CN117699021A - A truss-type engine mounting structure - Google Patents
A truss-type engine mounting structure Download PDFInfo
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- CN117699021A CN117699021A CN202311837418.3A CN202311837418A CN117699021A CN 117699021 A CN117699021 A CN 117699021A CN 202311837418 A CN202311837418 A CN 202311837418A CN 117699021 A CN117699021 A CN 117699021A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
本申请属于飞机发动机安装结构领域，特别涉及一种桁架式发动机安装结构。包括：前框，呈U形，所述前框上设置有用于发动机安装的接口；中框，呈U形，所述中框的前侧通过多根拉杆与所述前框连接，所述中框上设置有用于发动机安装的接口；后框，呈环形，所述后框的前侧通过多根拉杆与所述中框的后侧连接，所述后框的后侧通过多根拉杆与机翼连接；其中，相邻两个拉杆呈V形布置，所述发动机安装结构的底部形成用于发动机拆装的矩形开口。本申请能够将涡轮螺旋桨发动机安装在机翼下方，并且能够承受发动机拉力、扭矩及惯性载荷，传力直接，结构重量轻。
The present application belongs to the field of aircraft engine mounting structures, and particularly relates to a truss-type engine mounting structure. It includes: a front frame, which is U-shaped, and an interface for engine installation is provided on the front frame; a middle frame, which is U-shaped, and the front side of the middle frame is connected to the front frame through a plurality of tie rods. The frame is provided with an interface for engine installation; the rear frame is annular, the front side of the rear frame is connected to the rear side of the middle frame through multiple tie rods, and the rear side of the rear frame is connected to the machine through multiple tie rods. Wing connection; wherein, two adjacent tie rods are arranged in a V shape, and the bottom of the engine mounting structure forms a rectangular opening for engine disassembly and assembly. This application can install the turboprop engine under the wing, and can withstand engine pulling force, torque and inertia load, transmit force directly, and have light structural weight.
Description
Technical Field
The application belongs to aircraft engine mounting structure field, in particular to truss-like engine mounting structure.
Background
The engine mounting structure is a key part of the aircraft, and the engine can be safely and reliably mounted on the aircraft and directly related to the safety of flight. Generally, wing-mounted turboprop engine mounting structures can be divided into box-section and truss structures.
In the prior art, the box section type engine mounting structure is characterized in that the engine is mounted by arranging the load transmission box section between the wing and the engine, the engine mounting structure is independent and is less restricted by the engine, the engine is convenient to mount, dismount and maintain, but the structure is heavy, and larger resistance is brought to the aircraft. The truss type engine mounting structure is small in occupied space and simple in structural form, but the truss type engine mounting structure is poor in torsional rigidity, and the engine needs to be pushed out of the mounting structure forwards when being dismounted, or part of the pull rod needs to be dismounted, so that the quick-change requirement is difficult to meet.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a truss engine mounting structure that solves at least one of the problems of the prior art.
The technical scheme of the application is as follows:
a truss engine mounting structure, the engine mounting structure comprising:
the front frame is U-shaped, and an interface for mounting the engine is arranged on the front frame;
the middle frame is U-shaped, the front side of the middle frame is connected with the front frame through a plurality of pull rods, and an interface for installing an engine is arranged on the middle frame;
the rear frame is annular, the front side of the rear frame is connected with the rear side of the middle frame through a plurality of pull rods, and the rear side of the rear frame is connected with the wing through a plurality of pull rods;
the two adjacent pull rods are arranged in a V shape, and a rectangular opening for disassembling and assembling the engine is formed at the bottom of the engine mounting structure.
In at least one embodiment of the present application, the plurality of tie rods on the rear side of the rear frame are connected to the wing through a wing lower wall joint, a wing lower edge joint and a wing upper edge joint, respectively.
In at least one embodiment of the present application,
the front frame is of a rib structure of an open-section web plate with a front frame web plate and a front frame reinforcing rib;
three I-shaped butt joint areas are arranged on the top and the left side and the right side of the front frame, and each I-shaped butt joint area is provided with a shock absorber butt joint hole, wherein torque compensator butt joint holes are further formed above the shock absorber butt joint holes on the left side and the right side;
the bottom of the front frame is symmetrically provided with a butt joint single lug.
In at least one embodiment of the present application, an I-shaped butt joint is mounted in each of the three I-shaped butt joint butt joints of the front frame, the I-shaped butt joint having two single-ear tabs distributed in a straight line.
In at least one embodiment of the present application,
the middle frame is of a rib structure with a middle frame web and a middle frame reinforcing rib and provided with a cross-section web;
two L-shaped butt joint areas are arranged at the top of the middle frame;
the left side and the right side of the middle frame are respectively provided with a shock absorber connecting double ear;
two first frame joint connection areas are symmetrically arranged at the bottom of the middle frame.
In at least one embodiment of the present application,
the two L-shaped butt joint butt joints of the middle frame are respectively provided with an L-shaped butt joint, and each L-shaped butt joint is provided with two single-lug lugs distributed in an L shape;
the first frame joint connection that crosses in two places of center connects installs respectively and crosses the frame joint, cross the frame joint and have four single ear tabs, wherein, the single ear tab of bottom is the outside interface of mounting structure.
In at least one embodiment of the present application,
the rear frame is of a closed section web reinforced structure with a rear frame web and rear frame reinforced ribs;
five second frame joint connection areas are arranged on the rear frame and are respectively positioned at four corners and the top of the rear frame.
In at least one embodiment of the present application, a firewall connection edge is disposed at the annular opening of the rear frame.
In at least one embodiment of the present application, the five second frame-passing joint joints of the rear frame are respectively provided with a four-ear frame-passing joint or a three-ear frame-passing joint, the four-ear frame-passing joint is provided with four single-ear tabs, and the three-ear frame-passing joint is provided with three single-ear tabs, wherein the single-ear tab at the bottom is an external interface of the mounting structure.
In at least one embodiment of the present application, two ends of the pull rod are in a binaural joint shape, and the middle part is in an equal straight circular ring shape.
The invention has at least the following beneficial technical effects:
the truss type engine mounting structure can mount the turboprop engine below the wing and can bear engine tension, torque and inertial load; the engine mounting structure adopts a multi-force transmission path design, is a damaged mounting structure and can ensure the flight safety of an airplane to the greatest extent; the engine mounting structure has direct force transmission and light structure weight; the engine mounting structure has a concise lower opening, and can ensure the daily inspection maintenance and quick replacement requirements of the engine.
Drawings
FIG. 1 is a schematic illustration of a truss engine mounting structure assembly of one embodiment of the present application;
FIG. 2 is an angular view of a truss engine mounting structure of an embodiment of the present application;
FIG. 3 is another angular view of a truss engine mounting structure of an embodiment of the present application;
FIG. 4 is a schematic view of a U-shaped front frame of one embodiment of the present application;
FIG. 5 is a schematic view of a U-shaped middle frame of one embodiment of the present application;
FIG. 6 is a schematic view of an annular back frame of one embodiment of the present application;
FIG. 7 is a schematic illustration of an I-shaped butt joint connection of one embodiment of the present application;
FIG. 8 is a schematic illustration of an L-shaped butt joint connection of one embodiment of the present application;
FIG. 9 is a schematic view of a frame joint connection according to one embodiment of the present application;
fig. 10 is a schematic diagram of a four-ear through-frame joint connection according to one embodiment of the present application.
Wherein:
1-an engine mounting structure; 11-front frame; 111-a damper docking hole; 112-torque compensator docking aperture; 113-butt joint single ear; 114-front frame reinforcing ribs; 115-front frame web; 12-middle frame; 121-the shock absorber connects the ears; 122-a first frame-passing joint connection region; a 123-L shaped butt joint section; 124-middle frame reinforcing ribs; 125-middle frame web; 13-a rear frame; 131-a second frame-passing joint connection region; 132-a rear frame reinforcing rib; 133-a rear frame web; 134-firewall connection edge; 14-a pull rod; 15-I-shaped butt joint; a 16-L shaped butt joint; 17-a frame-passing joint; 18-four-ear frame joint; 19-three-ear frame joint; 20-wing lower wall joints; 21-a wing lower edge joint; 22-wing upper edge joint; 2-an engine; 3-wings; 4-an engine damper; 5-torque compensator.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application. Embodiments of the present application are described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of protection of the present application.
The present application is described in further detail below with reference to fig. 1-10.
The application provides a truss engine mounting structure for mounting a turboprop 2 under an aircraft wing 3. The engine mounting structure 1 includes: the front frame 11, the middle frame 12, the rear frame 13, the pull rods 14 and the plurality of joint structures form a statically indeterminate truss structure.
Specifically, as shown in fig. 1, the engine mounting structure 1 is divided into three sections by three frames, the front frame 11 and the middle frame 12 are all in a U shape, openings are downwards arranged, interfaces for mounting the engine 2 are respectively arranged on the front frame 11 and the middle frame 12, the front side of the middle frame 12 is connected with the front frame 11 through 6 pull rods 14, the rear frame 13 is in a ring shape, the front side of the rear frame 13 is connected with the rear side of the middle frame 12 through 8 pull rods 14, and the rear side of the rear frame 13 is connected with the wing 3 through 8 pull rods 14; wherein, two adjacent pull rods 14 are arranged in a V shape, a space truss is formed by a frame and the pull rods 14, the left side, the right side and the top of the engine mounting structure 1 are in a stable triangle structure from the integral geometric topology, and a rectangular opening for dismounting the engine 2 is formed at the bottom. As shown in fig. 2 and 3, 8 tie rods 14 behind the annular rear frame 13 are connected to the wing 3 via a wing lower wall joint 20, a wing lower edge joint 21 and a wing upper edge joint 22.
In the preferred embodiment of the present application, as shown in fig. 4, the front frame 11 is an open-section web-stiffened structure having a front frame web 115 and a front frame stiffener 114, and the overall rigidity is improved by the front frame stiffener 114; three I-shaped butt joint areas are arranged on the top and the left side and the right side of the front frame 11, and each I-shaped butt joint area is provided with a damper butt joint hole 111 for assembling the engine damper 4, wherein a torque compensator butt joint hole 112 for assembling the torque compensator 5 is also arranged above the damper butt joint holes 111 on the left side and the right side; the bottom of the front frame 11 is symmetrically provided with a single butt joint lug 113, and the single butt joint lug 113 is an external interface of the mounting structure.
In the preferred embodiment of the present application, as shown in fig. 5, the middle frame 12 is an open-section web reinforced structure with a middle frame web 125 and middle frame reinforcing ribs 124, and the overall rigidity and web stability can be effectively improved by the triangular arrangement of the middle frame reinforcing ribs 124; two L-shaped butt joint areas 123 are arranged on two sides of the top of the middle frame 12; four groups of shock absorber connecting double ears 121 are respectively arranged on the left side and the right side of the middle frame 12; two first frame-passing joint connection areas 122 are symmetrically arranged at the bottom of the middle frame 12.
In the preferred embodiment of the present application, as shown in fig. 6, the rear frame 13 is a closed-section web-stiffened structure having a rear frame web 133 and a rear frame stiffener 132; five second frame-passing joint connection areas 131 are arranged on the rear frame 13 and are respectively positioned at four corners and the top of the rear frame 13. The rear frame stiffener 132 within the rear frame 13 is arranged in a triangle/quadrilateral configuration to increase the out-of-plane stiffness of the frame. In this embodiment, the annular opening of the rear frame 13 is preferably provided with a firewall connection edge 134.
In the preferred embodiment of the present application, the U-shaped front frame 11 and the middle frame 12, and the annular rear frame 13 may be machined from different materials such as aluminum alloy, titanium alloy, or alloy steel, depending on the design requirements.
The truss type engine mounting structure is characterized in that corresponding pull rod joints are mounted on each frame structure, and accordingly assembly of each pull rod is achieved. Each pull rod joint consists of a single lug and a frame connecting surface, and can be formed by machining different materials such as aluminum alloy, titanium alloy or alloy steel according to different design requirements. As shown in fig. 7, the three I-shaped butt joint butt joints of the front frame 11 are respectively provided with an I-shaped butt joint 15, the I-shaped butt joint 15 is provided with two single-lug lugs distributed in a straight line, and each single-lug is connected with the pull rod 14 through a bolt; the frame connection surface of the I-shaped butt joint 15 is connected with the U-shaped front frame 11 through bolts. As shown in fig. 8 and 9, the two L-shaped butt joint areas 123 of the middle frame 12 are respectively provided with an L-shaped butt joint 16, the L-shaped butt joint 16 is provided with two single-lug lugs distributed in an L shape, and each single-lug is connected with the pull rod 14 through a bolt; the two L-shaped butt joints 16 are distributed on two sides of the U-shaped middle frame 12, and the two L-shaped butt joints 16 are connected with the middle frame 12 through bolts. The two first frame joint connection areas 122 of the middle frame 12 are respectively provided with a frame joint 17, the frame joint 17 is provided with four single-lug lugs, wherein the single-lug lugs at the bottom are external interfaces of the mounting structure, and lugs at the front end penetrate through openings of the first frame joint connection areas 122 and are connected with the pull rod 14 through bolts. As shown in fig. 10, the five second frame-passing joint connection areas 131 of the rear frame 13 are respectively provided with a four-ear frame-passing joint 18 or a three-ear frame-passing joint 19, the four-ear frame-passing joint 18 is provided with four single-ear lugs, each of which is connected with the pull rod 14 through bolts, two lugs at the front end penetrate through the openings of the second frame-passing joint connection areas 131 and are connected with the pull rod 14 through bolts, and the three-ear frame-passing joint 19 is provided with three single-ear lugs, wherein the single-ear lug at the bottom is an external interface of the mounting structure, and the mounting form of the single-ear lug is similar to that of the frame-passing joint 17.
The truss type engine mounting structure adopts the connection mode of the frame-passing joint, can effectively transfer the pull rod load through the joint, effectively avoids the tension of bolts, and improves the fatigue performance.
In the preferred embodiment of the present application, the two ends of the pull rod 14 are in the shape of double-lug joints, the middle is in the shape of an equal straight circular ring, the pull rod 14 can be made of different materials such as aluminum alloy, titanium alloy, alloy steel or composite material, and the structural form of the pull rod 14 can be an integral type, a threaded connection type or a welding type.
According to the truss type engine mounting structure, a hyperstatic structure is adopted to meet the damage safety requirement; the three-section truss is adopted, the engine is far away from the wing, and the blasting design requirement of the rotor of the aircraft engine is met; through the design of the open section, the disassembly, assembly and maintenance of the engine are convenient; the pull rod is matched with the frame through the joint single and double ears, and the bolt is in a sheared connection mode, so that the bolt is effectively prevented from being pulled, the fatigue weak point is reduced, and the service life of the engine mounting structure is prolonged.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A truss type engine mounting structure, characterized in that the engine mounting structure (1) includes:
the front frame (11) is U-shaped, and an interface for installing the engine (2) is arranged on the front frame (11);
the middle frame (12) is U-shaped, the front side of the middle frame (12) is connected with the front frame (11) through a plurality of pull rods (14), and an interface for installing the engine (2) is arranged on the middle frame (12);
the rear frame (13) is annular, the front side of the rear frame (13) is connected with the rear side of the middle frame (12) through a plurality of pull rods (14), and the rear side of the rear frame (13) is connected with the wing (3) through a plurality of pull rods (14);
the two adjacent pull rods (14) are arranged in a V shape, and a rectangular opening for disassembling and assembling the engine (2) is formed at the bottom of the engine mounting structure (1).
2. Truss engine mounting structure according to claim 1, characterized in that the tie rods (14) at the rear side of the rear frame (13) are connected to the wing (3) via a lower wing wall joint (20), a lower wing edge joint (21) and an upper wing edge joint (22), respectively.
3. The truss engine mounting structure of claim 1 wherein,
the front frame (11) is of an open-section web reinforced structure with a front frame web (115) and front frame reinforced ribs (114);
three I-shaped butt joint areas are arranged at the top and the left and right sides of the front frame (11), and each I-shaped butt joint area is provided with a damper butt joint hole (111), wherein a torque compensator butt joint hole (112) is further formed above the damper butt joint holes (111) at the left and right sides;
the bottom of the front frame (11) is symmetrically provided with a butt joint single lug (113).
4. A truss type engine mounting structure according to claim 3, wherein I-shaped butt joints (15) are respectively mounted at three I-shaped butt joint butt joints of the front frame (11), the I-shaped butt joints (15) having two single-lug tabs distributed in a straight line.
5. The truss engine mounting structure of claim 1 wherein,
the middle frame (12) is of an open-section web reinforced structure with a middle frame web (125) and middle frame reinforced ribs (124);
two L-shaped butt joint areas (123) are arranged at the top of the middle frame (12);
the left side and the right side of the middle frame (12) are respectively provided with a shock absorber connecting double ear (121);
two first frame joint connecting areas (122) are symmetrically arranged at the bottom of the middle frame (12).
6. The truss engine mounting structure of claim 5 wherein,
the two L-shaped butt joint areas (123) of the middle frame (12) are respectively provided with an L-shaped butt joint (16), and the L-shaped butt joint (16) is provided with two single-lug lugs distributed in an L shape;
the two first frame-passing joint connection areas (122) of the middle frame (12) are respectively provided with a frame-passing joint (17), and the frame-passing joint (17) is provided with four single-lug lugs, wherein the single-lug lugs at the bottom are external interfaces of the mounting structure.
7. The truss engine mounting structure of claim 1 wherein,
the rear frame (13) is of a closed-section web reinforcement structure with a rear frame web (133) and rear frame reinforcing ribs (132);
five second frame-passing joint connection areas (131) are arranged on the rear frame (13) and are respectively positioned at four corners and the top of the rear frame (13).
8. The truss type engine mounting structure according to claim 7, wherein a firewall connection edge (134) is provided at an annular opening of the rear frame (13).
9. The truss-like engine mounting structure according to claim 7, wherein five second frame-passing joint connection areas (131) of the rear frame (13) are respectively provided with a four-lug frame-passing joint (18) or a three-lug frame-passing joint (19), the four-lug frame-passing joint (18) is provided with four single-lug lugs, the three-lug frame-passing joint (19) is provided with three single-lug lugs, and the single-lug lugs at the bottom are external interfaces of the mounting structure.
10. The truss type engine mounting structure according to claim 1, wherein both ends of the tie rod (14) are in a binaural joint shape, and a middle portion is in an equi-straight circular shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311837418.3A CN117699021A (en) | 2023-12-28 | 2023-12-28 | A truss-type engine mounting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311837418.3A CN117699021A (en) | 2023-12-28 | 2023-12-28 | A truss-type engine mounting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117699021A true CN117699021A (en) | 2024-03-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311837418.3A Pending CN117699021A (en) | 2023-12-28 | 2023-12-28 | A truss-type engine mounting structure |
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| Country | Link |
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| CN (1) | CN117699021A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118637068A (en) * | 2024-07-31 | 2024-09-13 | 九成通用飞机设计制造(大连)有限公司 | Engine nacelle with hyperstatic structure |
| CN121553375A (en) * | 2025-11-24 | 2026-02-24 | 陕西飞机工业有限责任公司 | Engine bracket with multi-connecting rod suspension structure and assembly method |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6123293A (en) * | 1997-04-01 | 2000-09-26 | Deutsches Zentrum Fur Luft-Und Raumfahrt E.V. | Engine mount, particularly for a propeller-driven aircraft, comprising a tubular frame structure |
| US20160280381A1 (en) * | 2013-11-18 | 2016-09-29 | Lord Corporation | Turboprop engine attachment systems and methods |
-
2023
- 2023-12-28 CN CN202311837418.3A patent/CN117699021A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6123293A (en) * | 1997-04-01 | 2000-09-26 | Deutsches Zentrum Fur Luft-Und Raumfahrt E.V. | Engine mount, particularly for a propeller-driven aircraft, comprising a tubular frame structure |
| US20160280381A1 (en) * | 2013-11-18 | 2016-09-29 | Lord Corporation | Turboprop engine attachment systems and methods |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118637068A (en) * | 2024-07-31 | 2024-09-13 | 九成通用飞机设计制造(大连)有限公司 | Engine nacelle with hyperstatic structure |
| CN121553375A (en) * | 2025-11-24 | 2026-02-24 | 陕西飞机工业有限责任公司 | Engine bracket with multi-connecting rod suspension structure and assembly method |
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