CN113581476A - Engine back support structure and airplane - Google Patents
Engine back support structure and airplane Download PDFInfo
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- CN113581476A CN113581476A CN202110919984.3A CN202110919984A CN113581476A CN 113581476 A CN113581476 A CN 113581476A CN 202110919984 A CN202110919984 A CN 202110919984A CN 113581476 A CN113581476 A CN 113581476A
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- 238000009434 installation Methods 0.000 abstract description 6
- 230000005540 biological transmission Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
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- B64D27/40—
Abstract
The invention relates to an engine back-up structure and an airplane, wherein the engine back-up structure is used on the airplane and is characterized by comprising an engine front mounting section, an engine rear mounting section, an engine mounting beam, a beam front joint and an oblique beam support; the engine front mounting section and the engine rear mounting section are both arranged at the bottom of the engine and are respectively connected with the engine; the front engine mounting joint and the rear engine mounting joint are used for transferring vertical load and side load of the engine; one end of the beam front joint is connected with the engine mounting beam, and the other end of the beam front joint is connected with the airplane wing rear beam; the oblique beam support is connected with the engine mounting beam and the airplane wing back beam. The invention realizes the back-support type installation of the engine without changing the installation section and the thrust rod of the engine, has simple whole structure, adopts the components which are integrally formed, reduces the number of the components and is convenient for the installation of the back-support engine structure.
Description
Technical Field
The invention belongs to the technical field of aero-engines. In particular to an engine back support structure and an airplane.
Background
The wing body of the fusion aircraft can greatly reduce the resistance, increase the space of the passenger and cargo cabin of the aircraft, improve the flight performance of the aircraft and reduce the oil consumption rate of the aircraft. Aircraft engines are typically located under the wing, aft of the fuselage, and less so with the engine located above the leading edge of the wing. In the existing large passenger plane with the conventional structure, an engine is generally positioned below a wing, the engine of the existing small plane with the conventional structure is positioned at the rear part of a fuselage, and the engines of the existing small plane with the conventional structure are arranged on the front side of the upper part of the wing, but the engines of the existing plane arranged at the positions are very inconvenient for a maintainer to check and maintain the existing small plane, high-temperature-resistant materials and surface treatment are required to be carried out on the upper surface of the wing in an engine airflow spraying area, the engines are hung at the lower part of the wing, the height of a landing gear is higher, the overall height of the existing plane is overhigh, and the stability of the whole plane is poorer.
Disclosure of Invention
The invention aims to solve the defects in the prior art, and provides an engine back support structure and an airplane. The invention provides an arrangement mode and a mounting mode of an engine, which are used for solving the problems in the prior art.
The above technical object of the present invention will be achieved by the following technical solutions.
An engine back support structure is used on an airplane and comprises an engine front mounting section, an engine rear mounting section, an engine mounting beam, a beam front joint and an oblique beam support; the engine front mounting section and the engine rear mounting section are both arranged at the bottom of the engine and are respectively connected with the engine;
the front engine mounting joint and the rear engine mounting joint are used for transferring vertical load and side load of the engine;
one end of the beam front joint is connected with the engine mounting beam, and the other end of the beam front joint is connected with the airplane wing rear beam;
the oblique beam support is connected with the engine mounting beam and the airplane wing back beam.
There is further provided in accordance with the above-described aspect and any one of the possible implementations, an implementation in which the engine front mount section and the engine rear mount section are respectively connected to the engine by fasteners.
The above aspects and any possible implementations further provide an implementation in which the engine front mount section and the engine rear mount section are each connected to the engine mount beam by a shear pin and a tension bolt.
The above aspects and any possible implementation manners further provide an implementation manner, wherein the engine mounting beam is an integrally formed web plate type structure, the web plate type structure is formed by splicing symmetrical structures, and each symmetrical structure comprises a web plate, an oblique rib, a vertical rib and an upper and lower mounting surface.
The above-described aspects and any possible implementations further provide an implementation in which the web structure includes an engine front mount section mounting surface, an engine rear mount section mounting surface, a mounting beam front joint mounting surface, and a raker beam support mounting surface.
The above aspects and any possible implementation manners further provide an implementation manner, wherein the beam front joint is formed by splicing two integrally-formed web-type symmetrical structures and comprises three mounting surfaces, and one of the mounting surfaces is connected with the engine mounting beam; the other two mounting planes are connected with the rear wall of the airplane body or the rear beam of the airplane wing.
The above aspects and any possible implementation manners further provide an implementation manner, and the oblique beam supporting structure is formed by splicing two integrally formed web type symmetrical structures.
In accordance with the above aspect and any possible implementation manner, there is further provided an implementation manner, wherein vertical plates are disposed on both the front beam joint and the oblique beam support structure.
The invention also provides an aircraft which comprises an engine back-support structure, an engine, a fuselage and a back-support nacelle, wherein the back-support nacelle is arranged on the fuselage, the engine back-support structure is arranged inside the back-support nacelle, and the engine is arranged on the fuselage through the engine back-support structure.
The above aspect and any possible implementation further provide an implementation in which the number of the engine back-up structures is 2 to 5.
The invention has the beneficial technical effects
The engine back support structure provided by the embodiment of the invention is used on an airplane and comprises an engine thrust rod, an engine front mounting section, an engine rear mounting section, an engine mounting beam, a beam front joint and an oblique beam support; the engine thrust rod, the engine front mounting section and the engine rear mounting section are all arranged at the bottom of the engine and are respectively connected with the engine; the engine front mounting section and the engine rear mounting section are both connected with the engine mounting beam; one end of the beam front joint is connected with the engine mounting beam, and the other end of the beam front joint is connected with a rear wall of an airplane body or a rear wing beam; the oblique beam supporting structure is connected with the engine mounting beam and the rear wall of the airplane body or the rear wing beam. The invention realizes the back-support type installation of the engine without changing the installation section and the thrust rod of the engine, has simple whole structure, adopts the components which are integrally formed, reduces the number of the components and is convenient for the installation of the back-support engine structure.
Drawings
Embodiments of the invention are described in detail below with reference to the attached drawing figures, wherein:
FIG. 1 is a schematic front view of an engine back support structure in an embodiment of the present invention;
FIG. 2 is a schematic side view of an engine back support structure in an embodiment of the present invention;
FIG. 3 is a schematic illustration of an engine back support mounting beam configuration in an embodiment of the present invention;
fig. 4 is a schematic view of an aircraft layout in an embodiment of the invention.
The figures are labeled as follows: 1. an aircraft; 2. back-supporting the nacelle; 3. a back-support structure fairing; 4. hanging a tail; 5. an engine; 6. an engine thrust rod; 7. a front mounting section of the engine; 8. a rear mounting section of the engine; 9. an engine mounting beam; 10. a beam front joint; 11. a fuselage rear wall or a wing rear spar; 12. a fuselage back wall or a wing back beam stud; 13. supporting the inclined beam; 91. an engine front mounting section mounting surface; 92. the engine rear mounting section mounting surface comprises 93 and a web plate; 94. vertical reinforcement; 95. obliquely reinforcing; 131. a first mounting surface; 132. a second mounting surface.
Detailed Description
In order to make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following detailed description is made with reference to the accompanying drawings and specific examples, but the embodiments of the present invention are not limited thereto.
As shown in fig. 1-2, the engine back support structure of the present invention includes an engine thrust rod 6, an engine front mounting section 7, an engine rear mounting section 8, an engine mounting beam 9, a beam front joint 10, and an oblique beam support 13; the engine thrust rod 6, the engine front mounting section 7 and the engine rear mounting section 8 are all arranged at the bottom of the engine 5, are connected with the engine 5 through fasteners and are used for transmitting the load of the engine 5 to the engine mounting beam 9, wherein the engine thrust rod 6 is used for transmitting the thrust of the engine 5, and the engine front mounting section 7 and the engine rear mounting section 8 are used for transmitting the vertical load and the lateral load of the engine 5.
Preferably, the engine 5 in the embodiment of the invention is mounted on the engine mounting beam 9 through the engine front mounting joint 7 and the engine rear mounting joint 8, and the engine mounting beam 9 is connected through the shear pin and the tensile bolt in a manner of introduction connection, so that the load transmitted by the engine front mounting joint 7 and the engine rear mounting joint 8 is borne by the engine mounting beam 9.
Preferably, as shown in fig. 3, in the embodiment of the present invention, the engine mounting beam 9 is an integrally formed web-type structure, and the engine back-support structure has a design requirement of safe damage, for example, when a certain structure is damaged, the remaining structure can meet a load-bearing requirement of limiting a load, and the damage of the whole structure is avoided, therefore, the web-type structure of the engine mounting beam 9 is formed by splicing symmetrical structures, each structure includes a web 93, an oblique 95 rib, a vertical 94 rib, and upper and lower mounting surfaces, wherein the web 93 bears the vertical load of the engine 5 and the nacelle; the diagonal rib 95 and the vertical rib 94 bear the side load of the engine 5, and the vertical rib 94 corresponds to the ribs of the beam front joint 10 and the diagonal beam support 13, so that the loads of the engine 5 and the nacelle 2 are transmitted to the fuselage structure. The web plate type structure provides four main load transmission mounting planes, and comprises an engine front mounting section mounting surface 91, an engine rear mounting section mounting surface 92, a mounting beam front joint mounting surface and an oblique beam support mounting surface, wherein the mounting surfaces can provide effective connecting surfaces, and the effective transmission of loads is ensured. The engine mount beam 9 has a sufficient width to satisfy the requirement of the side load, and has a length equivalent to or slightly shorter than the length of the engine 5.
Preferably, the beam front joint 10 in the embodiment of the present invention is also formed by splicing two integrally formed web-type symmetrical structures, but three mounting surfaces are provided, one of which is connected to the engine mounting beam 9 and is mounted by shear pins and tensile bolts; the other two mounting planes are connected with the rear wall of the fuselage or the rear beam 11 of the wing and are mounted through tensile bolts.
Preferably, in the embodiment of the present invention, the oblique beam support 13 is formed by splicing two integrally formed web-type symmetric structures, and provides two mounting surfaces, namely a first mounting surface 131 and a second mounting surface 132, where the first mounting surface 131 is connected with the fuselage rear wall or the wing rear beam 11 and is mounted by a tensile bolt; the second mounting face 132 is connected to the bottom of the engine mounting beam 9 and is mounted by shear pins and tension bolts.
In other words, in the embodiment of the invention, the engine mounting beam 9, the beam front joint 10 and the oblique beam support 13 are formed by splicing two integrally formed web type symmetrical structures, so that the damage safety of the engine back support structure is realized.
The fuselage rear wall or the wing rear beam 11 is of a C-shaped structure and provides transverse supporting rigidity, the fuselage rear wall or the wing rear beam 11 is of a structural form of an upper wall plate and a lower wall plate, the tensile strength is improved, vertical plates are arranged on the beam front joint 10 and the oblique beam support 13, and a fuselage rear wall or the wing rear beam stud 12 is arranged at the fuselage rear wall or the wing rear beam 11 corresponding to the two vertical plates, so that the rigidity of the engine supporting structure is ensured.
Further, the invention provides a beam front joint 10 and an oblique beam support 13, which are connected with an engine mounting beam 9 and a fuselage rear wall or a wing rear beam 11 to form a stable triangular structure, wherein the beam front joint 10 is connected with the upper edge of the fuselage rear wall or the wing rear beam 11, and the oblique beam support 13 is connected with the lower edge of the fuselage rear wall or the wing rear beam 11, so that the integral stability of an engine back support structure is ensured.
Preferably, as shown in fig. 4, in the embodiment of the present invention, the engine 5 and the back-supported nacelle 2 are mounted on the fuselage or wing by the engine back-supporting structure, especially when the engine 5 and the back-supported nacelle 2 are mounted on the fuselage, the engine back-supporting structure is located inside the back-supported nacelle 2, and the engine back-supporting structure transmits the load of the vertical fin 4.
Preferably, the number of the engine back support structures in the embodiment of the invention is 2-5 for each airplane, so that the propelling and functional requirements of the airplane are met.
The airplane 1 comprises a back-support nacelle 2, a back-support structure fairing 3 and a vertical tail 4, the engine back-support structure provided by the invention can be used for installing an engine 5 on the airplane body or the wings, a feasible scheme is provided for realizing the design of the airplane with the fused wing body, the engine 5 is positioned at the tail part of the airplane body, the vertical tail 4 is arranged at the upper side of the engine 5 or the engine 5 is arranged at the upper part of the wings, and the vertical tail 4 is arranged at the upper part of the tail part of the airplane body.
As described above, the engine mounting section is mounted under the engine, so that the engine front mounting section 7 and the engine rear mounting section 8 are mounted together with the front mounting section mounting surface 91 and the rear mounting section mounting surface 92 of the engine mounting beam 9, the loads of the engine 5 in multiple directions are effectively transmitted and loaded on the engine body structure, the engine front mounting section 7 transmits torsion, gravity and lateral force, the engine rear mounting section 8 transmits thrust, gravity and lateral force, the rear wall or wing rear beam 11 of the engine body is of the engine body structure, after the engine rear wall or wing rear beam is mounted, the beam front joint 10 and the oblique beam support 13 are mounted, then the engine mounting beam 9 is mounted, and finally the engine 5, the engine thrust rod 6, the engine front mounting section 7 and the engine rear mounting section 8 are assembled and connected with the mounting beam 9.
While the foregoing description shows and describes several preferred embodiments of the invention, it is to be understood, as noted above, that the invention is not limited to the forms disclosed herein, but is not intended to be exhaustive or to exclude other embodiments and may be used in various other combinations, modifications, and environments and is capable of changes within the scope of the invention as expressed herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. An engine back support structure is used on an airplane and is characterized by comprising an engine front mounting section, an engine rear mounting section, an engine mounting beam, a beam front joint and an oblique beam support; the engine front mounting section and the engine rear mounting section are both arranged at the bottom of the engine and are respectively connected with the engine;
the front engine mounting joint and the rear engine mounting joint are used for transferring vertical load and side load of the engine;
one end of the beam front joint is connected with the engine mounting beam, and the other end of the beam front joint is connected with the airplane wing rear beam;
the oblique beam support is connected with the engine mounting beam and the airplane wing back beam.
2. The engine back support structure according to claim 1, wherein the engine front mounting boss and the engine rear mounting boss are connected to the engine by fasteners, respectively.
3. The engine back support structure according to claim 1, wherein the engine front mount section and the engine rear mount section are each connected to the engine mount beam by a shear pin and a tensile bolt.
4. The engine back-up structure of claim 1, wherein the engine mounting beam is an integrally formed web structure, the web structure is formed by splicing symmetrical structures, and each symmetrical structure comprises a web plate, an oblique rib, a vertical rib and upper and lower mounting surfaces.
5. The engine back support structure of claim 4, wherein the web structure includes an engine front mount section mounting face, an engine rear mount section mounting face, a mounting beam front joint mounting face, and a raker beam support mounting face.
6. The engine back-up structure of claim 1, wherein the beam front joint is formed by splicing two integrally formed web-type symmetrical structures and comprises three mounting surfaces, wherein one mounting surface is connected with the engine mounting beam; the other two mounting planes are connected with the wing back beam of the airplane.
7. The engine back support structure of claim 1, wherein the inclined beam support structure is formed by splicing two integrally formed web-type symmetrical structures.
8. The engine back support structure of claim 1, wherein vertical plates are disposed on both the front beam joint and the oblique beam support structure.
9. An aircraft comprising the engine back-up structure of any one of claims 1 to 8, an engine, a fuselage, and a back-up nacelle, wherein the back-up nacelle is disposed on the fuselage, the engine back-up structure is disposed inside the back-up nacelle, and the engine is disposed on the fuselage through the engine back-up structure.
10. The aircraft of claim 9 wherein the number of engine back-up structures is 2-5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110919984.3A CN113581476A (en) | 2021-08-11 | 2021-08-11 | Engine back support structure and airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110919984.3A CN113581476A (en) | 2021-08-11 | 2021-08-11 | Engine back support structure and airplane |
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| Publication Number | Publication Date |
|---|---|
| CN113581476A true CN113581476A (en) | 2021-11-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110919984.3A Pending CN113581476A (en) | 2021-08-11 | 2021-08-11 | Engine back support structure and airplane |
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| CN (1) | CN113581476A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114435602A (en) * | 2022-03-19 | 2022-05-06 | 北京航空航天大学 | Unmanned aerial vehicle engine mounting bracket |
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2021
- 2021-08-11 CN CN202110919984.3A patent/CN113581476A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114435602A (en) * | 2022-03-19 | 2022-05-06 | 北京航空航天大学 | Unmanned aerial vehicle engine mounting bracket |
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