CN217501803U - Single-power-rod control mechanism - Google Patents
Single-power-rod control mechanism Download PDFInfo
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- CN217501803U CN217501803U CN202221806260.4U CN202221806260U CN217501803U CN 217501803 U CN217501803 U CN 217501803U CN 202221806260 U CN202221806260 U CN 202221806260U CN 217501803 U CN217501803 U CN 217501803U
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- rocker arm
- guide groove
- base
- guide
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Abstract
The application discloses single power lever control mechanism, including base, throttle control cable, speed regulator control cable, the control cam of area guide slot, install on the base with the control cam relatively fixed's control rocking arm and rotate the speed governing rocking arm of installing on the base. When the control rocker arm moves forwards and backwards, the throttle control cable is driven to control the opening of the throttle valve, the air inlet of the engine is adjusted, the power adjustment of the engine is realized, the speed regulator control cable is fixed at the moment, and when the control rocker arm moves to the cruising power or above, the speed regulation rocker arm can drive the speed regulator control cable to move, so that the tension adjustment of the propeller is realized. The pilot can realize the coordinated control of the single lever on the power of the aircraft and the propeller speed regulator according to the flight requirement of the aircraft, the number of cockpit handles is reduced, the workload of the pilot is lightened, and the whole mechanism is an integrated mechanical integrated structure, has no electrical equipment and has a reliable structure.
Description
Technical Field
The utility model relates to an aircraft power integrated control field especially relates to a single power pole control mechanism.
Background
The airplane power control technology not only has control requirements on an engine, but also comprises control on a propeller and a coordinated integration technology of engine control and propeller control. The existing aircraft engine technology is rapidly developed, most engines are provided with engine control units to realize the autonomous detection and control of the engines, and engine control mechanisms implemented on the aircraft only need to input power requirements to the engine control units, and control of mixing ratio, oil injection, ignition, exhaust and the like in the engines is not related, so that a cockpit only needs to output a single signal to the engine control units for the control of the engines. For piston propeller aircraft, aircraft power control may also involve changes in propeller pitch, with large pitches being required for maximum pull on the aircraft as it takes off, and automatic pitch adjustment of the propellers being required for cruise to achieve constant engine speed with varying pull. Engine control signals need to be fed back to an engine control unit, propeller control needs to be fed back to a propeller speed regulator, the two controls are generally controlled by two rods arranged in a cockpit respectively, a pilot needs to set a combination of engine power control and propeller pitch control according to different flight working conditions of the airplane, operation is inconvenient, and the pilot has a large workload.
SUMMERY OF THE UTILITY MODEL
The utility model provides a to above-mentioned problem, a single power lever control mechanism is proposed.
The utility model discloses the technical scheme who takes as follows:
the application provides a single power lever control mechanism, includes:
a base;
the control rocker arm is rotatably arranged on the base through a rotating shaft;
one end of the throttle control cable is arranged on the control rocker arm;
the control cam is relatively fixed with the control rocker arm and synchronously rotates along with the control rocker arm, the control cam is provided with a first guide groove and a second guide groove which are mutually connected, the first guide groove is arc-shaped, the distance between each point on the arc-shaped central line of the first guide groove and the axis of the rotating shaft is the same, and the distance between at least a plurality of points on the central line of the second guide groove and the axis of the rotating shaft is different;
the speed regulating rocker arm is rotatably arranged on the base;
the guide piece is arranged on the speed regulation rocker arm, is matched with the first guide groove and the second guide groove and can move along the first guide groove and the second guide groove, the speed regulation rocker arm is fixed relative to the base when the guide piece moves on the first guide groove, and the speed regulation rocker arm rotates relative to the base after the guide piece enters the second guide groove from the first guide groove;
and one end of the speed regulator control cable is arranged on the speed regulating rocker arm.
The control cam is connected and fixed with the control rocker arm, so that the control cam rotates along with the rotation of the control rocker arm, when the control rocker arm moves forwards and backwards, the control cable of the throttle valve is driven to control the opening of the throttle valve, the air inlet of an engine is adjusted, the power adjustment of the engine is realized, at the moment, the control cable of the speed regulator is fixed, and when the control rocker arm moves to the cruising power or above, the control cable of the speed regulator is driven by the speed regulation rocker arm to move, and the tension adjustment of the propeller is realized. The pilot can realize the coordinated control of the single lever on the aircraft power and the propeller speed regulator according to the flight requirements of the aircraft, the number of cockpit handles is reduced, the workload of the pilot is lightened, and the whole mechanism is an integrated mechanical integrated structure, has no electrical equipment and is reliable in structure.
When the control cam is actually used, the track size and the inflection point position of the first guide groove and the second guide groove of the control cam are set according to the power of an engine and a speed regulator.
The center line of the guide groove refers to the center line of the guide groove on the symmetrical plane symmetrical to the upper surface and the lower surface of the control cam, and the distances from the center line to the groove wall of the guide groove are equal.
In practical application, the control rocker arm and the control cam can be fixed through a fastener, and can also be welded and fixed or formed through machining in an integrated machine.
Further, the speed regulation rocker arm is provided with a first part and a second part, the guide piece is arranged at the joint of the first part and the second part, one end, far away from the guide piece, of the first part is rotatably installed on the base, and the speed regulator control cable is connected with one end, far away from the guide piece, of the second part.
Furthermore, the speed regulating rocker arm is L-shaped or V-shaped.
When the speed regulating rocker is actually used, the size and the shape of the speed regulating rocker are matched with those of the control cam and the guide groove.
Furthermore, the two speed regulation rocker arms are respectively arranged on two sides of the control cam.
The two speed regulating rocker arms enable the mechanism to move more stably and reliably.
Further, the guide piece includes the axle and installs the abrasionproof piece on the axle, the axle is used for passing first guide slot and second guide slot, the abrasionproof piece is located between control cam and the speed governing rocking arm.
The abrasion-proof piece can relieve the friction between the guide piece and the control cam and between the speed regulation rocker arm and the control cam, and the service life of the mechanism is prolonged.
The throttle valve control cable is sleeved on one sleeve in a sliding manner, and the speed regulator control cable is sleeved on the other sleeve in a sliding manner.
The supporting frame enables the speed regulator control cable and the throttle valve control cable to be fixed relative to the base in the vertical direction, and the sleeve enables the speed regulator control cable and the throttle valve control cable to move back and forth along the horizontal direction to control the propeller speed regulator and the engine, so that the whole structure is more reliable, and the movement is more stable.
Furthermore, the end parts of the throttle control cable and the speed regulator control cable are respectively provided with a connector, the throttle control cable is hinged on the control rocker arm through the connector, and the speed regulator control cable is hinged on the speed regulation rocker arm through the connector.
When the speed regulating rocker arm drives the speed regulator control cable and the control rocker arm drives the throttle valve control cable to move, the hinged design enables the movement to be more stable.
Furthermore, the device also comprises a handle fixed on the control rocker arm.
The handle is used for holding and operating the control rocker arm, the design of the handle is in line with human engineering, and the connecting part of the handle and the control rocker arm is arranged according to the requirement, can be arranged at the top end of the control rocker arm and can also be arranged at the side part of the control rocker arm.
Furthermore, the handle is provided with a control button.
The control button is a shortcut key of a certain function.
Further, the base has a cam hole for providing a space for the control cam to rotate.
The utility model has the advantages that:
the control cam is connected and fixed with the control rocker arm, so that the control cam rotates along with the rotation of the control rocker arm, when the control rocker arm moves forwards and backwards, the control cable of the throttle valve is driven to control the opening of the throttle valve, the air inlet of an engine is adjusted, the power of the engine is adjusted, at the moment, the control cable of the speed regulator is fixed, and when the control rocker arm moves to the cruising power or above, the control cable of the speed regulator is driven by the speed regulation rocker arm to move, and the tension adjustment of the propeller is realized. The pilot can realize the coordinated control of the single lever on the aircraft power and the propeller speed regulator according to the flight requirements of the aircraft, the number of cockpit handles is reduced, the workload of the pilot is lightened, and the whole mechanism is an integrated mechanical integrated structure, has no electrical equipment and is reliable in structure.
Drawings
FIG. 1 is a schematic diagram of a single power lever control mechanism;
figure 2 is an isometric view of the base;
FIG. 3 is a front view of the control cam;
FIG. 4 is a front view of the timing rocker arm.
The figures are numbered:
1. a base; 2. a control cam; 3. a control rocker arm; 4. a connector; 5. a handle; 6. a throttle control cable; 7. a governor control cable; 8. a sleeve; 9. a support frame; 10. a limiting member; 11. a speed regulating rocker arm; 12. a guide; 13. an anti-wear member; 14. a first guide groove; 15. a second guide groove; 16. a joint; 17. a second portion; 18. a cam hole; 19. a lug portion; 20. mounting holes; 21. a first portion.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1-4, the present application provides a single power lever control mechanism, comprising:
a base 1;
the control rocker arm 3 is rotatably arranged on the base 1 through a rotating shaft;
one end of a throttle control cable 6 is arranged on the control rocker arm 3;
the control cam 2 (as shown in fig. 3) is fixed relative to the control rocker arm 3 and synchronously rotates along with the control rocker arm 3, the control cam 2 is provided with a first guide groove 14 and a second guide groove 15 which are connected with each other, the first guide groove 14 is arc-shaped, the distance between each point on the arc-shaped central line of the first guide groove 14 and the axis of the rotating shaft is the same, and the distance between at least a plurality of points on the central line of the second guide groove 15 and the axis of the rotating shaft is different;
the speed regulating rocker arm 11 is rotatably arranged on the base 1;
the guide piece 12 is arranged on the speed regulation rocker arm 11, the guide piece 12 is matched with the first guide groove 14 and the second guide groove 15 and can move along the first guide groove 14 and the second guide groove 15, when the guide piece 12 moves on the first guide groove 14, the speed regulation rocker arm 11 is fixed relative to the base 1, and after the guide piece 12 enters the second guide groove 15 from the first guide groove 14, the speed regulation rocker arm 11 rotates relative to the base 1;
one end of the speed regulator control cable 7 is arranged on the speed regulating rocker arm 11.
The control cam 2 and the control rocker arm 3 are connected and fixed, so that the control cam 2 rotates along with the rotation of the control rocker arm 3, when the control rocker arm 3 moves forwards and backwards, the throttle control cable 6 is driven to control the throttle opening, the air inlet of an engine is adjusted, the power of the engine is adjusted, and when the guide piece 12 moves on the first guide groove 14 and does not enter the second guide groove 14, the speed regulator control cable 7 is not moved. When the control rocker arm 3 moves to enable the guide piece 12 to be located at the joint of the first guide groove and the second guide groove, the airplane is at or above cruising power, the speed regulation rocker arm 11 is further controlled to rotate to drive the guide piece 12 to enter the second guide groove, the speed regulation rocker arm rotates at the moment, and then the speed regulator control cable 7 is driven to move, and propeller tension regulation is achieved. The pilot can realize the coordinated control of the single lever on the aircraft power and the propeller speed regulator according to the flight requirements of the aircraft, the number of cockpit handles 5 is reduced, the workload of the pilot is lightened, and the whole mechanism is an integrated mechanical integrated structure without electrical equipment and has a reliable structure.
In actual use, the sizes of the trajectories and the inflection positions of the first guide groove 14 and the second guide groove 15 of the control cam 2 are set according to the engine power and the governor.
The center line of the guide groove refers to the center line of the guide groove on the symmetrical plane symmetrical to the upper and lower surfaces of the control cam 2, and the distances from the center line to the groove wall of the guide groove are equal.
In this embodiment, the control rocker arm 3 and the control cam 2 are fixed by fasteners, and during actual use, the control rocker arm and the control cam can be welded and fixed or formed by machining in an integrated machine.
As shown in fig. 4, in the present embodiment, the governor rocker 11 has a first portion 21 and a second portion 17, the guide member 12 is disposed at the junction 16 of the first portion 21 and the second portion 17, one end of the first portion 21 remote from the guide member 12 is rotatably mounted on the base 1, and the governor control cable 7 is connected to one end of the second portion 17 remote from the guide member 12.
In this embodiment, the governor rocker 11 is L-shaped.
In actual use, the governor rocker 11 may be V-shaped, and the size and shape of the governor rocker 11 are coordinated with the size and shape of the control cam 2 and the guide groove.
In this embodiment, there are two timing rocker arms 11, which are respectively disposed on two sides of the control cam 2, and the two timing rocker arms 11 make the mechanism move more stably and reliably.
In practical use, only one speed regulating rocker arm 11 can be installed on the premise of ensuring stable and effective movement.
In this embodiment, the guide 12 comprises a shaft for passing through the first and second guide slots 14, 15 and a wear member 13 mounted on the shaft, the wear member 13 being located between the control cam 2 and the governor rocker 11.
The abrasion-proof piece 13 can relieve the friction between the guide piece 12 and the control cam 2 and between the speed regulation rocker arm 11 and the control cam 2, and the service life of the mechanism is prolonged.
In practical application, the wear-resistant layer can be coated on the surface layers of the speed regulating rocker arm 11, the control cam 2 and the shaft to achieve the purpose of wear resistance.
In this embodiment, the device further comprises a support frame 9 and two sleeves 8, wherein the support frame 9 is fixedly connected with the base 1, the sleeves 8 are fixed on the support frame 9, the throttle control cable 6 is slidably sleeved on one sleeve 8, and the governor control cable 7 is slidably sleeved on the other sleeve 8.
The supporting frame 9 enables the speed regulator control cables 7 and the throttle valve control cables 6 to be fixed relative to the base 1 in the vertical direction, and the sleeve 8 enables the speed regulator control cables 7 and the throttle valve control cables 6 to move back and forth along the horizontal direction to control the propeller speed regulator and the engine, so that the whole structure is more reliable, and the movement is more stable.
In other embodiments, the support frame 9 and the sleeve 8 may be arranged on the airframe to reduce the mass of the airframe.
In the embodiment, the end parts of the throttle control cable 6 and the speed regulator control cable 7 are respectively provided with a connector 4, the throttle control cable 6 is hinged on the control rocker arm 3 through the connector 4, and the speed regulator control cable 7 is hinged on the speed regulation rocker arm 11 through the connector 4.
When the speed regulating rocker arm 11 drives the speed regulator control cable 7 and the control rocker arm 3 drives the throttle control cable 6 to move, the hinged design ensures stable movement.
In this embodiment, a handle 5 is also included, which is fixed to the control rocker 3.
The handle 5 is used for holding and operating the control rocker 3, and is externally designed according to human engineering, and the connecting part of the handle 5 and the control rocker 3 is arranged as required, can be arranged at the top end of the control rocker 3, and can also be arranged at the side part of the control rocker 3.
In this embodiment, handle 5 and 3 joints of control rocking arm are installed at the top of control rocking arm 3, and convenient dismantlement of joint, maintenance and change.
In actual use, the handle 5 and the control rocker arm 3 can be welded or integrally formed as required.
In this embodiment, the handle 5 has at least one control button thereon. The control buttons may be shortcut keys for a certain function.
In the embodiment shown in fig. 2, the base 1 has a cam hole 18, and the cam hole 18 is used to provide a space for the control cam 2 to rotate, and in practical use, it may be in other forms, such as a groove structure, which can provide a space for the control cam 2 to rotate.
As shown in fig. 2, in the present embodiment, the base 1 has a plurality of lug parts 19 and mounting holes 20, and the lug parts 19 are used for mounting the control rocker 3, the governor rocker 11 and the support frame 9; the mounting hole 20 is used for mounting the entire single power control lever mechanism on the airplane body, and may be welded during actual use.
In this embodiment, a limiting member 10 is used to limit the position of one end of the hinged rotating shaft, so that the mechanism operates more reliably. In the embodiment, the position-limiting element 10 is a cotter pin.
Claims (10)
1. A single power lever control mechanism, comprising:
a base;
the control rocker is rotatably arranged on the base through a rotating shaft;
one end of the throttle control cable is arranged on the control rocker arm;
the control cam is relatively fixed with the control rocker arm and synchronously rotates along with the control rocker arm, the control cam is provided with a first guide groove and a second guide groove which are mutually connected, the first guide groove is arc-shaped, the distance between each point on the arc-shaped center line of the first guide groove and the axis of the rotating shaft is the same, and the distance between at least a plurality of points on the center line of the second guide groove and the axis of the rotating shaft is different;
the speed regulating rocker arm is rotatably arranged on the base;
the guide piece is arranged on the speed regulation rocker arm, is matched with the first guide groove and the second guide groove and can move along the first guide groove and the second guide groove, the speed regulation rocker arm is fixed relative to the base when the guide piece moves on the first guide groove, and the speed regulation rocker arm rotates relative to the base after the guide piece enters the second guide groove from the first guide groove;
and one end of the speed regulator control cable is arranged on the speed regulating rocker arm.
2. The single power lever control mechanism of claim 1, wherein the governor rocker arm has a first portion and a second portion, the guide is disposed at an intersection of the first portion and the second portion, an end of the first portion distal from the guide is pivotally mounted to the base, and the governor control cable is connected to an end of the second portion distal from the guide.
3. The single power lever control mechanism of claim 2, wherein the timing rocker arm is L-shaped or V-shaped.
4. The single power lever control mechanism of claim 2, wherein two of the governor rocker arms are disposed on either side of the control cam.
5. The single power lever control mechanism of claim 4, wherein the guide member comprises a shaft for passing through the first and second guide slots and a wear member mounted on the shaft between the control cam and the speed rocker arm.
6. The single power lever control mechanism of claim 1, further comprising a support bracket fixedly attached to the base and two bushings fixed to the support bracket, the throttle control cable being slidably received in one of the bushings and the governor control cable being slidably received in the other of the bushings.
7. The single power lever control mechanism of claim 6, wherein the ends of the throttle control cable and the governor control cable are each provided with a connector, the throttle control cable is hinged to the control rocker arm via the connector, and the governor control cable is hinged to the governor rocker arm via the connector.
8. The single power lever control mechanism of claim 1, further comprising a handle secured to the control rocker arm.
9. The single power lever control mechanism of claim 8, wherein the handle has a control button thereon.
10. The single power lever control mechanism of claim 1, wherein the base has a cam hole for providing space for the control cam to rotate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221806260.4U CN217501803U (en) | 2022-07-13 | 2022-07-13 | Single-power-rod control mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221806260.4U CN217501803U (en) | 2022-07-13 | 2022-07-13 | Single-power-rod control mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217501803U true CN217501803U (en) | 2022-09-27 |
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ID=83343384
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221806260.4U Active CN217501803U (en) | 2022-07-13 | 2022-07-13 | Single-power-rod control mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217501803U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115180124A (en) * | 2022-07-13 | 2022-10-14 | 浙江中航通飞研究院有限公司 | Single power rod control mechanism and aircraft |
-
2022
- 2022-07-13 CN CN202221806260.4U patent/CN217501803U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115180124A (en) * | 2022-07-13 | 2022-10-14 | 浙江中航通飞研究院有限公司 | Single power rod control mechanism and aircraft |
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