A supersonic aircraft and its air intake structure

Abstract

The present invention provides a supersonic aircraft and its air intake structure. The air intake structure includes: a housing, which includes a bottom wall and side walls connected to the bottom wall; and at least one partition component. At least a part of each partition component is located inside the housing and is spaced from the bottom wall of the housing to enclose an air intake passage. Each partition component is detachably connected to the side wall. One end of the bottom wall and the side wall enclose an air inlet, and the corresponding outer edge of the partition component and the side wall enclose an air outlet. Since each partition component and the housing are both independent modular structures and can be assembled in a detachable manner, it has low cost, good maintainability, does not require special processing technology, has small structural deformation, and the dimensions of each modular structure can be inspected and measured. When the housing or any partition component is damaged, only the damaged part needs to be replaced, and there is no need to scrap the entire air intake structure.

Description

Technical Field

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

[0002] The intake structure of a supersonic aircraft is a very important aerodynamic component, which is used to supply air to the aircraft engine. The inside of the channel of the intake structure must be sealed, and there is a certain pneumatic pressure inside during the working process. At present, most of the intake structures of supersonic aircraft are made of metal or non-metal and formed into an integral structure by casting process, or several metal plates are spliced and welded into an integral structure.

[0003] For the intake structure processed by integral molding, although it has good integrity and high strength, it has poor precision, high cost, and is prone to cracks during use; moreover, since its inside is a closed area, it is not easy to confirm the surface quality of the internal structure, and it is not easy to determine the dimensional tolerance and it cannot be detected; at the same time, since it is not disassemblable, it can only correspond to one technical state of the intake duct, and when a problem occurs locally, it is easy to cause the entire intake structure to be scrapped.

[0004] For the intake structure processed by splicing and welding, although its flow channel has high precision, due to its complex structure, the manufacturing cost is high; moreover, since welding is a special process, defects are easy to occur in the welds during the processing, and problems such as welding deformation and poor sealing are likely to occur; at the same time, since it is not disassemblable, it can only correspond to one technical state of the intake duct, and when a problem occurs locally, it is easy to cause the entire intake structure to be scrapped. Summary of the Invention

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

[0006] In a first aspect, the present invention proposes an intake structure of a supersonic aircraft, which includes: a housing, including a bottom wall and a side wall connected to the edge of the bottom wall, the bottom wall extending in a first direction; and at least one partition assembly, at least a part of each partition assembly is located inside the housing and is spaced apart from the bottom wall of the housing in a second direction to enclose an intake channel, and each partition assembly is detachably connected to the side wall. Wherein, one end of the bottom wall in the first direction and the side wall enclose an air inlet communicating with the intake channel, and the partition assembly and the corresponding outer edge of the side wall away from the bottom wall enclose an air outlet communicating with the 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 oppositely arranged in the third direction, and one end of the two first side wall portions in the first direction and the bottom wall enclose the air inlet. The second side wall portion is arranged at the other end of the two first side wall portions in the first direction. Wherein, in the second direction, a notch is provided at one end of each first side wall portion away from the bottom wall, and the partition channel assembly is arranged between two opposite notches and is detachably connected to the edge of the first side wall portion enclosing the notch.

[0008] Further, each partition channel assembly includes: a partition channel support seat, which is arranged between two opposite notches and is detachably connected to the edge of the first side wall portion enclosing the notch. The partition channel support seat is spaced from the bottom wall in the second direction to enclose the air inlet channel, and at least a part of the partition channel support seat corresponding to the notch is a frame structure; and two guard plates, which are arranged on both sides of the partition channel support seat along the third direction and are located in the corresponding notches, and each guard plate is detachably connected to the partition channel support seat.

[0009] Further, the partition channel support seat includes: a partition plate portion, which is located inside the housing and is spaced from the bottom wall to enclose the air inlet channel, and the partition plate portion is detachably connected to the edge of the first side wall portion enclosing the notch; and a frame portion, which is connected to the partition plate portion and encloses a plurality of cavities with the partition plate portion, and the frame portion is detachably connected to each guard plate.

[0010] Further, a plurality of first mounting holes are arranged at intervals along the extending direction of the edge on the edge of the first side wall portion enclosing the notch, and a plurality of second mounting holes are correspondingly arranged on the partition plate portion. The second mounting holes are bolted to the first mounting holes through fasteners.

[0011] Further, 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. The fourth mounting holes are bolted to the third mounting holes through fasteners.

[0012] Further, each partition channel assembly further includes a seal, and the seal is arranged between each first side wall portion and the partition plate portion. The partition plate portion is hermetically connected to each first side wall portion 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:

[0018] 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.

[0019] The intake structure of the present application is particularly applicable during the iterative process of the prior art state. In relevant tests for evaluating the intake structure and the performance of the aircraft engine, the relevant intake parameters can be changed by altering the cross-sectional shape of the intake passage, thereby evaluating different performance indicators. Compared with the intake structure processed by integral molding and the intake structure processed by welding, it can be achieved only by replacing the internal partition component or the housing.

[0020] The Summary of the Invention section is provided to introduce, in a simplified form, a selection of concepts that will be further described in the detailed description below. The Summary of the Invention section is not intended to identify the key features or essential features of the present disclosure, nor is it intended to limit the scope of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] By describing the exemplary embodiments of the present disclosure in more detail in conjunction with the accompanying drawings, the above and other objects, features, and advantages of the present disclosure will become more apparent. Among them, in the exemplary embodiments of the present disclosure, the same reference numerals generally represent the same components.

[0022] Figure 1 The structural schematic diagram of the supersonic aircraft of the present invention is shown;

[0023] Figure 2 The three-dimensional structural schematic diagram of the intake structure of the present invention is shown;

[0024] Figure 3 The internal structural schematic diagram of the intake structure of the present invention is shown;

[0025] Figure 4 The three-dimensional structural schematic diagram of the housing of the present invention is shown;

[0026] Figure 5 For Figure 4 the front view;

[0027] Figure 6 The three-dimensional structural schematic diagram of a partition component of the present invention is shown;

[0028] Figure 7 The three-dimensional structural schematic diagram of another partition component of the present invention is shown;

[0029] Figure 8 The three-dimensional structural schematic diagram of a partition support of the present invention is shown;

[0030] Figure 9 The three-dimensional structural schematic diagram of another partition support of the present invention is shown;

[0031] Figure 10 The structural schematic diagram of a guard plate of the present invention is shown;

[0032] Figure 11 Shows a schematic structural diagram of another protective plate of the present invention.

[0033] Among them, the reference numerals are as follows:

[0034] 100, intake structure;

[0035] 10, housing; 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;

[0036] 20, partition channel assembly; 20A, first partition channel assembly; 20B, second partition channel assembly;

[0037] 21, partition channel support; 211, partition portion; 212, frame portion; 22, protective plate; 23, seal;

[0038] A, intake channel; A1, intake port; A2, outlet port; B, notch; C1, first mounting hole; C2, second mounting hole; C3, third mounting hole; C4, fourth mounting hole; D, mounting groove;

[0039] 200, aircraft engine;

[0040] X, first direction; Y, second direction; Z, third direction. Detailed implementation manners

[0041] Hereinafter, embodiments of the present disclosure will be described in more detail with reference to the accompanying drawings. Although the embodiments of the present disclosure are shown in the 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 so that the present disclosure will be more thorough and complete, and can fully convey the scope of the present disclosure to those skilled in the art.

[0042] As used herein, the term "including" and its variants mean open inclusion, that is, "including but not limited to". Unless otherwise stated, the term "or" means "and / or". The term "based on" means "at least partially based 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. There may also be other explicit and implicit definitions hereinafter.

[0043] Hereinafter, a supersonic aircraft and its intake structure according to embodiments of the present application will be described with reference to the accompanying drawings.

[0044] Figure 1 Shows a schematic structural diagram of the supersonic aircraft of the present invention.

[0045] 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. Among them, the air intake structure 100 is used to supply air to the aircraft engine 200.

[0046] Figure 2 The three-dimensional structure diagram of the air intake structure of the present invention is shown. Figure 3 The internal structure diagram of the air intake structure of the present invention is shown.

[0047] Reference Figure 2 and Figure 3 , the air intake structure 100 of the supersonic aircraft of the embodiment of the present application includes a housing 10 and at least one partition assembly 20.

[0048] The housing 10 includes a bottom wall 11 and side walls 12 connected to the edge of the bottom wall 11, and the side walls 12 and the bottom wall 11 together enclose a cavity. Among them, the bottom wall 11 extends along the first direction X.

[0049] 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 plate structure, a curved structure, or a combined structure of a flat plate structure and a curved structure. However, no matter what structure the bottom wall 11 is, the bottom wall 11 always has a certain length along the first direction X.

[0050] The number of partition assemblies 20 can be one or more. At least part of each partition assembly 20 is located inside the housing 10 and is spaced from the bottom wall 11 of the housing 10 along the second direction Y to enclose an air intake passage A, and each partition assembly 20 is detachably connected to the side wall 12 of the housing 10.

[0051] Among them, one end of the bottom wall 11 of the housing 10 in the first direction X and the side wall 12 enclose an air intake port A1 communicating with the air intake passage 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 enclose an air outlet A2 communicating with the air intake passage A.

[0052] Specifically, when the number of partition assemblies 20 is one, the bottom of the partition assembly 20 and the bottom wall 11 of the housing 10 together enclose the air intake passage A; when the number of partition assemblies 20 is multiple, the multiple partition assemblies 20 are arranged side by side along the first direction X, and the bottoms of the multiple partition assemblies 20 and the bottom wall 11 of the housing 10 together enclose the air intake passage A.

[0053] In this embodiment, the intake structure 100 includes a housing 10 and at least one partition component 20. All the partition components 20 are assembled with the housing 10 and together enclose an intake passage A having an air inlet A1 and an air outlet A2, so as to supply air to the aircraft engine 200 by using the intake passage A. Since each partition component 20 and the housing 10 are both independent modular structures and can be assembled in a detachable manner, the modules can be disassembled and assembled as needed, with low cost, good maintainability, no need for special processing (mature process), small structural deformation, and the sizes of each modular structure can be inspected and measured. Moreover, when the housing 10 or any partition component 20 is damaged, only the damaged part needs to be replaced, and there is no need to scrap the entire intake structure 100. Furthermore, based on the independence between each partition component 20 and the housing 10, different cross-sectional shapes of the intake passage A can be formed by replacing the partition component 20 or the housing 10 with different shapes, thereby meeting different performance index requirements without adjusting the entire intake structure 100.

[0054] Therefore, the intake structure 100 of the present application is particularly suitable for the process of iterative pre-technical states. In the relevant tests for evaluating the performance of the intake structure 100 and the aircraft engine 200, the relevant intake parameters can be changed by changing the cross-sectional shape of the intake passage A, and then different performance indexes can be evaluated. Compared with the integrally formed intake structure and the welded intake structure, it can be achieved only by replacing the internal partition component 20 or the housing 10.

[0055] In some embodiments, the housing 10 can be machined from a metal material, which is convenient for controlling the internal and external surface dimensions and surface roughness of the housing 10. Moreover, the housing 10 and the partition component 20 can be detachably connected by setting screw through holes on the housing 10, and after they are assembled and connected, the inner wall of the housing 10 and the bottom of the partition component 20 together form the intake passage A.

[0056] Figure 4 The three-dimensional structural schematic diagram of the housing of the present invention is shown. Figure 5 is Figure 4 the front view of.

[0057] Referring to 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.

[0058] 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 and the bottom wall 11 enclose an air inlet A1. 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.

[0059] 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. The partition component 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. That is, a small part of the partition component 20 (i.e., only the bottom part) is located inside the housing 10 and is detachably connected to the housing 10, while the other parts are exposed to the housing 10 through the notch B. And, in the second direction Y, an air outlet A2 with the gas outlet direction facing the second direction Y is formed between the partition component 20 and the corresponding outer edge of the first side wall portion 121 away from the bottom wall 11.

[0060] In this embodiment, since one end of the housing 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 in the first direction X, and at the same time, an air outlet A2 with the gas outlet direction facing the second direction Y is formed in the second direction Y, it is convenient to supply air to the aircraft engine 200 through the air outlet A2 in this direction, improving the adaptability between the air intake structure 100 and the aircraft engine 200.

[0061] Refer to Figure 4 , the housing 10 further includes a stop wall 13. The stop wall 13 is located at one end of the first side wall portion 121 facing away from the second side wall portion 122, and the stop wall 13 connects the two first side wall portions 121 and encloses the air inlet A1 together with the two first side wall portions 121.

[0062] Refer to Figure 2 , the number of the partition components 20 is multiple. The multiple partition components 20 include a first partition component 20A and a second partition component 20B. The first partition component 20A and the second partition component 20B are arranged at intervals in the first direction X. Wherein, one end of the first partition component 20A abuts against the stop wall 13, and the other end and the corresponding outer edges of the two first side wall portions 121 enclose an air outlet A2. The second partition component 20B is arranged at intervals with the second side wall portion 122 and encloses an air outlet A2 with the second side wall portion 122 and the corresponding outer edges of the two first side wall portions 121.

[0063] Specifically, when the number of the partition channel components 20 is two, one end of the first partition channel component 20A abuts against the stop wall 13, and the other end, together with the second partition channel component 20B and the corresponding outer edges of the two first side wall portions 121, encloses an air outlet A2. The second partition channel component 20B is spaced apart from the second side wall portion 122 and, together with the second side wall portion 122 and the corresponding outer edges of the two first side wall portions 121, encloses an air outlet A2.

[0064] When the number of the partition channel components 20 is more than two, the first partition channel component 20A and the second partition channel component 20B are the partition channel components 20 located at both ends in the first direction X. Among them, one end of the first partition channel component 20A abuts against the stop wall 13, and the other end, together with the adjacent partition channel component 20 and the corresponding outer edges of the two first side wall portions 121, encloses an air outlet A2. The second partition channel component 20B is spaced apart from the second side wall portion 122 and, together with the second side wall portion 122 and the corresponding outer edges of the two first side wall portions 121, encloses an air outlet A2.

[0065] In this embodiment, by selecting the number of the partition channel components 20, different numbers of air outlets A2 can be formed to adapt to the air supply requirements of different aircraft engines 200, thereby improving the application range of the air intake structure 100 of the present application.

[0066] Continue to refer to Figure 2 and Figure 4 , the stop wall 13 includes 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. Among them, one end of the first partition channel component 20A is located between the two limiting portions 132 and abuts against the stop portion 131, and the first partition channel component 20A is detachably connected to the two limiting portions 132.

[0067] In this embodiment, the partition channel component 20 can be quickly positioned and installed through the positions of the two limiting portions 132. At the same time, connecting the partition channel component 20 to the limiting portions 132 can further improve the connection reliability between the partition channel component 20 and the housing 10.

[0068] Figure 6 Fig. shows a three-dimensional structural schematic diagram of a partition channel component of the present invention. Figure 7 Fig. shows a three-dimensional structural schematic diagram of another partition channel component of the present invention. Among them, Figure 6 and Figure 7 the general structures of the partition channel components in are the same, but there are differences in dimensions.

[0069] Refer to Figure 6 and Figure 7 , each partition channel component 20 includes a partition channel support 21 and two guard plates 22.

[0070] The partition support 21 is arranged between two opposite notches B and is detachably connected to the edge of the first side wall portion 121 that encloses the notch B. Moreover, the portion of the partition support 21 located inside the housing 10 is spaced apart from the bottom wall 11 along the second direction Y to enclose the intake passage A. Two guard plates 22 are arranged on both sides of the 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 partition support 21.

[0071] In this embodiment, the detachable connection between the partition assembly 20 and the first side wall portion 121 of the housing 10 is realized through the partition support 21. Moreover, by arranging the guard plates 22 on both sides of the partition support 21, the function of rectifying the shape can be achieved, and the influence of the external shape structure of the partition support 21 on the air flow can be avoided.

[0072] Specifically, in order to easily control the internal and external shape 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 metal processing or composite material molding. Countersunk screw holes can be arranged on the surface of each guard plate 22 for connecting the partition support 21.

[0073] Continue to refer to Figure 6 and Figure 7 As shown in, the partition support 21 includes a partition portion 211 and a frame portion 212. The partition portion 211 is located inside the housing 10 and is spaced apart from the bottom wall 11 to enclose the intake passage 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.

[0074] It can be understood that the partition portion 211 is the bottom portion of the partition support 21 that extends along the edge of the first side wall portion 121 that encloses the notch B. The whole of it is a solid structure and can be detachably connected to the first side wall portion 121. The frame portion 212 is the portion of the partition support 21 corresponding to the notch B, that is, the other portion except the bottom portion. Among them, the frame portion 212 is a structure with a hollowed-out portion formed by a plurality of rods or beams with different extending directions (which can also be called a hollow structure). The frame portion 212 encloses a plurality of cavities with the partition portion 211.

[0075] In this embodiment, the detachable connection between the partition assembly 20 and the first side wall portion 121 of the housing 10 is realized through the partition portion 211. Moreover, by setting a part of the partition support 21 (that is, the frame portion 212) as a hollow structure, the overall structural mass of the partition assembly 20 can be reduced. And, based on the setting of the guard plate 22, the guard plate 22 can block the notch B and the hollow structure on the partition support 21 corresponding to the notch B, so as to avoid the influence of the hollow structure on the partition support 21 on the air flow.

[0076] 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.

[0077] Continue to refer to Figure 6 and Figure 7 Each 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.

[0078] 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.

[0079] 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.

[0080] Figure 8 A schematic diagram of the three-dimensional structure of a partition support of the present invention is shown. Figure 9 FIG. 2 shows a three-dimensional structural schematic diagram of another type of aisle separation support of the present invention. Figure 8 and Figure 9 The general structure of the aisle supports is the same, but the sizes are different.

[0081] 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 Figure 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.

[0082] 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.

[0083] Reference Figure 8 and Figure 9, on the surface of the partition portion 211 facing each first side wall portion 121, an installation groove D is provided. The installation groove D is located between the connection position of the partition portion 211 and the first side wall portion 121 and the edge of the partition portion 211 (that is, the installation groove D is located between the center connection line of a plurality of second installation holes C2 and the bottom edge of the partition portion 211), and the inner wall of the installation groove D is connected to the seal 23. Among them, a part of the seal 23 extends out of the installation groove D to seal and connect the partition support 21 and the first side wall portion 121.

[0084] Since the installation groove D for installing the seal 23 is located between the connection position of the partition portion 211 and the first side wall portion 121 and the edge of the partition portion 211, the seal 23 is arranged close to the connection position of the partition portion 211 and the first side wall portion 121. In this way, after the housing 10 is connected to the partition assembly 20, the compression amount of the seal 23 can be ensured, thereby improving the sealing performance between the housing 10 and the partition assembly 20. Moreover, since the inner wall of the installation groove D is connected to the seal 23, the seal 23 can be prevented from coming out of the installation groove D during the installation process.

[0085] Specifically, the shape of the seal 23 is adapted to the installation groove D, and based on the size of the partition support 21, the seal 23 is formed into a strip-shaped structure.

[0086] The inner wall of the installation groove D and the seal 23 can be bonded by a glue with a certain temperature resistance, such as silicone rubber. Moreover, the seal 23 can be made of materials with different temperature resistances according to the different thermal environments of the intake structure 100.

[0087] Figure 10 The structural schematic diagram of a kind of guard plate of the present invention is shown. Figure 11 The structural schematic diagram of another kind of guard plate of the present invention is shown. Among them, Figure 10 and Figure 11 The general structures of the guard plates in are the same, but the sizes are different.

[0088] Refer to Figure 10 and Figure 11 , a plurality of third installation holes C3 are provided on the circumferential edge of each guard plate 22. Refer to Figure 8 and Figure 9 , a plurality of fourth installation holes C4 are correspondingly provided on the frame portion 212. Among them, the third installation hole C3 is a through hole, the fourth installation hole C4 is a threaded hole, and the third installation hole C3 is threadedly connected to the fourth installation hole C4 through a fastener (such as a bolt) to realize the detachable connection between the guard plate 22 and the partition support 21.

[0089] Therefore, in the present invention, by decomposing the integral structure into a detachable multi-part splicing structure (such as screw connection), the processing difficulty is reduced, disassembly and assembly are facilitated, and the structural dimensions and surface quality of all parts can be inspected and measured, which is convenient for confirming the product status. Moreover, based on the detachable structure of the intake structure 100 of the present invention, by changing the shape of the internal partition support 21 or changing the shape of the housing 10, different index requirements can be met, rather than having to reprocess the entire integral structure, thus saving costs. At the same time, the intake structure 100 of the present invention is applicable to formal product pneumatic-related tests, joint tests with engines (such as flight tests), and ground technical status iteration assessment tests. For example, in the scheme stage, during the early wind tunnel tests, it is convenient to be used as an assessment index for technical status iteration: if the effect obtained from the tests does not reach the designed state, the shape of the partition support 21 or the internal and external shapes of the housing 10 can be adjusted individually to quickly form a product, thereby saving costs and shortening the test cycle.

[0090] The embodiments of the present disclosure have been described above. The above description is exemplary and not exhaustive, and is not limited to the disclosed embodiments. Many modifications and variations are obvious to those of ordinary skill in the art in the technical field without departing from the scope and spirit of the described embodiments. The choice of terms used herein is intended to best explain the principles of the embodiments, practical applications, or improvements to the technology in the market, or to enable other ordinary skilled persons in the technical field 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) is located in the shell (10) and is spaced from the bottom wall (11) of the shell (10) along the second direction (Y) to enclose an air intake channel (A), and each channel partition assembly (20) is detachably connected to the side wall (12); wherein one end of the bottom wall (11) in the first direction (X) and the side wall (12) form an air inlet (A1) in communication with the air inlet channel (A); 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) in communication with the air inlet channel (A); 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 of the first side wall portions (121) away from the bottom wall (11), and the channel partition assembly (20) is arranged between two opposite notches (B) and is detachably connected to the edge of the first side wall portions (121) surrounding the notch (B); 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).

2. The air intake structure of a supersonic aircraft according to claim 1, characterized in that: The partition support (21) comprises: a partition portion (211) located in the housing (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 the edge of the first side wall portion (121) that encloses the notch (B); and The frame part (212) is connected to the partition part (211) and forms a plurality of cavities with the partition part (211), and the frame part (212) is detachably connected to each of the guard plates (22).

3. The air intake structure of a supersonic aircraft according to claim 2, 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), and the fourth mounting holes (C4) are bolted to the third mounting holes (C3) via fasteners.

4. The air intake structure of a supersonic aircraft according to claim 2, characterized in that: Each of the partition components (20) further includes a seal (23), wherein the seal (23) is disposed between each of the first side wall portions (121) and the partition portion (211), and the partition portion (211) is sealed and connected to each of the first side wall portions (121) via the corresponding seal (23).

5. The air intake structure of a supersonic aircraft according to claim 4, 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 installation groove (D) to seal and connect the partition support (21) and the first side wall portion (121).

6. The air intake structure of a supersonic aircraft according to any one of claims 1 to 5, 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 together with the two first side wall portions (121) enclosing the air inlet (A1); The number of the lane partition components (20) is plural, and the plural lane partition components (20) include a first lane partition component (20A) and a second lane partition component (20B), and the first lane partition component (20A) and the second lane partition component (20B) are arranged at intervals in the first direction (X); Wherein, one end of the first channel partition component (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); 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).

7. The air intake structure of a supersonic aircraft according to claim 6, 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).

8. 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 7.

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