the side wall of the rod body is provided with a deployable hole. The jetting hole and the deployable hole are respectively connected to the jetting device. When the jet gas ejected by the jet device is ejected from the deployment hole, the deployment rod, under the reaction force of the jet gas, causes the protective wing to switch from the retracted state to the deployed state; when the jet gas ejected by the jet device is ejected from the jet hole, the jet gas forms thermal protection for the tail end of the deployment rod. After the unfolding rod is unfolded to its maximum angle, it is locked by a locking mechanism; The unfolding mechanism includes a connecting rod and a slider; The front end of the rod is hinged to the load chamber, and a slide rail is provided on the rod. One end of the connecting rod is hinged to the load chamber, and the other end is connected to the slider. The slider is slidably connected to the slide rail.

2. The reentry vehicle shoulder jet thermal protection device according to claim 1, characterized in that, The jet device includes: a gas storage cylinder, a solenoid valve, and a gas collection chamber arranged sequentially from the front end to the rear end of the rod. The solenoid valve is connected between the gas storage cylinder and the gas collection chamber, and the gas collection chamber is connected to the jet hole and the expansion hole.

3. The reentry vehicle shoulder jet thermal protection device according to claim 2, characterized in that, The gas collection chamber includes interconnected cavities, multiple axial jet channels, and lateral jet channels. The jet holes are provided in multiple ways, and each jet hole is connected to a corresponding axial jet channel. The expansion hole is connected to the lateral jet channel.

4. The reentry vehicle shoulder jet thermal protection device according to claim 1, characterized in that, The load chamber is provided with a first lifting lug and a second lifting lug arranged at intervals along the axial direction of the load chamber. The front end of the rod is hinged to the load chamber through the first lifting lug, and the connecting rod is hinged to the load chamber through the second lifting lug.

5. The reentry vehicle shoulder jet thermal protection device according to claim 1, characterized in that, The protective wing also includes a skin attached to each of the deployment rods, the skin covering the head of the payload compartment in an umbrella shape, wherein the skin retracts and expands with the protective wing.

6. The reentry vehicle shoulder jet thermal protection device according to claim 5, characterized in that, The skin includes a heat-resistant surface connecting the front end of each of the deploying rods and a pneumatic deceleration surface connecting the front end to the rear end of each of the deploying rods and connected to the heat-resistant surface.

7. The reentry vehicle shoulder jet thermal protection device according to claim 1, characterized in that, The deployable rod is a hollow rod, and the deployable hole is located on the side wall of the deployable rod near the load chamber.

8. The reentry vehicle shoulder jet thermal protection device according to claim 2, characterized in that, The solenoid valve is a straight-through solenoid valve.

9. A control method for a shoulder jet thermal protection device on a reentry vehicle, characterized in that, The method, applied to the thermal protection device as described in any one of claims 1-8, comprises: In response to the command of the aircraft to perform a reentry and return mission, the control solenoid valve is opened, so that the jet gas ejected by the jet device is ejected from the deployment hole, thereby switching the protective wing from the retracted state to the deployed state; After the unfolding rod is unfolded to its maximum angle, it is locked by a locking mechanism; In response to the command indicating that the protective wing has completed deployment, the solenoid valve is controlled to close. The position of the aircraft during reentry and return is determined. When the aircraft is in the first position, the solenoid valve is controlled to open again, so that the jet gas ejected by the jet device is ejected from the jet hole to form thermal protection for the tail end of the deploying rod. The system determines the aircraft's position and / or the pressure difference between the inside and outside of the jet device during reentry and return. When the aircraft is in the second position and / or the pressure difference between the inside and outside of the jet device is balanced, the system controls the solenoid valve to close.

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