A fusion structure of a special-shaped aircraft cabin and an engine structure

Abstract

The present application relates to a fusion structure of a special-shaped aircraft cabin and an engine structure, belonging to the technical field of aircraft structures. The fusion structure of the special-shaped aircraft cabin and the engine structure includes a cabin general assembly. The cabin general assembly includes a first cabin, a second cabin, and a third cabin connected in sequence. The second cabin includes a first shell, a second shell, a third shell, and a fourth shell that overlap each other. An engine is disposed in the second cabin. The first cabin is connected to the front skirt of the engine, and the third cabin is connected to the rear skirt of the engine. In the present application, the front skirt of the engine can be connected to the first cabin, the rear skirt of the engine can be connected to the third cabin, the front skirt of the engine can be connected to the axial L-shaped end frame of the first cabin, and the rear skirt of the engine can be connected to the axial L-shaped end frame of the third cabin. The shell of the engine is the main load-bearing structure of the aircraft. By using the shell of the engine to bear the main loads such as the bending moment and axial force of the aircraft, the structural fusion of the engine and the cabin general assembly is achieved.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft structures, and particularly relates to a fusion structure of a special-shaped aircraft cabin and an engine structure. Background Art

[0002] When an aircraft flies at high speed, it is subjected to severe aerodynamic forces and aerodynamic heat loads. Heat protection and load bearing are important considerations in the design of the aircraft cabin structure. With the development of space technology, the requirement for lightweight cabin structures is getting higher and higher. When designing the cabin structure, the ways to achieve lightweight structures mainly include selecting lightweight materials, efficient structural forms, and integrated and fusion design approaches.

[0003] The engine is the power source of the aircraft, providing the power required for flight. Generally, a multi-stage rocket aircraft includes multi-stage engines. The engine needs to meet requirements such as load bearing during operation and be reliably connected to the cabin to transmit thrust. During the operation of a solid rocket engine, due to reasons such as high pressure and temperature rise, the engine will have obvious deformations. The reliable connection between the engine and the aircraft cabin and the external heat protection design of the engine are the key points and difficulties in aircraft structure design. Generally speaking, because a solid rocket engine bears high pressure, the engine shell has good mechanical properties. Making full use of the engine shell to bear loads such as bending moments and axial forces of the aircraft is an effective way for lightweight aircraft structure design. However, the engine is generally cylindrical in shape, and it is difficult to integrate and design the special-shaped aircraft cabin section and the engine. Factors such as deformation matching between the engine and the cabin, assembly processability, and reliability of heat protection and load bearing need to be fully considered.

[0004] In summary, the integrated design of the aircraft cabin and the engine is of great significance. How to solve the integrated structural design of the special-shaped aircraft cabin and the engine and meet the deformation matching, assembly, heat protection, and load bearing between the engine and the cabin are the key points and difficulties in the design. Summary of the Invention

[0005] The embodiments of the present application provide a fusion structure of a special-shaped aircraft cabin and an engine structure to solve the problem in the related art that it is inconvenient to integrally fuse the structures of the aircraft cabin and the engine.

[0006] The embodiments of the present application provide a fusion structure of a special-shaped aircraft cabin and an engine structure, including a cabin general assembly, and the cabin general assembly includes a first cabin, a second cabin, and a third cabin connected in sequence;

[0007] The second cabin includes a first shell, a second shell, a third shell, and a fourth shell that overlap each other;

[0008] An engine, and the engine is disposed in the second cabin;

[0009] The first cabin is connected to the front skirt of the engine, and the third cabin is connected to the rear skirt of the engine.

[0010] In some embodiments, the front skirt of the engine and the first cabin are connected by bolts.

[0011] In some embodiments, the rear skirt of the engine and the third cabin are connected by bolts.

[0012] In some embodiments, the first housing and the third housing are symmetrically arranged;

[0013] The second housing and the fourth housing are symmetrically arranged;

[0014] The first housing, the second housing, the third housing, and the fourth housing are all arc-shaped structures that cooperate with the engine.

[0015] In some embodiments, the two ends of the first housing are respectively connected to one end of the second housing and one end of the fourth housing by radial screws;

[0016] The two ends of the second housing are respectively connected to the other end of the second housing and the other end of the fourth housing by radial screws.

[0017] In some embodiments, control equipment is also provided in the second cabin.

[0018] In some embodiments, a first installation groove is provided at one end of the outer side of the second cabin close to the first cabin;

[0019] The first cabin and the second cabin are connected by a first screw passing through the first installation groove and the second cabin;

[0020] A heat shield covering the first screw is provided in the first installation groove.

[0021] In some embodiments, a second installation groove is provided at one end of the outer side of the second cabin close to the third cabin;

[0022] The second cabin and the third cabin are connected by a second screw passing through the second installation groove;

[0023] A waist-shaped hole is provided at the bottom of the second installation groove, and the second screw passes through the waist-shaped hole and is connected to the third cabin;

[0024] A heat shield covering the second screw is provided in the second installation groove.

[0025] In some embodiments, a lubricating layer is provided between the connection sections of the second cabin and the third cabin.

[0026] In some embodiments, the lubricating layer is made of copper alloy material.

[0027] An embodiment of the present application provides a fusion structure of an alien aircraft cabin and an engine structure, wherein the cabin assembly includes a first cabin, a second cabin, and a third cabin connected in sequence, wherein the second cabin and the first cabin are axially fixedly connected, and the second cabin and the third cabin are axially floatingly connected. When the engine is working and extending, the second cabin and the third cabin move axially relative to each other, thereby meeting the deformation matching requirements of the engine and cabin assembly.

[0028] The second cabin maintains the shape of the aircraft, realizes the heat insulation of the engine, and bears the aerodynamic distribution load during flight. Through the overlap between the first shell, the second shell, the third shell and the fourth shell, the second cabin can be installed in blocks, which improves the assembly processability. After the engine is connected to the first cabin and the third cabin, the divided second cabin is easier to install and splice, and it is also convenient to disassemble the engine, thereby improving the installation efficiency and disassembly efficiency.

[0029] The front skirt of the engine is connected to the first cabin, the rear skirt of the engine is connected to the third cabin, the front skirt of the engine is connected to the axial L-shaped end frame of the first cabin, and the rear skirt of the engine is connected to the axial L-shaped end frame of the third cabin. The engine casing is the main load-bearing structure of the aircraft. The engine casing is used to bear the main loads of the aircraft such as bending moment and axial force, thereby realizing the structural integration of the engine and cabin assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0031] Figure 1 A schematic diagram of the structure provided in an embodiment of the present application;

[0032] Figure 2 This is a schematic diagram of the front skirt connection provided by the engine in the embodiment of this application;

[0033] Figure 3 This is a schematic diagram of the rear skirt connection provided by the engine in the embodiment of this application;

[0034] Figure 4 A schematic diagram of the connection between the second cabin and the first cabin in an embodiment of the present application;

[0035] Figure 5 A schematic diagram of the connection between the second cabin and the third cabin in an embodiment of the present application;

[0036] Figure 6 This is a structural diagram of the second cabin provided in an embodiment of the present application;

[0037] Figure 7 This is the enlarged schematic diagram of the structure provided in the present application. Figure 6 in the present application.

[0038] 1. Engine; 1a. Front skirt; 1b. Rear skirt; 2. Second cabin; 2a. First housing; 2b. Second housing; 2c. Third housing; 2d. Fourth housing; 3. First cabin; 4. Third cabin; 7. First screw; 8. Lubricating layer; 9. Second screw; 10. Heat shield; 11. Waist-shaped hole; 12. Heat-proof access cover. Specific embodiments

[0039] To make the objectives, technical solutions, and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Apparently, the described embodiments are some but not all of the embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts shall fall within the scope of protection of the present application.

[0040] The embodiments of the present application provide a structure integration structure of a special-shaped aircraft cabin and an engine, which can solve the problem of inconvenient structural integration of the aircraft cabin and the engine.

[0041] See Figures 1 - 3 and Figure 6 As shown in, the embodiments of the present application provide a structure integration structure of a special-shaped aircraft cabin and an engine, including

[0042] the overall assembly of the cabin and the engine 1.

[0043] Wherein, the overall assembly of the cabin includes the first cabin 3, the second cabin 2, and the third cabin 4 connected in sequence. The second cabin 2 is axially fixedly connected to the first cabin 3, and the second cabin 2 is axially floatingly connected to the third cabin 4. When the engine 1 works and elongates, the second cabin 2 and the third cabin 4 axially move relative to each other to meet the deformation matching requirements of the engine 1 and the overall assembly of the cabin.

[0044] The second cabin 2 includes the first housing 2a, the second housing 2b, the third housing 2c, and the fourth housing 2d that overlap each other.

[0045] The second cabin 2 is a shell arranged on the outside of the engine 1. The second cabin 2 maintains the shape of the aircraft, realizes the heat insulation of the engine 1, and bears the aerodynamic distribution load during flight. Through the overlap between the first shell 2a, the second shell 2b, the third shell 2c and the fourth shell 2d, the second cabin 2 can be installed in blocks to improve the assembly processability. After the engine 1 is connected to the first cabin 3 and the third cabin 4, the divided second cabin 2 is easier to install and splice, and it is also convenient to disassemble the engine 1, thereby improving the installation efficiency and disassembly efficiency.

[0046] Among them, the front skirt 1a of the engine 1 is connected to the first cabin body 3, the rear skirt 1b of the engine 1 is connected to the third cabin body 4, the front skirt 1a of the engine 1 is connected to the axial L-shaped end frame of the first cabin body 3, and the rear skirt 1b of the engine 1 is connected to the axial L-shaped end frame of the third cabin body 4. The casing of the engine 1 is the main load-bearing structure of the aircraft. The casing of the engine 1 is used to bear the main loads of the aircraft such as bending moment and axial force, thereby realizing the structural integration of the engine 1 and the cabin assembly.

[0047] In this embodiment, the front skirt 1a of the engine 1 is connected to the first cabin body 3 by bolts, so that the engine 1 and the first cabin body 3 are axially connected by an L-shaped end frame, thereby completing a fixed connection between the engine 1 and the first cabin body 3. A mounting plate extends from one end of the first cabin body 3 toward the second cabin body 2, and the front skirt 1a is arranged below the mounting plate and connected to the first cabin body 3.

[0048] In this embodiment, the rear skirt 1b of the engine 1 is connected to the third cabin body 4 by bolts, so that the rear skirt 1b of the engine 1 is connected to the third cabin body 4 axially in an L-shaped end frame, thereby completing a fixed connection between the engine 1 and the third cabin body 4. A mounting plate extends from one end of the third cabin body 4 toward the second cabin body 2, and the rear skirt 1b is arranged below the mounting plate and connected to the third cabin body 4.

[0049] In some optional implementations, see Figures 6 - 7 As shown, the first shell 2a and the third shell 2c are symmetrically arranged in the upper and lower parts, and the second shell 2b and the fourth shell 2d are symmetrically arranged in the left and right parts. The first shell 2a, the second shell 2b, the third shell 2c and the fourth shell 2d are all arc-shaped structures that cooperate with the engine 1. The first shell 2a, the second shell 2b, the third shell 2c and the fourth shell 2d form a diamond-shaped structure. When the engine 1 is located inside the second cabin 2, the upper and lower surfaces of the engine 1 are in contact with the inner sides of the first shell 2a and the third shell 2c, making the structure compact, improving space utilization, reducing the weight of the cabin assembly, and improving the efficiency of the engine 1.

[0050] In this embodiment, both ends of the first housing 2a are respectively connected to one end of the second housing 2b and one end of the fourth housing 2d by radial screws. Both ends of the second housing 2b are respectively connected to the other end of the second housing 2b and the other end of the fourth housing 2d by radial screws. The first housing 2a, the second housing 2b, the third housing 2c, and the fourth housing 2d are fixedly connected to each other through the radial screws, enabling them to be assembled and fixed. Moreover, heat-resistant caps 10 are also provided on the radial screws to endow them with heat-resistant capabilities and extend their service life. After the engine 1 is installed with the first cabin 3 and the third cabin 4, first, the second housing 2b and the fourth housing 2d are docked with the first cabin 3 and the third cabin 4, and then the first housing 2a and the third housing 2c are lapped with the second housing 2b and the fourth housing 2d.

[0051] In some alternative embodiments, referring to Figure 6 as shown, control devices are further provided in the second cabin 2. The control devices are arranged on both sides of the engine 1 and are located in the gaps between the second housing 2b and the fourth housing 2d and the engine 1, making full use of the space in the second cabin 2, improving the space utilization rate, and making the integration between the engine 1 and the overall cabin assembly more effective.

[0052] In some alternative embodiments, referring to Figure 1 and Figures 4 - 5 as shown, a first mounting groove is formed at one end of the outer side of the second cabin 2 close to the first cabin 3;

[0053] The first cabin 3 is connected to the second housing 2b and the fourth housing 2d of the second cabin 2 by first screws 7. The first screws 7 pass through the first mounting groove to connect with the second cabin 2. Heat-resistant caps 10 covering the first screws 7 are arranged in the first mounting groove, and heat resistance of the screws is achieved through the heat-resistant caps 10. The second cabin 2 is arranged above the mounting plate and connected thereto.

[0054] In this embodiment, a second mounting groove is formed at one end of the outer side of the second cabin 2 close to the third cabin 4. The second cabin 2 and the third cabin 4 are connected by second screws 9 passing through the second mounting groove. A waist-shaped hole 11 is formed at the bottom of the second mounting groove. The second screws 9 pass through the waist-shaped holes 11 to connect with the third cabin 4. Heat-resistant covers 12 covering the second screws 9 are arranged in the second mounting groove, enabling the second screws 9 to have heat-resistant capabilities through the heat-resistant covers 12. There is a gap between the interior of the heat-resistant covers 12 and the second screws 9, and this gap meets the requirements of the heat deformation of the engine 1. Through the waist-shaped holes 11, the second screws 9 can axially move along their lengths within the waist-shaped holes 11 to meet the matching requirements of the elongation deformation during the operation of the engine 1, avoiding the situation where the engine 1 cannot extend during heat deformation, which may easily cause damage and reduced service life, and also reducing the integration degree with the overall cabin assembly.

[0055] In this embodiment, a lubricating layer 8 is provided between the connecting sections of the second cabin 2 and the third cabin 4. The lubricating layer 8 is disposed between the contact surfaces where the second cabin 2 and the third cabin 4 overlap and are connected to each other, and is used to reduce the frictional force of axial movement between the second cabin 2 and the third cabin 4, which is beneficial for deformation matching.

[0056] In this embodiment, the lubricating layer 8 is made of a copper alloy material, which has high lubrication efficiency and long lubrication life.

[0057] The working principle and process of this application are as follows:

[0058] When assembling the cabin assembly and the engine 1, first connect the front skirt 1a of the engine 1 to the first cabin 3, and then connect the rear skirt 1b of the engine 1 to the third cabin 4, so that the engine 1 and the cabin assembly are integrated. The housing of the engine 1 bears loads such as bending moment and axial force of the aircraft, realizing the integrated structural design of the cabin assembly and the engine 1, achieving the purpose of structural weight reduction. Then, connect the second housing 2b and the fourth housing 2d to the first cabin 3 and the third cabin 4, and then overlap the first housing 2a and the third housing 2c with the second housing 2b and the fourth housing 2d, and the assembly can be completed, realizing the integrated installation between the engine 1 and the cabin assembly.

[0059] When the engine 1 undergoes thermal deformation, the second screw 9 can axially move along its length direction within the waist-shaped hole 11 through the waist-shaped hole 11, so as to meet the matching requirements of the elongation deformation during the operation of the engine 1, avoiding the situation that the engine 1 cannot extend during heat deformation, resulting in easy damage and reduced life, and also reducing the integration degree with the cabin assembly.

[0060] In the description of this application, it should be noted that the orientation or positional relationship indicated by terms such as "upper" and "lower" is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing this application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to this application. Unless otherwise clearly specified and defined, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific situations.

[0061] It should be noted that in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements but also includes other elements not expressly listed, or also includes elements inherent in such process, method, article or device. Without further limitation, an element defined by the statement "comprising an..." does not exclude the presence of additional identical elements in the process, method, article or device comprising the said element.

[0062] The above are only specific embodiments of the present application, enabling those skilled in the art to understand or implement the present application. Various modifications to these embodiments will be obvious to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to these embodiments shown herein, but rather will be accorded the widest scope consistent with the principles and novel features claimed herein.

Claims

1. A fusion structure of a special-shaped aircraft cabin and an engine structure, characterized in that Comprising: The overall assembly of the cabin, which includes a first cabin (3), a second cabin (2), and a third cabin (4) connected in sequence; The second cabin (2) includes a first housing (2a), a second housing (2b), a third housing (2c), and a fourth housing (2d) that overlap each other; An engine (1), which is arranged inside the second cabin (2); The first cabin (3) is connected to the front skirt (1a) of the engine (1), and the third cabin (4) is connected to the rear skirt (1b) of the engine (1); The first housing (2a) and the third housing (2c) are symmetrically arranged; The second housing (2b) and the fourth housing (2d) are symmetrically arranged; The first housing (2a), the second housing (2b), the third housing (2c), and the fourth housing (2d) are all arc-shaped structures that cooperate with the engine (1); A first installation groove is opened at one end of the outer side of the second cabin (2) close to the first cabin (3); The first cabin (3) and the second cabin (2) are connected by a first screw (7) passing through the first installation groove and connecting to the second cabin (2); A heat shield (10) covering the first screw (7) is arranged in the first installation groove; A second installation groove is opened at one end of the outer side of the second cabin (2) close to the third cabin (4); The second cabin (2) and the third cabin (4) are connected by a second screw (9) passing through the second installation groove; A waist-shaped hole (11) is opened at the bottom of the second installation groove, and the second screw (9) passes through the waist-shaped hole (11) and connects to the third cabin (4); A heat shield cover (12) covering the second screw (9) is arranged in the second installation groove.

2. The integrated structure of the special-shaped aircraft cabin and the engine as claimed in claim 1, characterized in that: The front skirt (1a) of the engine (1) and the first cabin (3) are connected by bolts.

3. The integrated structure of the special-shaped aircraft cabin and the engine as claimed in claim 2, characterized in that: The rear skirt (1b) of the engine (1) and the third cabin (4) are connected by bolts.

4. The integrated structure of the special-shaped aircraft cabin and the engine as claimed in claim 1, characterized in that: Both ends of the first housing (2a) are respectively connected to one end of the second housing (2b) and one end of the fourth housing (2d) by radial screws; Both ends of the second housing (2b) are respectively connected to the other end of the second housing (2b) and the other end of the fourth housing (2d) by radial screws.

5. The integrated structure of the special-shaped aircraft cabin and the engine as claimed in claim 1, characterized in that: Control equipment is also arranged inside the second cabin (2).

6. The integrated structure of the special-shaped aircraft cabin and the engine as claimed in claim 1, characterized in that: A lubricating layer (8) is arranged between the connection section of the second cabin (2) and the third cabin (4).

7. The integrated structure of the special-shaped aircraft cabin and the engine as claimed in claim 6, characterized in that: The lubricating layer (8) is made of copper alloy material.

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