Supersonic aircraft and air inlet structure thereof

Abstract

The invention provides a supersonic aircraft and an air inlet structure thereof, and the air inlet structure comprises a shell which comprises a bottom wall and a side wall connected to the bottom wall; and at least part of each separation channel assembly is located in the shell, the separation channel assembly and the bottom wall of the shell are arranged in a spaced mode to define an air inlet channel, and each separation channel assembly is detachably connected with the side wall. An air inlet is defined by one end of the bottom wall and the side wall, and an air outlet is defined by the partition channel assembly and the corresponding outer edge of the side wall. Because each separation channel assembly and the shell are of an independent module structure and can be assembled in a detachable mode, the cost is low, the maintainability is good, special process machining is not needed, the structural deformation is small, and the size of each module structure is detectable and measurable. When the shell or any separation channel assembly is damaged, only the damaged part needs to be replaced, and the whole air inlet structure does not need to be scrapped.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft manufacturing, and in particular to a supersonic aircraft and an air intake structure thereof. Background Art

[0002] The air intake structure of a supersonic aircraft is a very important aerodynamic component, which is used to supply air to the aircraft engine. The interior of the air intake structure must be sealed, and there is a certain amount of pneumatic pressure inside during operation. Currently, most of the air intake structures of supersonic aircraft are made of metal or non-metal and formed into an integrated structure through a casting process, or several metal plates are spliced ​​and welded into an integrated structure.

[0003] The air intake structure produced by one-piece molding has good integrity and high strength, but it has poor precision, high cost, and is prone to cracks during use. In addition, since the interior is a closed area, it is difficult to confirm the surface quality of the internal structure, and the dimensional tolerance is also difficult to determine and cannot be detected. At the same time, since it cannot be disassembled, it can only correspond to one technical state of the air intake duct. When a local problem occurs, it is easy to cause the entire air intake structure to be scrapped.

[0004] Although the air intake structure produced by welding has high flow path precision, its complex structure leads to high manufacturing cost. Also, since welding is a special process, defects are prone to occur in the welds during the processing, and problems such as welding deformation and poor sealing may occur. At the same time, since it cannot be disassembled, it can only correspond to one technical state of the air intake duct. If problems occur locally, the entire air intake structure may be scrapped. Summary of the invention

[0005] In order to solve the above problems, the present invention proposes a supersonic aircraft and an air intake structure thereof.

[0006] In the first aspect, the present invention proposes an air intake structure of a supersonic aircraft, which comprises: a shell, comprising a bottom wall and a side wall connected to the edge of the bottom wall, the bottom wall extending along a first direction; and at least one channel partition assembly, at least part of each channel partition assembly is located in the shell and is spaced from the bottom wall of the shell along a second direction to enclose an air intake channel, and each channel partition assembly is detachably connected to the side wall. Wherein, one end of the bottom wall in the first direction encloses an air inlet connected to the air intake channel with the side wall, and the corresponding outer edge of the channel partition assembly and the side wall away from the bottom wall encloses an air outlet connected to the air intake channel.

[0007] Further, the side wall includes two first side wall portions and a second side wall portion, the two first side wall portions are arranged opposite to each other along the third direction, and one end of the two first side wall portions in the first direction and the bottom wall form the air inlet, and the second side wall portion is arranged at the other end of the two first side wall portions in the first direction. In the second direction, a notch is arranged at one end of each first side wall portion away from the bottom wall, and the partition assembly is arranged between the two opposite notches and is detachably connected to the edge of the first side wall portion that forms the notch.

[0008] Furthermore, each of the channel partition components includes: a channel partition support, which is arranged between two opposite notches and is detachably connected to the edge of the first side wall portion that surrounds the notch, the channel partition support is spaced apart from the bottom wall in the second direction to surround the air intake channel, and at least a portion of the channel partition support corresponding to the notch is a frame structure; and two guard plates, which are arranged on both sides of the channel partition support along the third direction and are located in the corresponding notch, and each of the guard plates is detachably connected to the channel partition support.

[0009] Furthermore, the channel partition support includes: a partition portion, which is located in the shell and is spaced apart from the bottom wall to enclose the air intake channel, and the partition portion is detachably connected to the edge of the first side wall portion that encloses the notch; and a frame portion, which is connected to the partition portion and encloses a plurality of cavities with the partition portion, and the frame portion is detachably connected to each of the guard plates.

[0010] Furthermore, a plurality of first mounting holes arranged at intervals along the extension direction of the edge are provided on the edge of the first side wall portion surrounding the notch, and a plurality of second mounting holes are correspondingly provided on the partition portion, and the second mounting holes are bolted to the first mounting holes through fasteners.

[0011] Furthermore, a plurality of third mounting holes are arranged on the circumferential edge of each guard plate, and a plurality of fourth mounting holes are correspondingly arranged on the frame portion, and the fourth mounting holes are bolted to the third mounting holes via fasteners.

[0012] Furthermore, each of the channel partition assemblies also includes a seal, which is arranged between each of the first side wall portions and the partition portion, and the partition portion is sealed and connected to each of the first side wall portions through the corresponding seal.

[0013] Furthermore, a mounting groove is provided on the surface of the partition part facing each of the first side wall parts, the mounting groove is located between the connection position between the partition part and the first side wall part and the edge of the partition part, and the inner wall of the mounting groove is connected to the sealing member. Part of the sealing member extends out of the mounting groove to seal the partition support and the first side wall part.

[0014] Furthermore, the shell further includes a stop wall, the stop wall is located at one end of the first side wall portion away from the second side wall portion, and the stop wall connects the two first side wall portions and together with the two first side wall portions encloses the air inlet. The number of the channel partition assemblies is multiple, and the multiple channel partition assemblies include a first channel partition assembly and a second channel partition assembly, and the first channel partition assembly and the second channel partition assembly are spaced apart in the first direction. Among them, one end of the first channel partition assembly abuts against the stop wall, and the other end forms an air outlet with the corresponding outer edges of the two first side wall portions, and the second channel partition assembly is spaced apart from the second side wall portion and forms an air outlet with the second side wall portion and the corresponding outer edges of the two first side wall portions.

[0015] Furthermore, the stop wall includes a stop portion and limiting portions arranged on both sides of the stop portion in the third direction, and the limiting portions protrude from the stop portion along the first direction. One end of the first channel partition component is located between the two limiting portions and abuts against the stop portion, and the first channel partition component is detachably connected to the two limiting portions.

[0016] In a second aspect, the present invention provides a supersonic aircraft, which includes an aircraft engine and the above-mentioned air intake structure.

[0017] The beneficial effects of the present invention are as follows: In the air intake structure of the supersonic aircraft of the present application, the air intake structure includes a shell and at least one partition assembly, and all the partition assemblies are assembled with the shell and together form an air intake channel with an air inlet and an air outlet, so as to utilize the air intake channel to supply air to the aircraft engine. Since each partition assembly and the shell are independent module structures and can be assembled in a detachable manner, the modules can be disassembled and assembled as needed, and the cost is low, the maintainability is good, and no special process processing is required, the structural deformation is small, and the structural dimensions of each module are detectable and measurable. Moreover, when the shell or any partition assembly is damaged, only the damaged parts need to be replaced, and the entire air intake structure does not need to be scrapped. Moreover, based on the independence between each partition assembly and the shell, it is possible to form air intake channels with different cross-sectional shapes by replacing partition assemblies or shells of different shapes, thereby meeting different performance index requirements without adjusting the entire air intake structure.

[0018] The air intake structure of the present application is particularly suitable for use in the process of early technical status iteration. In related tests to assess the air intake structure and aircraft engine performance, the relevant parameters of the air intake can be changed by changing the cross-sectional shape of the air intake passage, thereby assessing different performance indicators. Compared with the air intake structure produced by one-piece molding and the air intake structure produced by butt welding, this can be achieved by simply replacing the internal partition assembly or the shell.

[0019] This Summary is provided to introduce a selection of concepts in a simplified form that are further described below in the Detailed Description. This Summary is not intended to identify key features or essential features of the disclosure, nor is it intended to limit the scope of the disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above and other objects, features and advantages of the present disclosure will become more apparent through a more detailed description of exemplary embodiments of the present disclosure in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present disclosure.

[0021] Figure 1 A schematic diagram of the structure of the supersonic aircraft of the present invention is shown; Figure 2 A three-dimensional schematic diagram of the air intake structure of the present invention is shown; Figure 3 A schematic diagram of the internal structure of the air intake structure of the present invention is shown; Figure 4 A schematic diagram of the three-dimensional structure of the housing of the present invention is shown; Figure 5 for Figure 4 The main view; Figure 6 A schematic diagram of the three-dimensional structure of a channel partition assembly of the present invention is shown; Figure 7 A schematic diagram of the three-dimensional structure of another channel partition assembly of the present invention is shown; Figure 8 A schematic diagram of the three-dimensional structure of a partition support of the present invention is shown; Fig. 9 A schematic diagram of the three-dimensional structure of another aisle separation support of the present invention is shown; Fig.10 A schematic structural diagram of a guard plate of the present invention is shown; Fig.11 A schematic structural diagram of another guard plate of the present invention is shown.

[0022] The reference numerals are as follows: 100. Air intake structure; 10. Shell; 11. Bottom wall; 12. Side wall; 121. First side wall portion; 122. Second side wall portion; 13. Stop wall; 131. Stop portion; 132. Limiting portion; 20, channel partition assembly; 20A, first channel partition assembly; 20B, second channel partition assembly; 21. aisle support; 211. partition plate; 212. frame; 22. guard plate; 23. sealing member; A, air inlet channel; A1, air inlet; A2, air outlet; B, notch; C1, first mounting hole; C2, second mounting hole; C3, third mounting hole; C4, fourth mounting hole; D, mounting slot; 200. Aircraft engines; X, first direction; Y, second direction; Z, third direction. DETAILED DESCRIPTION

[0023] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present disclosure more thorough and complete, and to fully convey the scope of the present disclosure to those skilled in the art.

[0024] As used herein, the term "including" and its variations mean open inclusion, i.e., "including but not limited to". Unless otherwise stated, the term "or" means "and / or". The term "based on" means "based at least in part on". The terms "an example embodiment" and "an embodiment" mean "at least one example embodiment". The term "another embodiment" means "at least one additional embodiment". The terms "first", "second", etc. may refer to different or the same objects. Other explicit and implicit definitions may also be included below.

[0025] The following describes a supersonic aircraft and its air intake structure according to an embodiment of the present application with reference to the accompanying drawings.

[0026] Figure 1 The schematic diagram of the structure of the supersonic aircraft of the present invention is shown.

[0027] Reference Figure 1 The supersonic aircraft 1000 of the embodiment of the present application includes an aircraft engine 200 and an air intake structure 100. The air intake structure 100 is used to supply air to the aircraft engine 200.

[0028] Figure 2 The three-dimensional structure schematic diagram of the air intake structure of the present invention is shown. Figure 3 A schematic diagram of the internal structure of the air intake structure of the present invention is shown.

[0029] Reference Figure 2 and Figure 3 The air intake structure 100 of the supersonic aircraft according to the embodiment of the present application includes a shell 10 and at least one partition assembly 20.

[0030] The housing 10 includes a bottom wall 11 and a side wall 12 connected to the edge of the bottom wall 11, and the side wall 12 and the bottom wall 11 together form a cavity. The bottom wall 11 extends along a first direction X.

[0031] It can be understood that the first direction X is the length direction of the bottom wall 11. Specifically, in the first direction X, the bottom wall 11 as a whole can be a flat structure, a curved structure, or a combination of a flat structure and a curved structure, but no matter what structure the bottom wall 11 has, the bottom wall 11 always has a certain length along the first direction X.

[0032] The number of the channel partition assembly 20 can be one or more. At least part of each channel partition assembly 20 is located in the housing 10 and is spaced from the bottom wall 11 of the housing 10 along the second direction Y to enclose the air intake channel A, and each channel partition assembly 20 is detachably connected to the side wall 12 of the housing 10.

[0033] The bottom wall 11 of the housing 10 and the side wall 12 at one end in the first direction X form an air inlet A1 connected to the air inlet channel A. In the second direction Y, the partition assembly 20 and the corresponding outer edge of the side wall 12 away from the bottom wall 11 form an air outlet A2 connected to the air inlet channel A.

[0034] Specifically, when the number of channel partition assemblies 20 is one, the bottom of the channel partition assembly 20 and the bottom wall 11 of the shell 10 together form an air intake channel A; when the number of channel partition assemblies 20 is multiple, the multiple channel partition assemblies 20 are arranged side by side along the first direction X, and the bottom of the multiple channel partition assemblies 20 and the bottom wall 11 of the shell 10 together form an air intake channel A.

[0035] In this embodiment, the air intake structure 100 includes a shell 10 and at least one partition assembly 20, and all the partition assemblies 20 are assembled with the shell 10 and together form an air intake channel A with an air inlet A1 and an air outlet A2, so as to supply air to the aircraft engine 200 using the air intake channel A. Since each partition assembly 20 and the shell 10 are independent module structures and can be assembled in a detachable manner, the modules can be disassembled and assembled as needed, with low cost, good maintainability, and no special process processing (mature process) is required, the structural deformation is small, and the structural dimensions of each module can be inspected and measured. In addition, when the shell 10 or any partition assembly 20 is damaged, it is only necessary to replace the damaged parts without scrapping the entire air intake structure 100. In addition, based on the independence between each partition assembly 20 and the shell 10, the partition assembly 20 or the shell 10 of different shapes can be replaced to form an air intake channel A with different cross-sectional shapes, thereby meeting different performance index requirements without adjusting the entire air intake structure 100.

[0036] Therefore, the air intake structure 100 of the present application is particularly suitable for use in the process of early technical status iteration. In relevant tests to evaluate the performance of the air intake structure 100 and the aircraft engine 200, the relevant parameters of the air intake can be changed by changing the cross-sectional shape of the air intake channel A, thereby evaluating different performance indicators. Compared with the air intake structure produced by one-piece molding and the air intake structure produced by butt welding, this can be achieved by simply replacing the internal partition assembly 20 or the shell 10.

[0037] In some embodiments, the housing 10 may be formed by machining of metal materials, which facilitates the control of the inner and outer surface dimensions and surface roughness of the housing 10. In addition, the housing 10 may be detachably connected to the channel partition assembly 20 by setting screw holes, and after the two are assembled and connected, the inner wall of the housing 10 and the bottom of the channel partition assembly 20 together form the air inlet channel A.

[0038] Figure 4 FIG. 1 shows a three-dimensional structural schematic diagram of a housing of the present invention, Figure 5 for Figure 4 main view.

[0039] Reference Figure 4 and Figure 5 The side wall 12 of the housing 10 includes two first side wall portions 121 and a second side wall portion 122 .

[0040] The two first side wall portions 121 are arranged opposite to each other along the third direction Z, and one end of the two first side wall portions 121 in the first direction X forms an air inlet A1 with the bottom wall 11, and the second side wall portion 122 is arranged at the other end of the two first side wall portions 121 in the first direction X and forms a closed structure with the two first side wall portions 121. In other words, at both ends of the housing 10 in the first direction X, one is an open end (for air intake) and the other is a closed end.

[0041] In the second direction Y, a notch B is provided at one end of each first side wall portion 121 away from the bottom wall 11, and the channel partition assembly 20 is disposed between two opposite notches B and is detachably connected to the edge of the first side wall portion 121 surrounding the notch B, that is, a small portion of the channel partition assembly 20 (i.e., only the bottom portion) is located in the shell 10 and is detachably connected to the shell 10, while the other portion is exposed to the shell 10 via the notch B. In addition, in the second direction Y, the channel partition assembly 20 and the corresponding outer edge of the first side wall portion 121 away from the bottom wall 11 surround a gas outlet A2 with the gas outlet direction facing the second direction Y.

[0042] In this embodiment, since one end of the shell 10 in the first direction X is set as an open end for air intake, and the other end is a closed end to prevent gas from flowing out from the first direction X, and at the same time, an outlet A2 is formed in the second direction Y with the gas outlet direction facing the second direction Y, it is convenient to supply air to the aircraft engine 200 through the outlet A2 in this direction, thereby improving the compatibility between the air intake structure 100 and the aircraft engine 200.

[0043] Reference Figure 4 The shell 10 further includes a stop wall 13 , which is located at one end of the first side wall portion 121 away from the second side wall portion 122 , and the stop wall 13 connects the two first side wall portions 121 and together with the two first side wall portions 121 forms an air inlet A1 .

[0044] Reference Figure 2 There are multiple lane partition assemblies 20, including a first lane partition assembly 20A and a second lane partition assembly 20B, which are spaced apart in the first direction X. One end of the first lane partition assembly 20A abuts against the stop wall 13, and the other end and the corresponding outer edges of the two first side wall portions 121 form an air outlet A2, and the second lane partition assembly 20B is spaced apart from the second side wall portion 122 and forms an air outlet A2 with the second side wall portion 122 and the corresponding outer edges of the two first side wall portions 121.

[0045] Specifically, when the number of channel partition components 20 is two, one end of the first channel partition component 20A abuts against the stop wall 13, and the other end forms an air outlet A2 with the second channel partition component 20B and the corresponding outer edges of the two first side wall portions 121; the second channel partition component 20B is spaced apart from the second side wall portion 122 and forms an air outlet A2 with the second side wall portion 122 and the corresponding outer edges of the two first side wall portions 121.

[0046] When the number of the partition assemblies 20 is more than two, the first partition assembly 20A and the second partition assembly 20B are the partition assemblies 20 located at both ends in the first direction X. Among them, one end of the first partition assembly 20A abuts against the stop wall 13, and the other end of the first partition assembly 20 adjacent to the first partition assembly 20 and the corresponding outer edges of the two first side wall portions 121 form an air outlet A2, and the second partition assembly 20B is spaced apart from the second side wall portion 122 and forms an air outlet A2 with the second side wall portion 122 and the corresponding outer edges of the two first side wall portions 121.

[0047] In this embodiment, different numbers of air outlets A2 can be formed by selecting the number of partition assemblies 20 to adapt to the air supply requirements of different aircraft engines 200, thereby improving the scope of application of the air intake structure 100 of the present application.

[0048] Continue to refer to Figure 2 and Figure 4 The stop wall 13 includes a stop portion 131 and limiting portions 132 disposed on both sides of the stop portion 131 in the third direction Z, and the limiting portions 132 protrude from the stop portion 131 along the first direction X. One end of the first lane partition component 20A is located between the two limiting portions 132 and abuts against the stop portion 131, and the first lane partition component 20A is detachably connected to the two limiting portions 132.

[0049] In this embodiment, the channel partition assembly 20 can be quickly positioned and installed by the positions of the two limiting portions 132. At the same time, the channel partition assembly 20 is connected to the limiting portion 132, which can further improve the connection reliability between the channel partition assembly 20 and the housing 10.

[0050] Figure 6 A schematic diagram of the three-dimensional structure of a channel partition assembly of the present invention is shown. Figure 7 The figure shows a three-dimensional structural diagram of another channel partition assembly of the present invention. Figure 6 and Figure 7 The general structure of the partition components is the same, but the sizes are different.

[0051] Reference Figure 6 and Figure 7 Each partition assembly 20 includes a partition support 21 and two guard plates 22.

[0052] The channel partition support 21 is disposed between two opposite notches B and is detachably connected to the edge of the first side wall portion 121 surrounding the notch B, and the portion of the channel partition support 21 located inside the housing 10 is spaced from the bottom wall 11 along the second direction Y to surround the air intake channel A. Two guard plates 22 are disposed on both sides of the channel partition support 21 along the third direction Z and are located in the corresponding notches B, and each guard plate 22 is detachably connected to the channel partition support 21.

[0053] In this embodiment, a detachable connection between the channel partition assembly 20 and the first side wall portion 121 of the shell 10 is achieved through the channel partition support 21, and by arranging protective plates 22 on both sides of the channel partition support 21, a rectifying effect can be achieved to avoid the influence of the external structure of the channel partition support 21 on the airflow.

[0054] Specifically, in order to easily control the inner and outer surface dimensions and surface roughness of the partition support 21, the partition support 21 can be formed by metal machining. The two guard plates 22 can be formed by metal sheet processing or composite material compression molding, and the surface of each guard plate 22 can be provided with a countersunk screw hole for connecting the partition support 21.

[0055] Continue to refer to Figure 6 and Figure 7 The partition support 21 includes a partition portion 211 and a frame portion 212. The partition portion 211 is located in the housing 10 and is spaced apart from the bottom wall 11 to enclose the air intake channel A, and the partition portion 211 is detachably connected to the edge of the first side wall portion 121 that encloses the notch B. The frame portion 212 is connected to the partition portion 211 and encloses a plurality of cavities with the partition portion 211, and the frame portion 212 is detachably connected to each guard plate 22.

[0056] It can be understood that the partition part 211 is the bottom part of the partition support 21 extending along the edge of the first side wall part 121 that surrounds the notch B. It is a solid structure as a whole and can be detachably connected to the first side wall part 121; and the frame part 212 is the part of the partition support 21 corresponding to the notch B, that is, the other part except the bottom part. Among them, the frame part 212 is a structure with a hollow part (also called a hollow structure) formed by multiple rods or beams extending in different directions, and the frame part 212 and the partition part 211 surround multiple cavities.

[0057] In this embodiment, the partition plate portion 211 is used to realize the detachable connection between the channel partition assembly 20 and the first side wall portion 121 of the housing 10, and the portion of the channel partition support 21 (i.e., the frame portion 212) is set as a hollow structure, which can reduce the overall structural quality of the channel partition assembly 20. In addition, based on the setting of the guard plate 22, the guard plate 22 can block the gap B and the hollow structure on the channel partition support 21 corresponding to the gap B, thereby avoiding the influence of the hollow structure on the channel partition support 21 on the airflow.

[0058] Furthermore, the frame portion 212 of each aisle partition support 21 can be connected to the interface of the aircraft engine 200 by providing a flange connection portion.

[0059] Continue to refer to Figure 6 and Figure 7 Each channel partition assembly 20 also includes a seal 23, which is arranged between each first side wall portion 121 and the partition portion 211, and the partition portion 211 is sealed and connected to each first side wall portion 121 through the corresponding seal 23.

[0060] In this embodiment, a seal 23 is provided between each first side wall portion 121 of the shell 10 and the partition portion 211 of the partition assembly 20 to ensure the sealing between the modules and prevent the airflow in the air intake channel A from leaking through the gaps between the modules and affecting the aircraft engine 200.

[0061] Specifically, the seal 23 is made of a flexible composite material, and can play a sealing role between the channel partition assembly 20 and the shell 10 through compression deformation, and the cross-sectional shape of the seal 23 can be circular, rectangular, etc.

[0062] Figure 8 A schematic diagram of the three-dimensional structure of a partition support of the present invention is shown. Fig. 9 FIG. 2 shows a three-dimensional structural diagram of another type of aisle separation support of the present invention. Figure 8 and Fig. 9 The general structure of the aisle supports is the same, but the sizes are different.

[0063] Reference Figure 5 The edge of the first side wall portion 121 of the housing 10 that forms the notch B is provided with a plurality of first mounting holes C1 that are arranged at intervals along the extending direction of the edge. Figure 8 and Fig. 9 A plurality of second mounting holes C2 are correspondingly arranged on the partition plate portion 211 of the partition assembly 20. The first mounting hole C1 is a through hole, and the second mounting hole C2 is a threaded hole. The first mounting hole C1 is threadedly connected to the second mounting hole C2 through a fastener (such as a bolt) to achieve a detachable connection between the housing 10 and the partition assembly 20.

[0064] Since the first mounting holes C1 are distributed along the edge of the gap B formed by the first side wall portion 121 , the connection stability between the shell 10 and the channel partition assembly 20 can be ensured.

[0065] Reference Figure 8 and Fig. 9, a mounting groove D is provided on the surface of the partition part 211 facing each first side wall part 121, the mounting groove D is located between the connection position of the partition part 211 and the first side wall part 121 and the edge of the partition part 211 (that is, the mounting groove D is located between the center line of the plurality of second mounting holes C2 and the bottom edge of the partition part 211), and the inner wall of the mounting groove D is connected to the sealing member 23. Part of the sealing member 23 extends out of the mounting groove D to seal the partition support 21 and the first side wall part 121.

[0066] Since the installation groove D for installing the sealing member 23 is located between the connection position between the partition part 211 and the first side wall part 121 and the edge of the partition part 211, the sealing member 23 is arranged close to the connection position between the partition part 211 and the first side wall part 121, so that after the shell 10 is connected with the channel partition assembly 20, the compression amount of the sealing member 23 can be ensured, thereby improving the sealing between the shell 10 and the channel partition assembly 20. In addition, since the inner wall of the installation groove D is connected to the sealing member 23, it can be prevented that the sealing member 23 falls out of the installation groove D during the installation process.

[0067] Specifically, the shape of the sealing member 23 is adapted to the mounting groove D, and based on the size of the partition support 21, the sealing member 23 is formed into a long strip structure.

[0068] The inner wall of the mounting groove D and the sealing member 23 can be bonded by a glue having a certain temperature resistance, such as silicone rubber. In addition, the sealing member 23 can be made of materials with different temperature resistances according to the different thermal environments of the air intake structure 100.

[0069] Fig.10 A schematic structural diagram of a guard plate of the present invention is shown. Fig.11 The schematic diagram of another protective plate of the present invention is shown. Fig.10 and Fig.11 The overall structure of the guard plates is the same, but the sizes are different.

[0070] Reference Fig.10 and Fig.11 A plurality of third mounting holes C3 are provided on the circumferential edge of each guard plate 22. Figure 8 and Fig. 9 , a plurality of fourth mounting holes C4 are correspondingly provided on the frame portion 212. Among them, the third mounting hole C3 is a through hole, and the fourth mounting hole C4 is a threaded hole. The third mounting hole C3 is threadedly connected with the fourth mounting hole C4 through a fastener (such as a bolt) to achieve a detachable connection between the guard plate 22 and the partition support 21.

[0071] Therefore, in the present invention, by decomposing the integrated structure into a detachable multi-part splicing structure (such as screw connection), the processing difficulty is reduced, the disassembly and assembly are convenient, and the structural dimensions and surface quality of all parts can be detected and measured, which is convenient for confirming the product status. In addition, based on the detachable structure of the air intake structure 100 of the present invention, by changing the shape of the internal partition support 21 or changing the shape of the shell 10, different index requirements can be met, instead of requiring all reprocessing like the integrated structure, thereby saving costs; at the same time, the air intake structure 100 of the present invention is suitable for formal product aerodynamic related tests, joint test tests with engines (such as flight tests) and ground technical status iteration assessment tests. For example, in the scheme stage, in the early wind tunnel test, it is convenient to use it as an assessment indicator and technical status iteration: if the test effect does not reach the design state, the product can be quickly formed by simply adjusting the shape of the partition support 21 or the inner and outer shapes of the shell 10, thereby saving costs and shortening the test cycle.

[0072] The embodiments of the present disclosure have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The selection of terms used herein is intended to best explain the principles of the embodiments, practical applications, or technical improvements in the market, or to enable other persons of ordinary skill in the art to understand the embodiments disclosed herein.

Claims

1. An air intake structure for a supersonic aircraft, characterized in that: include: A housing (10) comprising a bottom wall (11) and a side wall (12) connected to an edge of the bottom wall (11), wherein the bottom wall (11) extends along a first direction (X); and at least one channel partition assembly (20), at least a portion of each channel partition assembly (20) being located within the shell (10) and spaced apart from the bottom wall (11) of the shell (10) along a second direction (Y) to enclose an air intake channel (A), and each channel partition assembly (20) being detachably connected to the side wall (12); One end of the bottom wall (11) in the first direction (X) forms an air inlet (A1) connected to the air inlet channel (A) with the side wall (12), and the partition assembly (20) and the corresponding outer edge of the side wall (12) away from the bottom wall (11) form an air outlet (A2) connected to the air inlet channel (A).

2. The air intake structure of a supersonic aircraft according to claim 1, characterized in that: The side wall (12) comprises two first side wall portions (121) and a second side wall portion (122), the two first side wall portions (121) being arranged opposite to each other along a third direction (Z), and one end of the two first side wall portions (121) in the first direction (X) and the bottom wall (11) enclose the air inlet (A1), and the second side wall portion (122) is arranged at the other end of the two first side wall portions (121) in the first direction (X); Wherein, in the second direction (Y), a notch (B) is provided at one end of each first side wall portion (121) away from the bottom wall (11), and the partition assembly (20) is arranged between two opposite notches (B) and is detachably connected to the edge of the first side wall portion (121) surrounding the notch (B).

3. The air intake structure of a supersonic aircraft according to claim 2, characterized in that: Each of the partition components (20) comprises: a channel partition support (21) disposed between two opposite notches (B) and detachably connected to the edge of the first side wall portion (121) surrounding the notch (B); the channel partition support (21) is spaced apart from the bottom wall (11) in the second direction (Y) to surround the air inlet channel (A); and at least a portion of the channel partition support (21) corresponding to the notch (B) is a frame structure; and Two guard plates (22) are arranged on both sides of the lane partition support (21) along the third direction (Z) and are located in the corresponding notch (B), and each guard plate (22) is detachably connected to the lane partition support (21).

4. The air intake structure of a supersonic aircraft according to claim 3, characterized in that: The aisle separation support (21) comprises: a partition portion (211) located in the shell (10) and spaced apart from the bottom wall (11) to enclose the air inlet passage (A), and the partition portion (211) is detachably connected to an edge of the first side wall portion (121) that encloses the notch (B); and The frame portion (212) is connected to the partition portion (211) and forms a plurality of cavities with the partition portion (211), and the frame portion (212) is detachably connected to each of the guard plates (22).

5. The air intake structure of a supersonic aircraft according to claim 4, characterized in that: A plurality of first mounting holes (C1) are arranged at intervals along the extension direction of the edge of the first side wall portion (121) surrounding the notch (B), and a plurality of second mounting holes (C2) are correspondingly arranged on the partition portion (211), and the second mounting holes (C2) are bolted to the first mounting holes (C1) via fasteners; and / or A plurality of third mounting holes (C3) are arranged on the circumferential edge of each guard plate (22), and a plurality of fourth mounting holes (C4) are correspondingly arranged on the frame portion (212), wherein the fourth mounting holes (C4) are bolted to the third mounting holes (C3) via fasteners.

6. The air intake structure of a supersonic aircraft according to claim 4, characterized in that: Each of the channel partition components (20) further comprises a seal (23), wherein the seal (23) is arranged between each of the first side wall portions (121) and the partition portion (211), and the partition portion (211) is sealedly connected to each of the first side wall portions (121) via the corresponding seal (23).

7. The air intake structure of a supersonic aircraft according to claim 6, characterized in that: A mounting groove (D) is provided on the surface of the partition portion (211) facing each of the first side wall portions (121), the mounting groove (D) being located between a connection position between the partition portion (211) and the first side wall portion (121) and an edge of the partition portion (211), and an inner wall of the mounting groove (D) being connected to the sealing member (23); Part of the sealing member (23) extends out of the mounting groove (D) to seal the channel partition support (21) and the first side wall portion (121).

8. The air intake structure of a supersonic aircraft according to any one of claims 2 to 7, characterized in that: The housing (10) further comprises a stop wall (13), the stop wall (13) being located at one end of the first side wall portion (121) away from the second side wall portion (122), and the stop wall (13) connecting the two first side wall portions (121) and enclosing the air inlet (A1) together with the two first side wall portions (121); The number of the lane partition assemblies (20) is plural, and the plural lane partition assemblies (20) include a first lane partition assembly (20A) and a second lane partition assembly (20B), and the first lane partition assembly (20A) and the second lane partition assembly (20B) are arranged at intervals in the first direction (X); One end of the first channel partition component (20A) abuts against the stop wall (13), and the other end forms an air outlet (A2) with the corresponding outer edges of the two first side wall portions (121); the second channel partition component (20B) is spaced apart from the second side wall portion (122) and forms an air outlet (A2) with the second side wall portion (122) and the corresponding outer edges of the two first side wall portions (121).

9. The air intake structure of a supersonic aircraft according to claim 8, characterized in that: The stop wall (13) comprises a stop portion (131) and limiting portions (132) arranged on both sides of the stop portion (131) in the third direction (Z), and the limiting portions (132) protrude from the stop portion (131) along the first direction (X); One end of the first channel partition component (20A) is located between the two limiting portions (132) and abuts against the stop portion (131), and the first channel partition component (20A) is detachably connected to the two limiting portions (132).

10. A supersonic aircraft, characterized in that: It comprises an aircraft engine (200) and the air intake structure (100) according to any one of claims 1 to 9.

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