A special-shaped sub-cavity pressure-resistant supply tank structure and a design method thereof

Abstract

The application discloses a special-shaped sub-cavity pressure-resistant supply tank structure and a design method thereof, and relates to the technical field of active thermal protection. The special-shaped sub-cavity pressure-resistant supply tank structure comprises a tank body for storing liquid working medium and a liquid collecting and discharging body connected to one side of the tank body and used for collecting and discharging the liquid working medium. The liquid collecting and discharging body is provided with a liquid injection / discharge port in communication with the inside of the liquid collecting and discharging body, and is connected to a driving component through an air inlet. The driving component introduces gas with a certain pressure into the inside of each liquid storage cavity through the air inlet, and the gas with pressure drives the liquid working medium into the inside of the liquid collecting and discharging body for discharge. The liquid cooling working medium is efficiently and reliably stored and transported, so that the working medium is stably supplied to an active cooling system. The structure such as a spherical tank is not adopted, the space utilization rate can be improved, the design requirements of a high-integration-degree aircraft can be met, and the carrying capacity of the tank for the narrow, flat and special-shaped space design of the aircraft can be improved by arranging the reinforcing ribs.

Description

Technical Field

[0001] This invention relates to the field of active thermal protection technology, specifically to a non-standard compartmentalized pressure-resistant supply tank structure and its design method. Background Technology

[0002] The nose cone of a high-speed aircraft is the most severely heated part due to stagnant gas heating, and it is also a major challenge in aircraft thermal protection design. In the history of aircraft development, a "thermal barrier" phenomenon once existed, where the nose cone material could not withstand the aerodynamic heating of the aircraft, resulting in severe ablation and affecting flight success. This problem was later solved by increasing the nose cone radius and developing new materials. In recent years, near-space high-speed aircraft have developed rapidly. These aircraft fly within the atmosphere for extended periods, making aerodynamic heating and thermal protection issues even more prominent. At the same time, near-space high-speed aircraft have high requirements for lift-to-drag ratio. A small nose cone can effectively reduce drag and thus improve the lift-to-drag ratio. Therefore, finding a balance between high lift-to-drag ratio and good thermal protection performance has become a crucial consideration affecting aircraft performance. Tests have shown that traditional passive thermal protection methods using high-temperature resistant metals and composite materials are no longer sufficient to meet the non-ablation requirements under extreme high-speed environments, becoming a bottleneck restricting aircraft performance. Therefore, active thermal protection methods based on sweating cooling have emerged to address the nose cone thermal protection problem in extreme environments.

[0003] End-point cooling requires the use of a working fluid tank for the storage and management of the cooling working fluid. Traditional working fluid tanks are all regular structures: spherical, capsule-shaped, columnar, etc. However, the space inside an aircraft is small and the shape of the available space is often irregular. Using traditional tanks will result in a huge waste of space utilization, low space utilization, and difficulty in meeting the design requirements of current highly integrated aircraft. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this invention provides a non-standard, compartmentalized, pressure-resistant supply tank structure and its design method, which solves the problem that traditional aircraft tanks have regular shapes, low space utilization, and are difficult to meet the design requirements of current highly integrated aircraft.

[0005] To achieve the above objectives, the present invention is implemented through the following technical solution: a non-standard cavity pressure-resistant supply tank structure, comprising a tank body for storing liquid working fluid and a liquid collection and discharge port connected to one side of the tank body for collecting and discharging the liquid working fluid, wherein the liquid collection and discharge port is provided on one side and communicates with its interior.

[0006] The interior of the tank is divided into multiple liquid storage chambers by reinforcing ribs. Each liquid storage chamber is equipped with a driving component for squeezing the liquid working fluid out of the storage chamber and into the liquid collection and discharge chamber.

[0007] Furthermore, the driving component includes a gas-liquid isolation membrane and a membrane mounting rod. The gas-liquid isolation membrane is sleeved on the surface of the membrane mounting rod, and the membrane mounting rod is fixedly installed inside the liquid storage chamber. An air inlet is fixedly connected to each liquid storage chamber on the side of the tank away from the liquid collection and discharge position. The air inlet is connected to the inside of the gas-liquid isolation membrane.

[0008] Furthermore, a plurality of the reinforcing ribs are evenly arrayed inside the tank body, and the connection between the reinforcing ribs and the inner wall of the tank body is rounded.

[0009] Furthermore, the tank body, liquid collection and drainage system, and reinforcing ribs are all made of titanium alloy, and the tank body and liquid collection and drainage system are welded together.

[0010] Furthermore, the tank body and the reinforcing ribs are integrally formed using 3D printing technology, while the liquid collection and drainage system is manufactured through machining.

[0011] Furthermore, the length of the storage tank is 500mm to 1500mm, and the spatial envelope thickness of the storage tank is ≥25mm.

[0012] Furthermore, the injection / drainage port is located in the middle of the liquid collection and drainage system, and the surface of the liquid collection and drainage system has several collection holes. The interior of the liquid collection and drainage system is connected to the interior of the storage tank through the collection holes, and the collection holes correspond one-to-one with the storage chamber.

[0013] Furthermore, the cross-sectional shape of the storage tank is arc-shaped, and the cross-sectional shape of the liquid collection and drainage section is adapted to the cross-sectional shape of the storage tank.

[0014] Furthermore, a skin is fixedly connected to the surface of the storage tank.

[0015] A design method for a non-standard, compartmentalized, pressure-resistant supply tank includes the following steps:

[0016] S1, Based on the tank space, weight and filling constraints, titanium alloy material was initially selected, and the initial tank structure layout was designed;

[0017] S2. Analyze whether the initial tank structure layout meets the requirements of material performance and structural change in terms of strength and stiffness. If not, optimize the wall thickness and cross-sectional shape of the initial tank structure until the strength and stiffness meet the requirements of material performance and structural change.

[0018] S3. Analyze whether the tank structure, whose strength and stiffness meet the requirements of material performance and structural change, meets the requirements of space, weight and filling. If it does, the design is complete. Otherwise, adjust the number of reinforcing ribs, change the tank material, and repeat S1-S3.

[0019] The present invention has the following beneficial effects:

[0020] (1) The irregularly shaped, compartmentalized, pressure-resistant supply tank structure, by setting up a tank body, a liquid collection and drainage system and a driving component, distributes the liquid working medium to the interior of each liquid storage chamber for cooling. After cooling, the liquid working medium is squeezed into the interior of the liquid collection and drainage system by the driving component and discharged. It efficiently and reliably stores the cooling working medium, thereby stably supplying the working medium to the active cooling system. It does not adopt the traditional spherical, capsule-shaped, or columnar structure, which can improve the space utilization rate and meet the design requirements of current highly integrated aircraft. At the same time, the reinforcing ribs set inside the tank body can improve the load-bearing capacity of the tank with a small, flat, and irregularly shaped space design inside the aircraft.

[0021] (2) The design method of the irregularly shaped compartment pressure-resistant supply tank structure is to analyze the strength and stiffness of the irregularly shaped compartment tank under working pressure based on the layout design of the irregularly shaped compartment tank. Based on space and weight constraints, the tank structure is optimized by adjusting the cross-sectional shape of the tank, the wall thickness of the tank, and the number of reinforcing ribs, so as to obtain the final design scheme of the irregularly shaped compartment pressure-resistant supply tank. It can adapt to the small, flat and irregular space design inside the aircraft and meet the design requirements of the current high-integration aircraft.

[0022] Of course, any product implementing this invention does not necessarily need to achieve all of the advantages described above at the same time. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the storage tank structure of the present invention;

[0024] Figure 2 This is a schematic diagram of the structure of the drain port and collection hole of the present invention;

[0025] Figure 3 For the present invention Figure 2 A sectional view along line AA.

[0026] Figure 4 For the present invention Figure 2 Sectional view along line BB;

[0027] Figure 5 This is a schematic diagram of the gas-liquid isolation film structure when the liquid working fluid enters the storage chamber according to the present invention;

[0028] Figure 6 This is a cross-sectional view of the internal structure of the storage tank of the present invention;

[0029] Figure 7 This is a schematic diagram of the gas-liquid isolation membrane structure after the liquid working fluid is discharged from the storage chamber according to the present invention;

[0030] Figure 8 This is a schematic diagram of the internal structure of the storage tank of the present invention;

[0031] Figure 9 This is a schematic diagram of the structure of the thin film mounting rod of the present invention.

[0032] Figure 10 This is a flowchart illustrating the design method of the irregularly shaped, compartmentalized, pressure-resistant supply tank structure of the present invention.

[0033] In the diagram, 1. Storage tank; 2. Liquid collection and drainage port; 3. Injection / drainage port; 4. Reinforcing rib; 5. Storage chamber; 6. Gas-liquid isolation membrane; 7. Membrane mounting rod; 8. Air inlet; 9. Liquid collection hole; 10. Skin. Detailed Implementation

[0034] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] In the description of this invention, it should be understood that the terms "opening", "upper", "lower", "thickness", "top", "middle", "length", "inner", "around", etc., which indicate orientation or positional relationship, are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the components or elements referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting this invention.

[0036] Please see Figures 1-9 The present invention provides a technical solution: a non-standard cavity pressure-resistant supply tank structure, including a tank body 1 for storing liquid working fluid and a liquid collection and discharge 2 connected to one side of the tank body 1 for collecting and discharging the liquid working fluid, and an injection / discharge port 3 connected to the inside of the liquid collection and discharge 2.

[0037] The interior of the storage tank 1 is divided into multiple liquid storage chambers 5 by reinforcing ribs 4. Each liquid storage chamber 5 is equipped with a driving component for squeezing the liquid working medium out of the storage chamber 5 and into the liquid collection and discharge chamber 2.

[0038] Specifically, such as Figure 5 7 and Figure 9 As shown, the driving component includes a gas-liquid isolation membrane 6 and a membrane mounting rod 7. The gas-liquid isolation membrane 6 is sleeved on the surface of the membrane mounting rod 7. The membrane mounting rod 7 is fixedly installed inside the liquid storage chamber 5. An air inlet 8 is fixedly connected to each liquid storage chamber 5 on the side of the tank body 1 away from the liquid collection and discharge 2. The air inlet 8 is connected to the inside of the gas-liquid isolation membrane 6.

[0039] This implementation plan is divided into a liquid working fluid filling process and a liquid working fluid supply process.

[0040] Filling process: The liquid working medium is added to the liquid collection and drainage 2 through the injection / drainage port 3, and further enters the interior of the storage tank 1. The reinforcing rib 4 divides the interior of the storage tank 1 into multiple storage chambers 5. The liquid working medium fills into each storage chamber 5 to realize the filling of the liquid working medium.

[0041] Supply process: The reinforcing rib 4 divides the interior of the tank 1 into multiple liquid storage chambers 5. When the working fluid is filled, the external pressurized gas enters the interior of the gas-liquid isolation film 6 through the air inlet 8, causing the gas-liquid isolation film 6 to expand, thereby squeezing the liquid working fluid inside the liquid storage chamber 5 into the liquid collection and drainage 2. The liquid working fluid is further discharged from the liquid injection / drainage port 3. This process is repeated to stably supply the working fluid to the active cooling system, thereby achieving cooling.

[0042] Inside the storage chamber 5, the liquid working medium and the driving gas are separated by a gas-liquid isolation membrane. The gas-liquid isolation membrane transmits force but does not bear force. When the tank is working, the driving gas fills the middle of the gas-liquid isolation membrane with gas, causing the liquid working medium to be discharged into the liquid collection and drainage chamber and finally discharged from the liquid injection / drainage port 3. The above method can achieve the effect of high liquid working medium filling rate.

[0043] Specifically, such as Figure 1 As shown, several reinforcing ribs 4 are evenly arranged inside the tank body 1, and the connection between the reinforcing ribs 4 and the inner wall of the tank body 1 is rounded.

[0044] In this implementation scheme, the reinforcing rib 4 can enhance the structural strength. The upper and lower connecting reinforcing rib 4 in the thin-walled tank can significantly improve the load-bearing capacity, and the rounded corner design can avoid excessive stress concentration.

[0045] Specifically, the tank body 1, the liquid collection and drainage 2, and the reinforcing rib 4 are all made of titanium alloy, and the tank body 1 and the liquid collection and drainage 2 are welded together.

[0046] The storage tank 1 and the reinforcing rib 4 are integrally formed by 3D printing, while the liquid collection and drainage 2 is manufactured by machining.

[0047] In this implementation scheme, the titanium alloy material has high specific strength and specific stiffness performance, as well as good compatibility. The main body of the storage tank is manufactured in two sections. The storage tank body 1 is integrally formed by 3D printing process, and the liquid collection and drainage 2 is manufactured by machining or 3D printing process. After the storage tank body 1 is 3D printed, it is first assembled with the gas-liquid separation diaphragm. After the two sections are manufactured separately, they are assembled into one piece by welding process.

[0048] Specifically, the length of the storage tank 1 is 500 mm to 1500 mm, and the spatial envelope thickness of the storage tank 1 is ≥25 mm.

[0049] In this embodiment, the length of the storage tank 1 is 500mm to 1500mm and the thickness is ≥25mm, which can adapt to the small, flat, and irregularly shaped space inside the aircraft. At the same time, the thickness is set to be above 25mm to prevent the structural strength from being reduced due to excessive thinness.

[0050] Specifically, such as Figure 8 and Figure 2 As shown, the liquid injection / drainage port 3 is located in the middle of the liquid collection and drainage 2. Several liquid collection holes 9 are opened on the surface of the liquid collection and drainage 2. The interior of the liquid collection and drainage 2 is connected to the interior of the storage tank 1 through the liquid collection holes 9. The liquid collection holes 9 correspond one-to-one with the storage chamber 5.

[0051] In this embodiment, the liquid collection hole 9 corresponds one-to-one with the liquid storage chamber 5, which can achieve better diversion, so that the interior of each liquid storage chamber 5 can be filled with liquid working medium, and at the same time facilitates liquid drainage.

[0052] Specifically, such as Figure 8 As shown, the width of the storage tank 1 gradually increases from the side closest to the liquid collection and discharge 2 to the side furthest from the liquid collection and discharge 2. The cross-sectional shape of the storage tank 1 is arc-shaped, and the cross-sectional shape of the liquid collection and discharge 2 is adapted to the cross-sectional shape of the storage tank 1.

[0053] In this embodiment, the tank body 1 is designed with the above shape, which can adapt to the small, flat, and irregular space inside the aircraft.

[0054] Specifically, such as Figure 6 As shown, a skin 10 is fixedly connected to the surface of the storage tank 1.

[0055] In this embodiment, the skin 10 can protect the tank structure from external environmental damage, while its streamlined shape can better match the space of the aircraft, improving the space utilization of the aircraft.

[0056] like Figure 10 As shown, a design method for a non-standard, compartmentalized, pressure-resistant supply tank includes the following steps:

[0057] S1. Based on the tank space, weight and filling constraints, titanium alloy material is initially selected, and the initial tank structure layout is designed.

[0058] S2. Analyze whether the initial tank structure layout meets the requirements of material performance and structural change in terms of strength and stiffness. If not, optimize the wall thickness and cross-sectional shape of the initial tank structure until the strength and stiffness meet the requirements of material performance and structural change.

[0059] S3. Analyze whether the tank structure, which meets the requirements of material performance and structural change in terms of strength and stiffness, meets the requirements of space, weight and filling. If it does, the design is complete. Otherwise, adjust the number of reinforcing ribs, change the tank material, and repeat S1-S3.

[0060] In this implementation plan, based on the layout design of the irregularly shaped compartmented storage tank, the strength and stiffness under working pressure are analyzed. Based on space and weight constraints, the tank structure is optimized by adjusting the cross-sectional shape, wall thickness, and number of reinforcing ribs, resulting in the final design scheme of the irregularly shaped compartmented pressure-resistant supply tank.

[0061] 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.

[0062] The preferred embodiments of the present invention disclosed above are merely illustrative of the invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention. The invention is limited only by the claims and their full scope and equivalents.

Claims

1. A uniquely shaped, compartmentalized, pressure-resistant supply tank structure, characterized in that, It includes a storage tank (1) for storing liquid working fluid and a liquid collection and discharge port (2) connected to one side of the storage tank (1) for collecting and discharging the liquid working fluid. The liquid collection and discharge port (2) is provided with an injection / discharge port (3) connected to its interior. The interior of the tank body (1) is divided into multiple liquid storage chambers (5) by reinforcing ribs (4). Each liquid storage chamber (5) is provided with a driving component for squeezing the liquid working medium out of the liquid storage chamber (5) and into the liquid collection and discharge chamber (2). The driving component includes a gas-liquid isolation membrane (6) and a membrane mounting rod (7). The gas-liquid isolation membrane (6) is sleeved on the surface of the membrane mounting rod (7). The membrane mounting rod (7) is fixedly installed inside the liquid storage chamber (5). An air inlet (8) is fixedly connected to each liquid storage chamber (5) on the side of the tank body (1) away from the liquid collection and discharge (2). The air inlet (8) is connected to the inside of the gas-liquid isolation membrane (6). The liquid injection / drainage port (3) is located in the middle of the liquid collection and drainage (2). Several liquid collection holes (9) are opened on the surface of the liquid collection and drainage (2). The interior of the liquid collection and drainage (2) is connected to the interior of the storage tank (1) through the liquid collection holes (9). The liquid collection holes (9) correspond one-to-one with the storage chamber (5). This improves the load-bearing capacity of the storage tank with its small, flat, and irregularly shaped space design inside the aircraft.

2. The irregularly shaped, compartmentalized, pressure-resistant supply tank structure according to claim 1, characterized in that: Several reinforcing ribs (4) are evenly arranged in an array inside the tank body (1), and the connection between the reinforcing ribs (4) and the inner wall of the tank body (1) is rounded.

3. The irregularly shaped, compartmentalized, pressure-resistant supply tank structure according to claim 2, characterized in that: The tank body (1), the liquid collection and drainage (2) and the reinforcing rib (4) are all made of titanium alloy. The tank body (1) and the liquid collection and drainage (2) are welded together.

4. The irregularly shaped, compartmentalized, pressure-resistant supply tank structure according to claim 3, characterized in that: The storage tank (1) and the reinforcing rib (4) are integrally formed by 3D printing, and the liquid collection and drainage (2) is manufactured by machining.

5. The irregularly shaped, compartmentalized, pressure-resistant supply tank structure according to claim 4, characterized in that: The length of the storage tank (1) is 500mm to 1500mm, and the spatial envelope thickness of the storage tank (1) is ≥25mm.

6. The irregularly shaped, compartmentalized, pressure-resistant supply tank structure according to claim 1, characterized in that: The cross-sectional shape of the storage tank (1) is arc-shaped, and the cross-sectional shape of the liquid collection and discharge (2) is adapted to the cross-sectional shape of the storage tank (1).

7. A non-standard, compartmentalized, pressure-resistant supply tank structure according to any one of claims 1-6, characterized in that: The surface of the storage tank (1) is fixedly connected with a skin (10).

8. The design method of the irregularly shaped, compartmentalized, pressure-resistant supply tank structure according to any one of claims 1-6, characterized in that, Includes the following steps: S1. Based on the tank space, weight and filling constraints, select titanium alloy material and design the initial tank structure layout. S2. Analyze whether the initial tank structure layout meets the requirements of material performance and structural change in terms of strength and stiffness. If not, optimize the wall thickness and cross-sectional shape of the initial tank structure until the strength and stiffness meet the requirements of material performance and structural change. S3. Analyze whether the tank structure, which meets the requirements of material performance and structural change in terms of strength and stiffness, meets the requirements of space, weight and filling. If it does, the design is complete. Otherwise, adjust the number of reinforcing ribs, change the tank material, and repeat S1-S3.

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