Throttle valve control mechanism of aero-engine

Abstract

The throttle valve control mechanism of the aero-engine comprises a base, a fixing column is fixedly arranged in the center of the upper surface of the base, a step lining is fixedly arranged on the outer side of the fixing column, and a valve swing arm is rotationally arranged on the upper portion of the outer side of the step lining. A connecting rod hole connected with an external throttle valve connecting rod is formed in the upper surface of one end of the valve swing arm, a stay wire hole used for fixing a stay wire is formed in the upper surface of the other end of the valve swing arm, and a valve swing arm spring sleeves the outer side of the step bushing and is arranged between the base and the valve swing arm; the single-cylinder throttle valve control mechanism is suitable for single-cylinder throttle valve control used by light airplanes, small model airplanes, unmanned aerial vehicles and the like, the overall structure is simple, control is convenient, the overall manufacturing and maintenance cost of cylinders is reduced, response is rapid, and the throttle valve control mechanism is suitable for large-scale popularization and application. And the opening degree of the throttle valve is adjusted more quickly and accurately.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engines, in particular to a throttle operating mechanism of an aviation engine. Background Art

[0002] A piston aircraft engine generates power through the reciprocating motion of pistons within cylinders. Piston aircraft engines are often designed with horizontally opposed, multi-cylinder configurations. This layout is widely used in various aircraft types due to its advantages such as good balance and a low center of gravity. However, for light aircraft, small model aircraft, and drones, the continued use of a multi-cylinder design increases the overall weight of the aircraft, affecting its flight time and maneuverability. Furthermore, multi-cylinder engines are expensive to manufacture and maintain, and the throttle control structure of carburetors or electronic fuel injectors on multiple cylinders is more complex, making them unsuitable for light aircraft, small model aircraft, and drones. Therefore, we propose a throttle control mechanism for an aircraft engine. Utility Model Content

[0003] The technical problem to be solved by the present invention is to overcome the existing defects and provide a throttle control mechanism for an aircraft engine, which is suitable for single-cylinder throttle control used in light aircraft, small aircraft models, drones, etc. The overall structure is simple and the control is convenient, which reduces the overall manufacturing and maintenance costs of the cylinder, etc., and can effectively solve the problems in the background technology.

[0004] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a throttle control mechanism of an aircraft engine, comprising a base, a fixing column fixedly provided at the center of the upper surface of the base, a step bushing fixedly provided on the outer side of the fixing column, a valve swing arm rotatably provided on the upper outer side of the step bushing, a connecting rod hole connected to the external throttle connecting rod is provided on the upper surface of one end of the valve swing arm, a wire hole for fixing the wire is provided on the upper surface of the other end of the valve swing arm, a valve swing arm spring is sleeved on the outer side of the step bushing, and the valve swing arm spring is arranged between the base and the valve swing arm; a mounting seat is fixedly provided on the upper surface of the base near the wire hole, and a limiting rod for limiting the valve swing arm is provided on the mounting seat.

[0005] As a preferred technical solution of the present invention, mounting holes are provided at the four corners of the upper surface of the base except for the mounting seat.

[0006] As an optimal technical solution of the present invention, the upper surface of the valve rocker arm is provided with a rocker arm spring hole corresponding to the top end of the valve rocker arm spring, and the upper surface of the base is provided with a base spring hole corresponding to the bottom end of the valve rocker arm spring.

[0007] As a preferred technical solution of the present invention, an annular groove is provided on the outer surface of the top end of the fixing column, a retaining ring is clamped in the groove, and the retaining ring is arranged on the upper part of the valve swing arm.

[0008] As a preferred technical solution of the present invention, an upper washer is provided between the retaining ring and the valve swing arm.

[0009] As a preferred technical solution of the present invention, a lower washer is provided at the outer bottom of the fixing column, and the lower washer is provided between the step bushing and the base.

[0010] As a preferred technical solution of the present invention, a screw hole is provided on the upper surface of the mounting seat, and an external thread corresponding to the screw hole is provided on the lower outer surface of the limiting rod.

[0011] As a preferred technical solution of the present invention, the upper portion of the limiting rod is a frustum portion, and the diameter of the frustum portion decreases from top to bottom.

[0012] Compared with the existing technology, the beneficial effects of the utility model are: it is suitable for single-cylinder throttle control used in light aircraft, small aviation models, drones, etc., with a simple overall structure and convenient control, reducing the overall manufacturing and maintenance costs of the cylinder, and has a quick response, making it faster and more accurate to adjust the throttle opening. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a structural diagram of the utility model;

[0014] Figure 2 For this utility model Figure 1 Exploded diagram.

[0015] In the figure: 1 base, 2 mounting hole, 3 fixing column, 4 base spring hole, 5 valve rocker arm spring, 6 slot, 7 lower washer, 8 step bushing, 9 valve rocker arm, 10 upper washer, 11 retaining ring, 12 rocker arm spring hole, 13 connecting rod hole, 14 cable hole, 15 mounting seat, 16 limit rod. DETAILED DESCRIPTION

[0016] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described 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.

[0017] See also Figure 1-2The utility model provides a technical solution: a throttle control mechanism of an aircraft engine, comprising a base 1, a fixed column 3 is fixedly provided at the center of the upper surface of the base 1, a step bushing 8 is fixedly provided on the outer side of the fixed column 3, the upper outer diameter of the step bushing 8 is smaller than the lower outer diameter thereof, and a valve swing arm 9 in the shape of a compass mark is provided on the upper portion for rotation, a connecting rod hole 13 connected to an external throttle connecting rod is opened on the upper surface of one end of the valve swing arm 9, and the throttle connecting rod is respectively connected to the connecting rod hole 13 and the operating rod of the external throttle The working rod is hinged, and a wire hole 14 for fixing the wire is opened on the upper surface of the other end of the valve swing arm 9. When the throttle is operated, one end of the valve swing arm 9 is driven to move by the wire, so that the valve swing arm 9 rotates and the throttle connecting rod is driven to move at the same time, thereby adjusting the throttle opening. The overall structure is simple and easy to control. It is suitable for single-cylinder throttle control used in light aircraft, small aviation models, drones, etc., which reduces the overall manufacturing and maintenance costs of the cylinder, and has a quick response, and is faster and more accurate in adjusting the throttle opening.

[0018] The valve rocker arm spring 5 is sleeved on the outside of the step bushing 8, and the valve rocker arm spring 5 is arranged between the base 1 and the valve rocker arm 9. The upper and lower ends of the valve rocker arm spring 5 are provided with vertical bending parts. A rocker arm spring hole 12 corresponding to the top of the valve rocker arm spring 5 is opened on the upper surface of the valve rocker arm 9, and a base spring hole 4 corresponding to the bottom of the valve rocker arm spring 5 is opened on the upper surface of the base 1. The upper and lower bent ends of the valve rocker arm spring 5 are respectively fixed in the rocker arm spring hole 12 and the base spring hole 4, so that when the valve rocker arm 9 rotates, the valve rocker arm spring 5 is driven to deform, and a reset torque is provided for the valve rocker arm 9 when it is reset.

[0019] According to the preferred technical solution, a mounting seat 15 is fixedly provided on the upper surface of the base 1 near the wire hole 14 , and a limiting rod 16 for limiting the valve swing arm 9 is provided on the mounting seat 15 . The limiting rod 16 is used to limit the initial position of the valve swing arm 9 .

[0020] A further preferred technical solution is that a screw hole is provided on the upper surface of the mounting seat 15, and an external thread corresponding to the screw hole is provided on the lower outer surface of the limiting rod 16. The limiting rod 16 is installed in the screw hole of the mounting seat 15 through a threaded connection, which is convenient for disassembly, assembly, maintenance, replacement, etc.

[0021] Furthermore, the upper part of the limit rod 16 is a conical part, and the diameter of the conical part decreases from top to bottom. By rotating the limit rod 16 at different numbers of revolutions, the different positions of the conical part can be brought into contact with and limited by the valve rocker arm 9, that is, the initial position of the valve rocker arm 9 can be adjusted, and then the minimum opening angle of the external throttle and the idle speed of the aircraft engine can be adjusted, that is, the idle speed of the aircraft engine can be adjusted by adjusting the height of the limit rod 16, and the control is more convenient.

[0022] According to a preferred technical solution, mounting holes 2 are provided at the four corners of the upper surface of the base 1 except for the mounting seat 15 , that is, three mounting holes 2 are provided, and the base 1 can be fixed by bolts or the like.

[0023] According to a preferred technical solution, an annular groove 6 is provided on the outer surface of the top end of the fixing column 3, and a retaining ring 11 is clamped in the groove 6. The retaining ring 11 is arranged on the upper part of the valve swing arm 9, and the valve swing arm 9 is axially limited by the retaining ring 11.

[0024] According to the preferred technical solution, an upper gasket 10 is provided between the retaining ring 11 and the valve swing arm 9 to protect the retaining ring 11 and the valve swing arm 9; a lower gasket 7 is provided at the outer bottom of the fixed column 3, and the lower gasket 7 is provided between the step bushing 8 and the base 1 to protect the contact surface between the step bushing 8 and the base 1 to reduce wear.

[0025] The undisclosed parts of the present invention are all prior art, and their specific structures, materials and working principles will not be described in detail. Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A throttle control mechanism for an aircraft engine, comprising a base (1), characterized in that: A fixing column (3) is fixedly provided at the center of the upper surface of the base (1), a step bushing (8) is fixedly provided on the outer side of the fixing column (3), a valve swing arm (9) is rotatably provided on the upper outer side of the step bushing (8), a connecting rod hole (13) connected to an external throttle connecting rod is provided on the upper surface of one end of the valve swing arm (9), a wire hole (14) for fixing a wire is provided on the upper surface of the other end of the valve swing arm (9), a valve swing arm spring (5) is sleeved on the outer side of the step bushing (8), and the valve swing arm spring (5) is provided between the base (1) and the valve swing arm (9); a mounting seat (15) is fixedly provided on the upper surface of the base (1) near the wire hole (14), and a limiting rod (16) for limiting the valve swing arm (9) is provided on the mounting seat (15).

2. The throttle control mechanism of an aircraft engine according to claim 1, characterized in that: The four corners of the upper surface of the base (1) are all provided with mounting holes (2) except for the mounting seat (15).

3. The throttle control mechanism of an aircraft engine according to claim 1, characterized in that: The upper surface of the valve swing arm (9) is provided with a swing arm spring hole (12) corresponding to the top end of the valve swing arm spring (5), and the upper surface of the base (1) is provided with a base spring hole (4) corresponding to the bottom end of the valve swing arm spring (5).

4. The throttle control mechanism of an aircraft engine according to claim 1, characterized in that: An annular clamping groove (6) is provided on the outer surface of the top end of the fixing column (3), a retaining ring (11) is clamped in the clamping groove (6), and the retaining ring (11) is arranged on the upper part of the valve swing arm (9).

5. The throttle operating mechanism of an aircraft engine according to claim 4, characterized in that: An upper washer (10) is provided between the retaining ring (11) and the valve swing arm (9).

6. The throttle control mechanism of an aircraft engine according to claim 1, characterized in that: A lower washer (7) is provided at the outer bottom of the fixing column (3), and the lower washer (7) is provided between the step bushing (8) and the base (1).

7. The throttle operating mechanism of an aircraft engine according to claim 1, characterized in that: The upper surface of the mounting seat (15) is provided with a screw hole, and the lower outer surface of the limiting rod (16) is provided with an external thread corresponding to the screw hole.

8. The throttle operating mechanism of an aircraft engine according to claim 7, characterized in that: The upper portion of the limiting rod (16) is a frustum portion, and the diameter of the frustum portion decreases from top to bottom.

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