Throttle valve control mechanism of horizontally opposed aero-engine

Abstract

The utility model discloses a throttle valve control mechanism of a horizontally opposed aero-engine. The throttle valve control mechanism comprises a base, a vertical shaft, a T-shaped plate, a connecting rod, a reset torsion spring and a limiting screw, wherein the vertical shaft is vertically fixed on the base; the T-shaped plate is rotatably mounted on the vertical shaft, the T-shaped plate is provided with an operating arm and two rocker arms, and connecting rod connecting holes with the rotating axis of the T-shaped plate as the symmetric center are formed in the two rocker arms; the connecting rod is hinged between the connecting rod connecting hole and the throttle valve; the reset torsion spring is installed on the vertical shaft and used for providing reset torque for the T-shaped plate. The limiting screw is screwed to the base, and the head of the limiting screw abuts against the T-shaped plate and is used for adjusting the initial rotation angle of the T-shaped plate. According to the throttle valve control mechanism, a plurality of throttle valves can be opened synchronously, the opening degrees of the throttle valves are kept consistent, and it is guaranteed that the cylinders have approximately equal oil supply amount. The throttle valve control mechanism is simple in structure, easy to adjust and high in universality.

Description

Technical Field

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

[0002] Currently, piston aircraft engines mostly utilize a horizontally opposed multi-cylinder layout. Common horizontally opposed aircraft engines include opposed twin-cylinder, opposed quad-cylinder, opposed six-cylinder, and opposed eight-cylinder. Each cylinder in a multi-cylinder aircraft engine requires a carburetor or electronic fuel injector. Whether using a carburetor or electronic fuel injector, the throttle openings must be synchronized to ensure that each cylinder receives a roughly equal amount of fuel. Therefore, a throttle control mechanism is required to maintain consistent throttle openings. Utility Model Content

[0003] In order to overcome the deficiencies in the background technology, the utility model discloses a throttle control mechanism for a horizontally opposed aircraft engine, the purpose of which is to simplify the structure and keep the openings of the throttles consistent.

[0004] Specifically, the present invention adopts the following technical solutions:

[0005] A throttle control mechanism for a horizontally opposed aircraft engine, comprising:

[0006] base;

[0007] Vertical axis, fixed vertically on the base;

[0008] A T-shaped plate is rotatably mounted on the vertical shaft. The T-shaped plate has a control arm and two rocker arms. The two rocker arms are provided with connecting rod connection holes with the rotation axis of the T-shaped plate as the symmetrical center.

[0009] A connecting rod, hinged between the connecting rod connection hole and the throttle valve;

[0010] The reset torsion spring is installed on the vertical shaft and is used to provide reset torque for the T-plate;

[0011] The limit screw is screwed on the base, and its head is against the T-plate, and is used to adjust the initial rotation angle of the T-plate.

[0012] To further improve the technical solution, an anti-loosening compression spring is provided between the limit screw and the base.

[0013] To further improve the technical solution, a wire connection hole for connecting the tension wire is provided on the operating arm.

[0014] To further improve the technical solution, a sensor mounting seat is provided on the base, and the sensor mounting seat is used to install a temperature sensor.

[0015] To further improve the technical solution, the connecting rod is adjustable in length.

[0016] To further improve the technical solution, the connecting rod includes a rod, and hinge shafts are screwed at both ends of the rod.

[0017] After implementing the above technical solution, compared with the background technology, the beneficial effects produced by the present invention are:

[0018] The throttle operating mechanism can open multiple throttle valves synchronously and keep the opening of each throttle valve consistent, ensuring that each cylinder has a roughly equal amount of oil supply.

[0019] The throttle valve has a simple structure, is easy to adjust, and has strong versatility. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Attachment Figure 1 What is shown is the structural schematic diagram of this throttle operating mechanism.

[0021] Attachment Figure 2 Shown is the attached Figure 1 Exploded diagram.

[0022] Attachment Figure 3 Shown is a schematic structural diagram of a T-type plate.

[0023] Attachment Figure 4 Shown is a schematic diagram of the installation of the throttle control mechanism on an opposed twin-cylinder aircraft engine.

[0024] Attachment Figure 5 Shown is a schematic diagram of the installation of the throttle control mechanism on an opposed four-cylinder aircraft engine.

[0025] In the attached figure: 1. Base; 2. Vertical shaft; 3. T-plate; 31. Control arm; 32. Cable connection hole; 33. Rocker arm; 34. Connecting rod connection hole; 4. Reset torsion spring; 5. Connecting rod; 6. Washer; 7. L-shaped retaining ring; 8. Limit screw; 9. Anti-loosening compression spring; 10. Sensor mounting seat; 11. Throttle valve; 12. Linkage rod; 13. Tie wire. DETAILED DESCRIPTION

[0026] The following describes preferred embodiments of the present invention with reference to the accompanying drawings. Those skilled in the art should understand that these embodiments are merely intended to illustrate the technical principles of the present invention and are not intended to limit the scope of protection of the present invention. It should be noted that, in the description of the present invention, terms such as "front," "rear," "up," "down," "left," "right," "vertical," "horizontal," "inside," and "outside" indicating directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings. This is merely for ease of description and does not indicate or imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. It should also be noted that, in the description of the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can mean fixed, detachable, or integral; mechanical or electrical; direct, indirect through an intermediary, or internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0027] Refer to the attached Figure 1 and attached Figure 2 A throttle control mechanism for a horizontally opposed aircraft engine includes a base 1, a vertical shaft 2, a T-plate 3, a connecting rod 5, a return torsion spring 4, and a limit screw 8. The structure and function thereof are described in detail below.

[0028] The base 1 is a sheet metal part, including a bottom plate and a vertical plate. The bottom plate is provided with connection holes. The base 1 can be fixed on the casing of the aircraft engine through screws and the connection holes.

[0029] The vertical shaft 2 is vertically fixed on the bottom plate of the base 1. The vertical shaft 2 has a stepped structure with a larger bottom and a smaller top. An annular groove is provided on the upper half of the vertical shaft 2.

[0030] The T-shaped plate 3 is roughly T-shaped and is rotatably mounted on the vertical shaft 2. Specifically, the T-shaped plate 3 is sleeved on the upper half of the vertical shaft 2. Washers 6 are provided on the upper and lower surfaces of the T-shaped plate 3, and an L-shaped retaining ring 7 is clamped in the annular groove to limit the axial position of the T-shaped plate 3.

[0031] Refer to the attached Figure 3 The T-shaped plate 3 has a manipulation arm 31 and two rocker arms 33. The two rocker arms 33 are provided with connecting rod connection holes 34 with the rotation axis of the T-shaped plate 3 as the symmetry center. The manipulation arm 31 is provided with a wire connection hole 32 for connecting a reinforcement wire.

[0032] The connecting rod 5 is hinged between the connecting rod connecting hole 34 and the throttle valve 11. In the present embodiment, the connecting rod 5 comprises a rod, and a hinge shaft is screwed at both ends of the rod. Due to the screw connection structure, the connecting rod 5 is adjustable in length.

[0033] The reset torsion spring 4 is installed on the vertical shaft 2. One end of the reset torsion spring 4 is hooked on the bottom plate, and the other end is hooked on the T-shaped plate 3. The function of the reset torsion spring 4 is to provide a reset torque for the T-shaped plate 3.

[0034] Limit screw 8 is threaded onto the vertical plate of base 1, with its head resting on T-plate 3. This adjusts the initial rotation angle of T-plate 3, which determines the minimum opening angle of throttle valve 11 and the aircraft engine's idle speed. In other words, adjusting limit screw 8 can adjust the aircraft engine's idle speed. To prevent limit screw 8 from loosening, a compression spring 9 is interposed between limit screw 8 and base 1.

[0035] In order to facilitate the detection of the temperature of the aircraft engine, a sensor mounting seat 10 is provided on the base 1. The sensor mounting seat 10 is used to mount a temperature sensor. Integrating the sensor mounting seat 10 on the base 1 is conducive to improving the integration of the aircraft engine.

[0036] Refer to the attached Figure 4 For an opposed twin-cylinder aircraft engine, the throttle operating mechanism is fixed in the middle position of the two cylinders on the casing during assembly, and then the connecting rod 5 is hinged between the connecting rod connecting hole 34 and the throttle 11, and a tensioning wire 13 is installed in the tensioning wire connecting hole 32.

[0037] The speed of the aircraft engine is related to the opening of the throttle valve 11. During operation, pulling the tie wire 13 rotates the T-plate 3, which then drives the two throttle valves 11 to open synchronously through the two connecting rods 5. Because the length of the connecting rod 5 is adjustable, even if the openings of the two throttle valves 11 are inconsistent, the openings of the two throttle valves 11 can be kept consistent by adjusting the length of the connecting rod 5.

[0038] Refer to the attached Figure 5 For opposed four-cylinder aircraft engines, a linkage rod 12 can be used to connect the two throttle control mechanisms into one. In this way, pulling the tie wire 13 can cause the four throttle valves 11 to open synchronously, so that the opening degrees of the four throttle valves 11 remain consistent. Similarly, opposed six-cylinder and opposed eight-cylinder aircraft engines can also use a linkage rod 12 to connect multiple throttle control mechanisms into one.

[0039] As can be seen from the above, the throttle operating mechanism can open multiple throttle valves synchronously and keep the opening of each throttle valve consistent, ensuring that each cylinder has a roughly equal amount of fuel supply.

[0040] Parts not described in detail are prior art. 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 may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A throttle control mechanism for a horizontally opposed aircraft engine, characterized by: include: base; Vertical axis, fixed vertically on the base; A T-shaped plate is rotatably mounted on the vertical shaft. The T-shaped plate has a control arm and two rocker arms. The two rocker arms are provided with connecting rod connection holes with the rotation axis of the T-shaped plate as the symmetrical center. A connecting rod, hinged between the connecting rod connection hole and the throttle valve; The reset torsion spring is installed on the vertical shaft and is used to provide reset torque for the T-plate; The limit screw is screwed on the base, and its head is against the T-plate, and is used to adjust the initial rotation angle of the T-plate.

2. The throttle control mechanism for a horizontally opposed aircraft engine according to claim 1, wherein: An anti-loosening compression spring is arranged between the limit screw and the base.

3. The throttle control mechanism for a horizontally opposed aircraft engine according to claim 1, wherein: A tension wire connection hole for connecting a tension wire is provided on the operating arm.

4. The throttle control mechanism for a horizontally opposed aircraft engine according to claim 1, wherein: A sensor mounting seat is provided on the base, and the sensor mounting seat is used for mounting a temperature sensor.

5. The throttle control mechanism for a horizontally opposed aircraft engine according to claim 1, wherein: The connecting rod is adjustable in length.

6. The throttle control mechanism for a horizontally opposed aircraft engine according to claim 5, characterized in that: The connecting rod comprises a rod, and hinge shafts are screwed on both ends of the rod.

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