Aviation piston engine belt pulley fixing device

Abstract

The invention provides a belt pulley fixing device for an aviation piston engine. The belt pulley fixing device comprises a belt, a lower belt pulley, an upper support, a lower support, a shock pad and a tensioning executing mechanism. Wherein when the engine is in a non-working state, the belt is in a loose state, and power is cut off; when the engine is in a working state, the belt is in a tensioned state to realize power transmission; according to the invention, the engine can be reliably fixed on the helicopter, so that the engine can provide stable power output, and the output shaft of the engine can have a certain amount of vertical up-and-down displacement function.

Description

Technical Field

[0001] The present application belongs to the field of aviation power installation technology, and specifically relates to a pulley fixing device for an aviation piston engine. Background Art

[0002] The power output of helicopter piston engines in the form of pulleys must not only meet the requirements of strength, vibration isolation, and safe and reliable extraction of engine power.

[0003] At the same time, it is also necessary to realize that the engine output shaft can have a certain amount of vertical up and down displacement function to realize the transmission and disconnection of power to solve the problem of difficulty in starting the engine under load.

[0004] It is generally difficult to transmit and disconnect power in conventional installations. Summary of the invention

[0005] Purpose of the invention: In order to solve the problem of difficulty in starting an engine with load, a pulley fixing device for an aviation piston engine is proposed.

[0006] The present application provides a pulley fixing device for an aviation piston engine, the device comprising: a belt 1, a lower pulley 2, an upper bracket 3, a lower bracket 4, a shock absorbing pad 5 and a tensioning actuator 6;

[0007] Among them, when the engine is not in operation, the belt is in a relaxed state, thereby disconnecting the power; when the engine is in operation, the belt is in a tensioned state, thereby transmitting the power.

[0008] Preferably, when the engine is started, the tensioning actuator is in a contracted state so that the engine is in a non-tensioned state; when the engine is started to idle speed, the tensioning actuator is extended to achieve power transmission.

[0009] Preferably, the tensioning actuator comprises: a fixed end, actuating rod, an actuator, and a lower end engine fixing point.

[0010] Preferably, the engine fixing point at the lower end of the tensioning actuator is connected to the upper engine bracket, and the tensioning actuator drives the extension and contraction movement of the actuator-driven actuator rod to push the engine to rotate up and down around the rear mounting fulcrum of the engine to achieve vertical movement of the lower pulley installed on the engine.

[0011] Preferably, the upper support comprises: a main support, a screw rod, and a transverse connecting rod.

[0012] Preferably, the upper bracket is connected to the fuselage structure through a transverse link joint bearing, and the transverse link rotates around the joint bearing and compresses the shock-absorbing pad to achieve up and down displacement of the engine. At the same time, the screw and the transverse link prevent the engine from lateral displacement, and the shock-absorbing pad isolates the engine and the fuselage structure from vibration and impact.

[0013] Preferably, the lower bracket includes: a main bracket, a screw rod, and a transverse connecting rod.

[0014] Preferably, the lower bracket is connected to the fuselage structure through a transverse link joint bearing, and the transverse link rotates around the joint bearing and compresses the shock-absorbing pad to achieve up and down displacement of the engine. At the same time, the screw and the transverse link are used to prevent the engine from twisting, and the vibration and impact of the engine and the fuselage structure are isolated by the shock-absorbing pad.

[0015] This application has the following technical effects:

[0016] The present invention can reliably fix the engine on the helicopter, so that the engine can provide stable power output and can realize the function that the output shaft of the engine can have a certain amount of vertical up and down displacement. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural schematic diagram of a pulley fixing device for an aviation piston engine provided in an embodiment of the present application;

[0018] Figure 2 is a structural schematic diagram of a tensioning actuator provided in an embodiment of the present application;

[0019] Figure 3 is a structural schematic diagram of an upper bracket provided in an embodiment of the present application;

[0020] Figure 4 It is a structural schematic diagram of a lower bracket provided in an embodiment of the present application. DETAILED DESCRIPTION

[0021] See also Figure 1-Figure 4 The present application provides a lower pulley installation for a helicopter piston engine, comprising a belt 1, a lower pulley 2, an upper bracket 3, a lower bracket 4, a shock-absorbing pad 5 and a tensioning actuator 6.

[0022] The engine is not in operation (not tensioned) Figure 1 As shown by the dotted line, the belt 1 is in a relaxed state at this time, realizing the disconnection of power; the engine working state (tension state) is as shown in FIG. Figure 1 As shown by the solid line, the belt 1 is in a tensioned state at this time, realizing power transmission.

[0023] When starting the engine, the tensioning actuator 6 is in a contracted state so that the engine is in a non-tensioned state to solve the problem of difficulty in starting the engine with load. When the engine starts to idle, the tensioning actuator 6 is extended to achieve power transmission.

[0024] Among them, the engine fixing point 64 at the lower end of the tensioning actuator 6 is connected to the upper engine bracket 3. The tensioning actuator 6 drives the extension and contraction movement of the actuator rod 62 through the actuator 63 to push the engine to rotate up and down around the rear mounting fulcrum of the engine to realize the vertical movement of the lower pulley 2 installed on the engine.

[0025] Among them, the upper bracket 3 is connected to the fuselage structure through the transverse connecting rod 33 joint bearing, and the transverse connecting rod 33 rotates around the joint bearing and compresses the shock-absorbing pad 5 to realize the up and down displacement of the engine. At the same time, the screw 32 and the transverse connecting rod 33 are used to prevent the lateral displacement of the engine, and the vibration and impact of the engine and the fuselage structure are isolated by the shock-absorbing pad 5.

[0026] Among them, the lower bracket 4 is connected to the fuselage structure through the transverse connecting rod 43 joint bearing, and the transverse connecting rod 43 rotates around the joint bearing and compresses the shock-absorbing pad 5 to realize the up and down displacement of the engine. At the same time, the screw 42 and the transverse connecting rod 43 are used to prevent the engine from twisting, and the vibration and impact of the engine and the fuselage structure are isolated by the shock-absorbing pad 5.

[0027] Among them, see Figure 2 The tensioning actuator 6 includes: a fixed end 61, actuating rod 62, an actuator 63, and a lower engine fixing point 64.

[0028] In one possible implementation, see Figure 3 The upper support 3 includes: a main support 31, a screw rod 32, and a transverse connecting rod 33.

[0029] In one possible implementation, see Figure 4 The lower bracket 4 includes: a main bracket 41, a screw rod 42, and a transverse connecting rod 43.

[0030] The present invention can reliably fix the engine on the helicopter, so that the engine can provide stable power output and realize the function that the engine output shaft can have a certain amount of vertical displacement.

[0031] In other embodiments of the present application, a lower pulley installation of a helicopter piston engine is provided, including a belt 1, a lower pulley 2, an upper bracket 3, a lower bracket 4 and a shock-absorbing pad 5, so that the engine output shaft can have a certain amount of vertical up and down displacement function, thereby achieving power transmission and disconnection, so as to solve the problem of difficulty in starting the engine under load.

[0032] It should be noted that the engine can be reliably fixed on the helicopter by being composed of brackets and pulleys with different functions, and the engine output shaft can have a certain amount of vertical adjustment of the belt distance.

[0033] The present invention can reliably fix the engine on the helicopter, so that the engine can provide stable power output and can realize the function that the output shaft of the engine can have a certain amount of vertical up and down displacement.

[0034] In other embodiments of the present application, the present application provides an aviation piston engine pulley fixing device, which includes: a belt 1, a lower pulley 2, an upper bracket 3, a lower bracket 4, a shock-absorbing pad 5 and a tensioning actuator 6.

[0035] Among them, when the engine is not in operation, the belt is in a relaxed state, thereby disconnecting the power; when the engine is in operation, the belt is in a tensioned state, thereby transmitting the power.

[0036] When the engine is started, the tensioning actuator is in a contracted state so that the engine is in a non-tensioned state; when the engine starts to idle, the tensioning actuator is extended to achieve power transmission.

[0037] The tensioning actuator includes: a fixed end, a moving rod, an actuator, and a lower end engine fixing point.

[0038] Among them, the engine fixing point at the lower end of the tensioning actuator is connected to the upper engine bracket. The tensioning actuator drives the extension and contraction movement of the actuator-driven actuator rod to push the engine to rotate up and down around the rear mounting fulcrum of the engine to achieve vertical movement of the lower pulley installed on the engine.

[0039] The upper support includes: a main support, a screw rod, and a transverse connecting rod.

[0040] Among them, the upper bracket is connected to the fuselage structure through a transverse link joint bearing, and the engine is displaced up and down by the transverse link rotating around the joint bearing and compressing the shock-absorbing pad.

[0041] At the same time, screws and transverse connecting rods are used to prevent lateral displacement of the engine, and shock-absorbing pads are used to isolate the vibration and impact of the engine and fuselage structure.

[0042] Wherein, the lower support includes: a main support, a screw rod, and a transverse connecting rod.

[0043] Among them, the lower bracket is connected to the fuselage structure through a transverse link joint bearing, and the engine is able to move up and down by rotating the transverse link around the joint bearing and compressing the shock-absorbing pad.

[0044] At the same time, screws and transverse connecting rods are used to prevent the engine from twisting, and shock-absorbing pads are used to isolate the engine and fuselage structure from vibration and impact.

[0045] The present invention can reliably fix the engine on the helicopter, so that the engine can provide stable power output and can realize the function that the output shaft of the engine can have a certain amount of vertical up and down displacement.

[0046] In other embodiments of the present application, in order to solve the problem of difficulty in starting the engine under load, the present application provides a pulley fixing device for an aviation piston engine, the device comprising: a belt 1, a lower pulley 2, an upper bracket 3, a lower bracket 4, a shock absorbing pad 5 and a tensioning actuator 6.

[0047] The present invention can reliably fix the engine on the helicopter, so that the engine can provide stable power output and can realize the function that the output shaft of the engine can have a certain amount of vertical up and down displacement.

Claims

1. A pulley fixing device for an aviation piston engine, characterized in that: The device comprises: a belt (1), a lower pulley (2), an upper bracket (3), a lower bracket (4), a shock-absorbing pad (5) and a tensioning actuator (6); Among them, when the engine is not in operation, the belt is in a relaxed state, thereby disconnecting the power; when the engine is in operation, the belt is in a tensioned state, thereby transmitting the power.

2. The device according to claim 1, characterized in that When the engine is started, the tensioning actuator is in a contracted state so that the engine is in a non-tensioned state; when the engine starts to idle, the tensioning actuator is extended to achieve power transmission.

3. The device according to claim 2, characterized in that The tensioning actuator includes: a fixed end, a moving rod, an actuator, and a lower end engine fixing point.

4. The device according to claim 3, characterized in that The engine fixing point at the lower end of the tensioning actuator is connected to the upper bracket of the engine. The tensioning actuator drives the extension and contraction of the actuator rod to push the engine to rotate up and down around the rear mounting fulcrum of the engine to realize the vertical movement of the lower pulley installed on the engine.

5. The device according to claim 4, characterized in that The upper bracket includes: a main bracket, a screw rod, and a transverse connecting rod.

6. The device according to claim 5, characterized in that The upper bracket is connected to the fuselage structure through a transverse link joint bearing. The transverse link rotates around the joint bearing and compresses the shock-absorbing pad to achieve up and down displacement of the engine. At the same time, the screw and transverse link prevent the engine from lateral displacement, and the shock-absorbing pad isolates the engine and fuselage structure from vibration and impact.

7. The device according to claim 6, characterized in that The lower bracket includes: a main bracket, a screw rod, and a transverse connecting rod.

8. The device according to claim 7, characterized in that The lower bracket is connected to the fuselage structure through a transverse link joint bearing. The transverse link rotates around the joint bearing and compresses the shock-absorbing pad to achieve up and down displacement of the engine. At the same time, the screw and transverse link are used to prevent the engine from twisting, and the shock-absorbing pad is used to isolate the engine and fuselage structure from vibration and impact.

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