Connection Structure for Aeroengine Installation and Fixed-Wing Aircraft

Abstract

The present invention discloses a connecting structure for installing an aircraft engine and a fixed-wing aircraft. The connecting structure for installing the aircraft engine comprises: a partition, which is arranged obliquely on a fuselage; a load-bearing baffle, which is fixed to the oblique top edge of the partition, and is connected to a thrust strut that carries the thrust of the aircraft engine; a mounting platform is fixed to the oblique bottom of the partition; a connecting base is fixed to the mounting platform, and a shock-absorbing rubber is provided between the connecting base and the mounting platform, and the aircraft engine is fixed to the connecting base. The fixed-wing aircraft comprises an aircraft engine mounting structure, a fuselage and an aircraft engine, a plurality of support plates are provided at the rear of the fuselage corresponding to the cockpit, the support plates are fixed to the inside of the fuselage, the partition is obliquely fixed to the top of the support plate, the aircraft engine is fixed to the mounting platform, and the tail of the aircraft engine is rotatably connected to a propeller. The present invention realizes the power layout of a pushback engine, adds a thrust strut, improves structural reliability, and has good flame retardant and heat insulation effects.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft engine installation, and in particular relates to a connecting structure for aircraft engine installation and a fixed-wing aircraft. Background Art

[0002] At present, the development of light and small aircraft at home and abroad is becoming increasingly rapid, and the requirements for the installation of aircraft engines are becoming more and more stringent. Among aircraft of the same level, reducing the aircraft's own weight often means improving the aircraft's performance. The engine is the core component of the aircraft. Proper installation can not only ensure the performance of the aircraft, but also avoid safety hazards. The engine installation of traditional fixed-wing aircraft is a front-pull engine installation method, that is, the engine is installed on the nose of the aircraft and the propeller is installed in front of the engine, or the engine is installed on the side of the fuselage firewall through the engine support frame. The use of multiple aircraft engine layouts makes it difficult to achieve a rear thrust layout, and the installation is unreliable. The self-weight is large, affecting flight performance.

[0003] Chinese patent CN202121393468.3 discloses an engine mounting bracket for a light fixed-wing aircraft. The bracket is easy to assemble and disassemble, which facilitates the assembly of the engine. However, the bracket cannot solve the problem of high-temperature insulation when installing the engine, and further affects the service life of the bracket.

[0004] Therefore, how to provide a connection structure for mounting an aero-engine and a fixed-wing aircraft is a problem that those skilled in the art urgently need to solve. Summary of the Invention

[0005] In view of this, the present invention provides a connection structure for installing an aircraft engine and a fixed-wing aircraft. The aircraft engine installation structure can better share the thrust, solve the high-temperature insulation problem, and improve the connection stability of the structure. The pushback engine can protect the propeller, has high aerodynamic efficiency, improves thrust, and is more convenient to maintain.

[0006] In order to achieve the above-mentioned object, the present invention adopts the following technical solution: an aircraft engine mounting structure, comprising:

[0007] a partition, the partition being arranged obliquely on the fuselage;

[0008] A load-bearing baffle, the load-bearing baffle being vertically fixed to the inclined top edge of the partition, and the load-bearing baffle being connected to a thrust strut that carries the thrust of the aircraft engine;

[0009] a mounting stand fixed to the inclined bottom of the partition;

[0010] A connecting base is fixed on the mounting platform, a shock-absorbing rubber is provided between the connecting base and the mounting platform, and the aircraft engine is fixed on the connecting base.

[0011] The beneficial effects of the present invention are as follows: the aviation engine mounting structure can solve the problem of high-temperature heat insulation of the engine, better disperse the stress load, the partition can disperse the thrust of the engine to the fuselage, avoid stress concentration, and better extend the service life of the structure, the connecting base is used to connect the engine to the mounting platform, and shock-absorbing rubber is arranged between the connecting base and the mounting platform, which has a certain degree of expansion freedom and can also reduce noise, making the fuselage more stable during flight and less affected by engine vibration. The arranged thrust bracket can also reduce the radial force of the engine connecting bolts.

[0012] Preferably, the mounting stand includes an H-shaped base plate, an oil cooling seat plate and a supporting plate, the supporting plate is obliquely fixed on the partition, the oil cooling seat plate is vertically fixed to the inclined bottom of the partition, the H-shaped base plate is horizontally fixed to the top of the oil cooling seat plate and the supporting plate, and the connecting bases are grouped in pairs and are respectively fixed on the H-shaped base plate.

[0013] The resulting technical effect is: the H-shaped base plate is the installation base of the engine, which can disperse the thrust load of the engine to the fuselage; the oil cooling seat plate supports the H-shaped base plate while providing an installation base for the oil cooling assembly; the bearing plate is arranged obliquely on the partition plate, which supports the H-shaped base plate while better dispersing the radial thrust of the H-shaped base plate.

[0014] Preferably, the connecting base is an L-shaped aluminum alloy base, and the H-shaped bottom plate includes a PVC substrate layer and a carbon fiber reinforcement layer, and the thickness of the carbon fiber reinforcement layer gradually increases near the connection area of the metal connector.

[0015] The resulting technical effect is: the connecting base is made of aluminum alloy, which is light in weight, high in strength and has high fire resistance. The H-shaped base plate made of composite materials has high strength and adopts a distributed force connection method to optimize resource utilization while ensuring strength.

[0016] Preferably, the outer surfaces of the connecting base and the H-shaped bottom plate are coated with a flame retardant heat insulation layer.

[0017] The resulting technical effect is that the flame retardant thermal insulation layer can reduce the high temperature impact of the engine on the composite material and ensure the reliability of the structure.

[0018] Preferably, a lubricating oil cooling assembly is installed on the lubricating oil cooling seat plate.

[0019] The present invention also provides a fixed-wing aircraft, which includes an aircraft engine mounting structure, a fuselage and an aircraft engine. The fuselage is provided with a plurality of support plates at the rear of the cockpit, the support plates are fixed inside the fuselage, the partitions are fixed at an angle on the top of the support plates, the aircraft engine is fixed on a mounting stand, and the tail of the aircraft engine is rotatably connected to a propeller.

[0020] The resulting technical effect is: using the support plate to improve the reliability of the connection between the aircraft engine mounting structure and the fuselage, better disperse the force, realize the aviation power pushback layout of the fixed-wing aircraft, high aerodynamic efficiency, the propeller does not affect the pilot's performance, and can also avoid foreign objects hitting the propeller. The ground test is safe and convenient for maintenance.

[0021] Preferably, the aircraft engine is a piston aircraft engine, the thrust strut is arranged obliquely and its two ends are respectively connected to the aircraft engine and the load-bearing baffle.

[0022] The resulting technical effect is: using thrust struts to disperse the engine thrust to the fuselage structure, reducing the radial force of the engine connecting bolts, and extending the service life of the aircraft engine mounting structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 A schematic diagram of an aircraft engine mounting structure of the present invention Figure 1 ;

[0024] Figure 2 A schematic diagram of an aircraft engine mounting structure of the present invention Figure 2 ;

[0025] Figure 3 This is a schematic diagram of the installation of an aircraft engine mounting structure of the present invention. Figure 1 ;

[0026] Figure 4 This is a schematic diagram of the installation of an aircraft engine mounting structure of the present invention. Figure 2 ;

[0027] Figure 5 The structure of a fixed-wing aircraft of the present invention Figure 1 ;

[0028] Figure 6 The structure of a fixed-wing aircraft of the present invention Figure 2 .

[0029] 1 partition, 2 fuselage, 3 load baffle, 4 thrust strut, 5 aircraft engine, 6 mounting stand, 61H base plate, 62 oil cooling seat plate, 63 load-bearing plate, 7 connecting base, 8 shock-absorbing rubber, 9 oil cooling assembly, 10 support plate, 11 propeller. DETAILED DESCRIPTION

[0030] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0031] See the attached Figures 1 to 6 According to an embodiment of the present invention, a connection structure for mounting an aircraft engine includes:

[0032] Bulkhead 1 is arranged obliquely on the fuselage 2; the inclined bulkhead facilitates carrying the high-pressure thrust generated by the engine, facilitates distributing the load to the fuselage, and avoids stress concentration effects;

[0033] A load-bearing baffle 3 is vertically fixed to the inclined top edge of the partition 1. During actual use, both ends of the load-bearing baffle 3 are fixedly connected to the fuselage. A thrust strut 4 that bears the thrust of the aircraft engine 5 is connected to the load-bearing baffle. The thrust strut shares the radial force of the aircraft engine connecting bolts, thereby reducing the radial force of the aircraft engine connecting bolts and improving the reliability of the connection structure.

[0034] The mounting stand 6 is fixed to the inclined bottom of the partition 1 and is the basis for mounting the aircraft engine;

[0035] The connecting base 7 is fixed on the mounting stand 6. A shock-absorbing rubber 8 is provided between the connecting base 7 and the mounting stand 6. The aircraft engine 5 is fixed on the connecting base 7. The connecting base plays the role of transition connection to the engine. The shock-absorbing rubber reduces the vibration effect of the aircraft engine on the fuselage.

[0036] In other embodiments, the mounting stand 6 includes an H-shaped base plate 61, an oil cooling seat plate 62 and a bearing plate 63. The bearing plate 63 is fixed obliquely on the partition 1 and can also disperse the thrust load of the engine. The oil cooling seat plate 62 is vertically fixed on the inclined bottom of the partition 1, and the H-shaped base plate 61 is horizontally fixed on the top of the oil cooling seat plate 62 and the bearing plate 63. In actual use, the two ends of the H-shaped base plate are fixed to the fuselage, and the connecting bases 7 are grouped in pairs and fixed on the H-shaped base plate 61 respectively.

[0037] In other specific embodiments, the connecting base 7 is an L-shaped aluminum alloy base, and the H-shaped bottom plate 61 is a composite material plate, which includes a PVC substrate layer and a carbon fiber reinforcement layer. The thickness of the carbon fiber reinforcement layer gradually increases near the connection area of the metal connector, thereby increasing the regional connection strength. The connection area near the metal connector is the specific bolt connection area between the H-shaped bottom plate and the connecting base.

[0038] The connection area with the machine body is increased by connecting the base 7, so that the force is well dispersed.

[0039] In some other embodiments, the outer surfaces of the connecting base 7 and the H-shaped bottom plate 61 are coated with a flame retardant and heat-insulating layer. During actual use, the parts of the composite material affected by high temperature are coated with a flame retardant and heat-insulating material layer to improve the flame retardant and heat-insulating effect of the connecting structure (the operating temperature of the aircraft engine is high).

[0040] In some other specific embodiments, a lubricating oil cooling assembly 9 is installed on the lubricating oil cooling seat plate 62, and the lubricating oil cooling assembly establishes a communication relationship with the internal lubricating oil circuit of the engine. The lubricating oil is used to reduce the friction between the rotating parts, and the lubricating oil cooling assembly can ensure the normal operating temperature between the rotating parts.

[0041] The present invention also discloses a fixed-wing aircraft, which includes a connection structure for installing an aircraft engine, a fuselage 2 and an aircraft engine 5. A plurality of support plates 10 are provided at the rear of the fuselage 2 corresponding to the cockpit. The support plates 10 are fixed inside the fuselage. A partition 1 is fixed obliquely on the top of the support plates 10. The aircraft engine 5 is fixed on a mounting stand 6. The tail of the aircraft engine 5 is rotatably connected to a propeller 11.

[0042] The resulting technical effect is: the fixed-wing aircraft adopts a rear-push engine installation structure, the propeller will not affect the line of sight in the cockpit, and during ground tests, it will reduce accidental injuries to maintenance personnel. The rear-thrust layout can improve aerodynamic efficiency and increase thrust. The aircraft engine is arranged behind the fuselage cockpit, which can also protect the propeller and avoid being hit by foreign objects on the runway.

[0043] In other embodiments, the aircraft engine 5 is a piston aircraft engine, the thrust strut 4 is arranged at an angle and its two ends are respectively connected to the aircraft engine 5 and the load-bearing baffle 3. The thrust strut 4 can disperse the thrust of the engine to the load-baffle and even the fuselage, reducing stress concentration.

[0044] As for the devices and methods of use disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the description is relatively simple, and the relevant parts can be referred to the description of the methods.

[0045] The above description of the disclosed embodiments is intended to enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not limited to the embodiments shown herein but is intended to conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A connection structure for mounting an aircraft engine, characterized in that: include: A partition (1), the partition (1) being arranged obliquely on the fuselage (2); A load-bearing baffle (3), the load-bearing baffle (3) being vertically fixed to the inclined top edge of the partition (1), and a thrust strut (4) for bearing the thrust of the aircraft engine (5) being connected to the load-bearing baffle (3); A mounting frame (6), wherein the mounting frame (6) is fixed to the inclined bottom of the partition (1); the mounting frame (6) comprises an H-shaped bottom plate (61), a lubricating oil cooling seat plate (62) and a bearing plate (63); the bearing plate (63) is fixed obliquely on the partition (1); the lubricating oil cooling seat plate (62) is fixed vertically to the inclined bottom of the partition (1); and the H-shaped bottom plate (61) is fixed horizontally to the top of the lubricating oil cooling seat plate (62) and the bearing plate (63); A connecting base (7) is fixed on the mounting platform (6), a shock-absorbing rubber (8) is provided between the connecting base (7) and the mounting platform (6), and the aircraft engine (5) is fixed on the connecting base (7).

2. The connection structure for mounting an aircraft engine according to claim 1, characterized in that: The connecting bases (7) are grouped in pairs and are respectively fixed on the H-shaped bottom plate (61).

3. The connection structure for mounting an aircraft engine according to claim 2, characterized in that: The connecting base (7) is an L-shaped aluminum alloy base, and the H-shaped bottom plate (61) includes a PVC substrate layer and a carbon fiber reinforcement layer, wherein the thickness of the carbon fiber reinforcement layer gradually increases near the connection area of the metal connector.

4. The connection structure for mounting an aircraft engine according to claim 3, characterized in that: The outer surfaces of the connecting base (7) and the H-shaped bottom plate (61) are both coated with a flame retardant heat insulation layer.

5. The connection structure for mounting an aircraft engine according to claim 2, characterized in that: A lubricating oil cooling assembly (9) is installed on the lubricating oil cooling seat plate (62).

6. A fixed-wing aircraft, characterized in that: The invention comprises a connecting structure for mounting an aircraft engine according to any one of claims 1 to 5, a fuselage (2) and an aircraft engine (5), wherein the fuselage (2) is provided with a plurality of support plates (10) at the rear of the cabin, the support plates (10) are fixed inside the fuselage, the partition (1) is fixed obliquely on the top of the support plates (10), the aircraft engine (5) is fixed on a mounting stand (6), and the tail of the aircraft engine (5) is rotatably connected to a propeller (11).

7. The fixed-wing aircraft according to claim 6, characterized in that: The aero-engine (5) is a piston-type aero-engine, the thrust strut (4) is arranged obliquely, and its two ends are respectively connected to the aero-engine (5) and the force-bearing baffle (3).

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