Resonance exhaust pipe of aviation piston engine

Abstract

The invention provides a resonance exhaust pipe of an aviation piston engine. The resonance exhaust pipe comprises a first exhaust manifold connected with an exhaust port of a first air cylinder of the aviation piston engine; the second exhaust manifold is connected with an exhaust port of a second cylinder of the aviation piston engine; the exhaust end of the first exhaust manifold and the exhaust end of the second exhaust manifold are both connected with the air inlet end of a corrugated vibration reduction pipe. The exhaust end of the corrugated vibration reduction pipe is connected with the air inlet end of the diverging pipe; the exhaust end of the diverging pipe is connected with the air inlet end of the straight pipe; the exhaust end of the straight pipe is connected with the air inlet end of the reducing pipe; the exhaust end of the reducing pipe is connected with the air inlet end of the exhaust tail pipe, and the exhaust end of the exhaust tail pipe is connected with the air inlet end of the turbocharger. According to the scheme, through the first exhaust manifold, the second exhaust manifold, the corrugated vibration reduction pipe, the diverging pipe, the straight pipe, the reducing pipe and the exhaust tail pipe, uniform exhaust of the two air cylinders of the engine can be achieved, exhaust resistance is reduced, and engine power is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aviation piston engine exhaust, in particular to a resonance exhaust pipe of an aviation piston engine. Background Art

[0002] With the widespread use of drones, the requirements for drone power devices are high power, low fuel consumption, and good high-altitude performance. The aviation piston two-stroke engine is small in size, light in weight, and simple in structure, making it a good choice for drone power. The two-stroke engine does not have an independent intake and exhaust structure for separate ventilation, and its working state is directly related to the ventilation quality. After adding the supercharging system, the design of the exhaust resonance tube has a great influence on the ventilation quality and the utilization of intake and exhaust energy. In order to efficiently utilize the exhaust capacity of the two-stroke engine, the design of the exhaust pipe is particularly important. Summary of the invention

[0003] The present invention provides a resonance exhaust pipe for an aviation piston engine. Through a first exhaust manifold, a second exhaust manifold, a corrugated vibration damping pipe, a gradually expanding pipe, a straight pipe, a gradually contracting pipe and an exhaust tail pipe, uniform exhaust of two cylinders of the aviation piston engine can be achieved, exhaust resistance can be effectively reduced, and the power of the aviation piston engine can be improved. The corrugated vibration damping pipe can achieve position compensation and shock absorption effects, thereby preventing the exhaust pipeline from being damaged by vibration cracking caused by the vibration of the aviation piston engine.

[0004] In order to solve the above technical problems, the technical solution of the present invention is as follows:

[0005] An aviation piston engine resonance exhaust pipe, comprising:

[0006] a first exhaust manifold connected to the exhaust port of the first cylinder of the aviation piston engine;

[0007] a second exhaust manifold connected to the exhaust port of the second cylinder of the aviation piston engine;

[0008] The exhaust ends of the first exhaust manifold and the second exhaust manifold are both connected to the intake end of the corrugated vibration damping pipe;

[0009] The exhaust end of the corrugated vibration damping pipe is connected to the intake end of the gradually expanding pipe;

[0010] The exhaust end of the gradually expanding pipe is connected to the intake end of the straight pipe;

[0011] The exhaust end of the straight pipe is connected to the intake end of the tapered pipe;

[0012] The exhaust end of the reducer is connected to the air intake end of the exhaust tail pipe, and the exhaust end of the exhaust tail pipe is connected to the air intake end of the turbocharger.

[0013] Optionally, the exhaust ends of the first exhaust manifold and the second exhaust manifold form a preset angle, and the exhaust ends of the first exhaust manifold and the second exhaust manifold are formed with connecting pipes, and the connecting pipes are connected to the intake end of the corrugated vibration damping pipe.

[0014] Optionally, the air inlet end of the corrugated vibration damping tube is connected to the connecting tube via a V-shaped clamp, and the air outlet end of the corrugated vibration damping tube is connected to the air inlet end of the gradually expanding tube via a V-shaped clamp.

[0015] Optionally, the lengths and outer diameters of the first exhaust manifold, the second exhaust manifold, the corrugated vibration damping pipe, the gradually expanding pipe, the straight pipe, the gradually converging pipe and the exhaust tail pipe are determined by a first formula.

[0016] Optionally, the extension directions of the first exhaust manifold, the second exhaust manifold, the corrugated vibration damping pipe, the gradually expanding pipe, the straight pipe, the gradually converging pipe and the exhaust tail pipe are determined according to the spatial layout of the aviation piston engine.

[0017] Optionally, the aviation piston engine resonance exhaust pipe further comprises:

[0018] a first fixing frame connected to the reducer;

[0019] a second fixing frame connected to the straight pipe;

[0020] The first fixing frame and the second fixing frame are connected to the outer casing of the aviation piston engine.

[0021] Optionally, the first fixing frame includes:

[0022] an arc-shaped portion connected to the reducer;

[0023] A horizontal connecting portion is formed at both ends of the arc-shaped portion, and a first connecting hole is penetrated through the surface of the horizontal connecting portion.

[0024] Optionally, the first connection hole extends horizontally and passes through a side surface of the horizontal connection portion.

[0025] Optionally, the second fixing frame is a plate-shaped structure, and a second connecting hole is provided through the surface of the second fixing frame.

[0026] Optionally, the cross-section of the second fixing frame is a U-shaped structure.

[0027] The above solution of the present invention includes at least the following beneficial effects:

[0028] The above scheme of the present invention can achieve uniform exhaust of two cylinders of an aviation piston engine through the first exhaust manifold, the second exhaust manifold, the bellows damper tube, the gradually expanding tube, the straight tube, the gradually contracting tube and the exhaust tail pipe, thereby effectively reducing exhaust resistance and improving the power of the aviation piston engine; the bellows damper tube can play a position compensation and shock absorbing effect, thereby avoiding vibration cracking and damage to the exhaust pipeline caused by the vibration of the aviation piston engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic diagram of the three-dimensional structure of a resonance exhaust pipe of an aviation piston engine provided by an embodiment of the present invention;

[0030] Figure 2 is a top view of a resonance exhaust pipe of an aviation piston engine provided by an embodiment of the present invention;

[0031] Figure 3 The present invention is a schematic diagram of the connection structure between the resonance exhaust pipe of an aviation piston engine and the engine provided by an embodiment of the present invention.

[0032] The following are the descriptions of the reference numerals:

[0033] 1. First exhaust manifold; 2. Second exhaust manifold; 3. Corrugated vibration damping pipe; 4. First fixing frame; 5. Gradual expansion pipe; 6. Second fixing frame; 7. Straight pipe; 8. Gradual contraction pipe; 9. Exhaust tail pipe. DETAILED DESCRIPTION

[0034] The exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present invention and to enable the scope of the present invention to be fully communicated to those skilled in the art.

[0035] like Figures 1 to 3 As shown, an embodiment of the present invention provides an aviation piston engine resonance exhaust pipe, comprising:

[0036] A first exhaust manifold 1 connected to the exhaust port of the first cylinder of the aviation piston engine;

[0037] A second exhaust manifold 2 connected to the exhaust port of the second cylinder of the aviation piston engine;

[0038] The exhaust ends of the first exhaust manifold 1 and the second exhaust manifold 2 are both connected to the intake end of the corrugated vibration damping pipe 3;

[0039] The exhaust end of the corrugated vibration damping tube 3 is connected to the intake end of the gradually expanding tube 5;

[0040] The exhaust end of the gradually expanding pipe 5 is connected to the intake end of the straight pipe 7;

[0041] The exhaust end of the straight pipe 7 is connected to the intake end of the tapered pipe 8;

[0042] The exhaust end of the reducer 8 is connected to the intake end of the exhaust tail pipe 9, and the exhaust end of the exhaust tail pipe 9 is connected to the intake end of the turbocharger.

[0043] In this embodiment, the aviation piston engine is a horizontally opposed two-cylinder two-stroke aviation piston engine, and the ignition timing of the first cylinder and the second cylinder of the aviation piston engine differs by 180°CA;

[0044] When the aviation piston engine is working, the first cylinder of the aviation piston engine is in the ignition power stroke, the second cylinder of the aviation piston engine is in the compression stroke, the exhaust port of the first cylinder of the aviation piston engine is opened, the scavenging port of the first cylinder of the aviation piston engine is closed, the scavenging port of the second cylinder of the aviation piston engine is opened, the exhaust port of the second cylinder of the aviation piston engine is opened, the pressure in the first cylinder of the aviation piston engine is greater than the pressure in the diffuser 5, the exhaust gas in the first cylinder of the aviation piston engine enters the diffuser 5 through the first exhaust manifold 1 and the corrugated vibration damping tube 3, the air enters the second cylinder of the aviation piston engine, and the second The pressure in the cylinder is lower than the pressure in the gradually expanding tube 5, and the air is sealed in the second cylinder of the aviation piston engine; the exhaust port of the first cylinder of the aviation piston engine is opened, the scavenging port of the first cylinder of the aviation piston engine is opened, the scavenging port of the second cylinder of the aviation piston engine is closed, the exhaust port of the second cylinder of the aviation piston engine is opened, and the air enters the first cylinder of the aviation piston engine. The pressure in the first cylinder of the aviation piston engine is lower than the pressure in the gradually expanding tube 5, and the air is sealed in the first cylinder of the aviation piston engine. The pressure in the second cylinder of the aviation piston engine is lower than the pressure in the gradually expanding tube 5, and the air is sealed in the second cylinder of the aviation piston engine;

[0045] The second cylinder of the aviation piston engine is in the ignition power stroke, the first cylinder of the aviation piston engine is in the compression stroke, the exhaust port of the second cylinder of the aviation piston engine is opened, the scavenging port of the second cylinder of the aviation piston engine is closed, the scavenging port of the first cylinder of the aviation piston engine is opened, the exhaust port of the first cylinder of the aviation piston engine is opened, the pressure in the second cylinder of the aviation piston engine is greater than the pressure in the diffuser 5, the exhaust gas in the second cylinder of the aviation piston engine enters the diffuser 5 through the second exhaust manifold 2 and the corrugated vibration damping tube 3, the air enters the first cylinder of the aviation piston engine, and the pressure in the first cylinder of the aviation piston engine is The pressure is less than the pressure in the gradually expanding tube 5, and the air is sealed in the first cylinder of the aviation piston engine; the exhaust port of the second cylinder of the aviation piston engine is opened, the scavenging port of the second cylinder of the aviation piston engine is opened, the scavenging port of the first cylinder of the aviation piston engine is closed, the exhaust port of the first cylinder of the aviation piston engine is opened, and the air enters the first cylinder of the aviation piston engine. The pressure in the first cylinder of the aviation piston engine is less than the pressure in the gradually expanding tube 5, and the air is sealed in the first cylinder of the aviation piston engine. The pressure in the second cylinder of the aviation piston engine is less than the pressure in the gradually expanding tube 5, and the air is sealed in the second cylinder of the aviation piston engine;

[0046] The exhaust gas in the gradually expanding pipe 5 enters the turbocharger through the straight pipe 7, the gradually contracting pipe 8 and the exhaust tail pipe 9;

[0047] Through the above process, the two cylinders of the aviation piston engine can be evenly exhausted through the first exhaust manifold 1, the second exhaust manifold 2, the corrugated vibration damping tube 3, the gradually expanding tube 5, the straight tube 7, the gradually contracting tube 8 and the exhaust tail pipe 9, thereby effectively reducing the exhaust resistance and improving the power of the aviation piston engine; the corrugated vibration damping tube 3 can achieve position compensation and shock absorption effects, thereby avoiding vibration and damage to the exhaust pipeline caused by the vibration of the aviation piston engine; the outer diameter of the gradually expanding tube 5 gradually increases, which is convenient for the exhaust gas in the gradually expanding tube 5 to be discharged into the straight tube 7 and the gradually contracting tube 8, and the outer diameter of the gradually contracting tube 8 gradually decreases, which can form a transmitting wave, and utilizes the reflected wave to maintain the pressure in the gradually expanding tube 5, thereby sealing the air in the first cylinder of the aviation piston engine or the second cylinder of the aviation piston engine, reducing the loss of air entering the first cylinder of the aviation piston engine or the second cylinder of the aviation piston engine, and helping to improve the efficiency of the aviation piston engine.

[0048] In an optional embodiment of the present invention, the exhaust ends of the first exhaust manifold 1 and the second exhaust manifold 2 are at a preset angle, and the exhaust ends of the first exhaust manifold 1 and the second exhaust manifold 2 are formed with connecting pipes, which are connected to the intake end of the corrugated vibration damping pipe 3.

[0049] In this embodiment, the preset angle is 35° to 40°. By setting the exhaust ends of the first exhaust manifold 1 and the second exhaust manifold 2 at the preset angle, it is possible to ensure that the exhaust gas in the first cylinder of the aviation piston engine can smoothly pass through the first exhaust manifold 1 into the corrugated vibration damping pipe 3, and ensure that the exhaust gas in the second cylinder of the aviation piston engine can smoothly pass through the second exhaust manifold 2 into the corrugated vibration damping pipe 3, thereby reducing the impact resistance generated by the airflow in the first exhaust manifold 1 and the second exhaust manifold 2, which helps to ensure smooth exhaust.

[0050] In an optional embodiment of the present invention, the air inlet end of the corrugated vibration damping tube 3 is connected to the connecting pipe through a V-shaped clamp, and the air outlet end of the corrugated vibration damping tube 3 is connected to the air inlet end of the gradually expanding tube 5 through a V-shaped clamp.

[0051] In this embodiment, the connection between the corrugated vibration damping tube 3 and the connecting tube and the gradually expanding tube 5 is achieved by using a V-shaped clamp, which can ensure the stability and sealing of the connection; at the same time, it is convenient to disassemble, assemble and replace the corrugated vibration damping tube 3.

[0052] In an optional embodiment of the present invention, the lengths and outer diameters of the first exhaust manifold 1, the second exhaust manifold 2, the corrugated vibration damper pipe 3, the diverging pipe 5, the straight pipe 7, the converging pipe 8 and the exhaust tail pipe 9 are determined by a first formula.

[0053] In this embodiment, the outer diameter of the first exhaust manifold 1 and the second exhaust manifold 2 is preferably 60 mm, and the length of the first exhaust manifold 1 and the second exhaust manifold 2 is preferably 225 mm; the outer diameter of the corrugated vibration damping tube 3 is preferably 60 mm, and the length of the corrugated vibration damping tube 3 is preferably 50 mm; the outer diameter of the small diameter end of the gradually expanding tube 5 is preferably 60 mm, the outer diameter of the large diameter end of the gradually expanding tube 5 is preferably 128 mm, and the length of the gradually expanding tube 5 is preferably 525 mm; the outer diameter of the straight tube 7 is preferably 128 mm, and the length of the straight tube 7 is preferably 235 mm; the outer diameter of the small diameter end of the gradually reducing tube 8 is preferably 80 mm, the outer diameter of the large diameter end of the gradually reducing tube 8 is preferably 128 mm, and the length of the gradually expanding tube 5 is preferably 350 mm; the outer diameter of the exhaust tail pipe 9 is preferably 80 mm, and the length of the exhaust tail pipe 9 is preferably 100 mm;

[0054] Determine the length and outer diameter of the first exhaust manifold 1, the second exhaust manifold 2, the corrugated vibration damping pipe 3, the gradually expanding pipe 5, the straight pipe 7, the gradually contracting pipe 8 and the exhaust tail pipe 9 by the first formula;

[0055] The first formula is:

[0056]

[0057] Among them, D L Indicates the diameter of the resonant exhaust pipe at the length L; u L represents the air flow velocity at the length L of the resonant exhaust pipe; R1 represents the damping coefficient; ui P represents the air flow velocity at the length L of the resonant exhaust pipe; L Indicates the pressure at the length L of the resonant exhaust pipe; A L It represents the cross-sectional area at the length L of the resonant exhaust pipe;

[0058] L represents the length of a section of the resonance exhaust pipe; c represents the velocity of the pulse pressure wave; θ represents the exhaust angle of the exhaust port of a section of the resonance exhaust pipe; n represents the engine speed;

[0059] pass Determine the diameter of each section of the resonant exhaust pipe; by Determine the length of each section of the resonant exhaust pipe; wherein each section of the resonant exhaust pipe is a first exhaust manifold 1, a second exhaust manifold 2, a corrugated vibration damping pipe 3, a gradually expanding pipe 5, a straight pipe 7, a gradually contracting pipe 8 and an exhaust tail pipe 9;

[0060] The lengths and outer diameters of the first exhaust manifold 1, the second exhaust manifold 2, the corrugated vibration damping pipe 3, the gradually expanding pipe 5, the straight pipe 7, the gradually contracting pipe 8 and the exhaust tail pipe 9 are determined through the above process, which can ensure uniform exhaust of the two cylinders of the engine, effectively reduce exhaust resistance and improve engine power.

[0061] In an optional embodiment of the present invention, the extension directions of the first exhaust manifold 1, the second exhaust manifold 2, the corrugated vibration damping pipe 3, the diverging pipe 5, the straight pipe 7, the converging pipe 8 and the exhaust tail pipe 9 are determined according to the spatial layout of the aviation piston engine.

[0062] In this embodiment, the direction of the resonant exhaust pipe is based on the spatial arrangement of engine components. The engine dimensions are 550mm*579mm*580mm in length, width and height, and the engine resonant exhaust pipe does not exceed this dimension. At the same time, according to the engine mounting requirements, the resonant exhaust pipe is required to avoid the engine mounting bracket, and the resonant exhaust pipe is arranged in a disc shape.

[0063] Through the above process, the extension directions of the first exhaust manifold 1, the second exhaust manifold 2, the corrugated vibration damping tube 3, the gradually expanding tube 5, the straight tube 7, the gradually contracting tube 8 and the exhaust tail pipe 9 are determined, thereby determining the exhaust angle of the exhaust port of each section of the resonant exhaust pipe, thereby facilitating the determination of the length and diameter of each section of the resonant exhaust pipe, and achieving uniform exhaust of the two cylinders of the aviation piston engine, effectively reducing the exhaust resistance and improving the power of the aviation piston engine.

[0064] In an optional embodiment of the present invention, the aviation piston engine resonance exhaust pipe further comprises:

[0065] A first fixing frame 4 connected to the reducer 8;

[0066] A second fixing frame 6 connected to the straight pipe 7;

[0067] The first fixing frame 4 and the second fixing frame 6 are connected to the outer casing of the aviation piston engine.

[0068] In this embodiment, the connection between the tapered pipe 8 and the aviation piston engine is realized through the first fixing frame 4, and the connection between the straight pipe 7 and the aviation piston engine is realized through the second fixing frame 6, so that the stability of the overall resonance exhaust pipe can be ensured;

[0069] In this embodiment, during the specific connection, the parts where the first fixing bracket 4 and the second fixing bracket 6 are connected to the aviation piston engine casing are both provided with shock-absorbing pads.

[0070] In an optional embodiment of the present invention, the first fixing frame 4 includes:

[0071] An arc-shaped portion connected to the reducer 8;

[0072] A horizontal connection part is formed at both ends of the arc-shaped part, and a first connection hole is penetrated on the surface of the horizontal connection part.

[0073] In this embodiment, the arc portion is welded to the tapered tube 8. By setting the arc portion, the connection stability between the first fixing frame 4 and the tapered tube 8 can be improved; the horizontal connecting portion and the first connecting hole facilitate the connection between the first fixing frame 4 and the aviation piston engine casing.

[0074] In an optional embodiment of the present invention, the first connecting hole extends horizontally and passes through a side surface of the horizontal connecting portion.

[0075] In this embodiment, by making the first connection hole extend horizontally and penetrate the side surface of the horizontal connection portion, the connection operation between the first fixing frame 4 and the aviation piston engine casing can be further simplified.

[0076] In an optional embodiment of the present invention, the second fixing frame 6 is a plate-shaped structure, and a second connecting hole is provided through the surface of the second fixing frame 6 .

[0077] In this embodiment, the second fixing frame 6 is connected to the straight pipe 7 by welding, and the second fixing frame 6 with a plate-shaped structure and the second connecting hole facilitate the connection between the second fixing frame 6 and the aviation piston engine casing.

[0078] In an optional embodiment of the present invention, the cross-section of the second fixing frame 6 is a U-shaped structure.

[0079] In this embodiment, by making the cross section of the second fixing frame 6 a U-shaped structure, the strength of the second fixing frame 6 can be improved, thereby ensuring the stability of the entire resonance exhaust pipe.

[0080] The aviation piston engine resonance exhaust pipe provided by the above-mentioned embodiment of the present invention can achieve uniform exhaust of the two cylinders of the aviation piston engine through the first exhaust manifold 1, the second exhaust manifold 2, the corrugated vibration damping pipe 3, the gradually expanding pipe 5, the straight pipe 7, the gradually contracting pipe 8 and the exhaust tail pipe 9, effectively reducing the exhaust resistance and improving the power of the aviation piston engine; the corrugated vibration damping pipe 3 can play a position compensation and shock absorption effect, avoiding the vibration of the aviation piston engine causing vibration cracking and damage to the exhaust pipeline; by setting the exhaust ends of the first exhaust manifold 1 and the second exhaust manifold 2 to a preset angle, it can ensure that the exhaust gas in the first cylinder of the aviation piston engine can smoothly pass through the first exhaust manifold 1 to enter the corrugated vibration damping pipe 3, and ensure that the exhaust gas in the second cylinder of the aviation piston engine can smoothly pass through the second exhaust manifold 2 to enter the corrugated vibration damping pipe 3, thereby reducing the impact of the airflow in the first exhaust manifold 1 and the second exhaust manifold 2. resistance, which helps to ensure smooth exhaust; the connection between the bellows damper tube 3 and the connecting tube and the gradually expanding tube 5 is achieved through the V-shaped clamp, which can ensure the stability and sealing of the connection; at the same time, it is convenient to disassemble, assemble and replace the bellows damper tube 3; by determining the extension direction of the first exhaust manifold 1, the second exhaust manifold 2, the bellows damper tube 3, the gradually expanding tube 5, the straight tube 7, the gradually reducing tube 8 and the exhaust tail pipe 9, as well as the length and outer diameter of the first exhaust manifold 1, the second exhaust manifold 2, the bellows damper tube 3, the gradually expanding tube 5, the straight tube 7, the gradually reducing tube 8 and the exhaust tail pipe 9, it is possible to achieve uniform exhaust of the two cylinders of the aviation piston engine, effectively reduce the exhaust resistance, and improve the power of the aviation piston engine; the connection between the gradually reducing tube 8 and the aviation piston engine is achieved through the first fixing frame 4, and the connection between the straight tube 7 and the aviation piston engine is achieved through the second fixing frame 6, which can ensure the stability of the overall resonant exhaust pipe.

[0081] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A resonance exhaust pipe for an aviation piston engine, characterized in that: include: A first exhaust manifold (1) connected to the exhaust port of the first cylinder of the aviation piston engine; A second exhaust manifold (2) connected to the exhaust port of the second cylinder of the aviation piston engine; The exhaust ends of the first exhaust manifold (1) and the second exhaust manifold (2) are both connected to the intake end of the corrugated vibration damping pipe (3); The exhaust end of the corrugated vibration damping tube (3) is connected to the intake end of the gradually expanding tube (5); The exhaust end of the gradually expanding pipe (5) is connected to the intake end of the straight pipe (7); The exhaust end of the straight pipe (7) is connected to the intake end of the tapered pipe (8); The exhaust end of the reducer (8) is connected to the intake end of the exhaust tail pipe (9), and the exhaust end of the exhaust tail pipe (9) is connected to the intake end of the turbocharger.

2. The aviation piston engine resonance exhaust pipe according to claim 1, characterized in that: The exhaust ends of the first exhaust manifold (1) and the second exhaust manifold (2) are at a preset angle, and the exhaust ends of the first exhaust manifold (1) and the second exhaust manifold (2) are formed with connecting pipes, and the connecting pipes are connected to the intake end of the corrugated vibration damping pipe (3).

3. The aviation piston engine resonance exhaust pipe according to claim 2, characterized in that: The air inlet end of the corrugated vibration damping pipe (3) is connected to the connecting pipe via a V-shaped clamp, and the air outlet end of the corrugated vibration damping pipe (3) is connected to the air inlet end of the gradually expanding pipe (5) via a V-shaped clamp.

4. The aviation piston engine resonance exhaust pipe according to claim 1, characterized in that: The lengths and outer diameters of the first exhaust manifold (1), the second exhaust manifold (2), the corrugated vibration damping pipe (3), the gradually expanding pipe (5), the straight pipe (7), the gradually contracting pipe (8) and the exhaust tail pipe (9) are determined by a first formula.

5. The aviation piston engine resonance exhaust pipe according to claim 1, characterized in that: The extension directions of the first exhaust manifold (1), the second exhaust manifold (2), the corrugated vibration damping pipe (3), the gradually expanding pipe (5), the straight pipe (7), the gradually converging pipe (8) and the exhaust tail pipe (9) are determined according to the spatial layout of the aviation piston engine.

6. The aviation piston engine resonance exhaust pipe according to claim 1, characterized in that: Also includes: A first fixing frame (4) connected to the reducer (8); a second fixing frame (6) connected to the straight pipe (7); The first fixing frame (4) and the second fixing frame (6) are connected to the outer casing of the aviation piston engine.

7. The aviation piston engine resonance exhaust pipe according to claim 6, characterized in that: The first fixing frame (4) comprises: an arc-shaped portion connected to the reducer (8); A horizontal connecting portion is formed at both ends of the arc-shaped portion, and a first connecting hole is penetrated through the surface of the horizontal connecting portion.

8. The aviation piston engine resonance exhaust pipe according to claim 7, characterized in that: The first connection hole extends horizontally and passes through a side surface of the horizontal connection portion.

9. The aviation piston engine resonance exhaust pipe according to claim 6, characterized in that: The second fixing frame (6) is in a plate-shaped structure, and a second connection hole is provided through the surface of the second fixing frame (6).

10. The aviation piston engine resonance exhaust pipe according to claim 9, characterized in that: The cross section of the second fixing frame (6) is a U-shaped structure.

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