CN109372641B - Light aircraft engine control mechanism - Google Patents
Light aircraft engine control mechanism Download PDFInfo
- Publication number
- CN109372641B CN109372641B CN201811511236.6A CN201811511236A CN109372641B CN 109372641 B CN109372641 B CN 109372641B CN 201811511236 A CN201811511236 A CN 201811511236A CN 109372641 B CN109372641 B CN 109372641B
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- China
- Prior art keywords
- control lever
- choke valve
- control
- steel cable
- mounting support
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D11/00—Arrangements for, or adaptations to, non-automatic engine control initiation means, e.g. operator initiated
- F02D11/04—Arrangements for, or adaptations to, non-automatic engine control initiation means, e.g. operator initiated characterised by mechanical control linkages
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D9/00—Controlling engines by throttling air or fuel-and-air induction conduits or exhaust conduits
- F02D9/08—Throttle valves specially adapted therefor; Arrangements of such valves in conduits
Abstract
The invention belongs to the general airplane power control technology, and particularly relates to a light airplane engine control mechanism. The light aircraft engine operating mechanism comprises an accelerator control rod handle, a choke valve control rod handle, an accelerator control rod, a choke valve control rod, an installation support and a steel cable. The throttle control lever handle and the choke valve control lever handle are respectively arranged at the operating ends of the throttle control lever and the choke valve control lever. The mounting support is arranged on the mounting support, the middle of the accelerator control rod penetrates through the mounting support, the lower end of the accelerator control rod is connected with the steel cable, and the steel cable penetrates through a through hole in the lower portion of the mounting support to serve as the accelerator control steel cable. The middle part of the choke valve control rod is rotationally fixed on the side surface of the mounting bracket, the lower end of the choke valve control rod is connected with another steel cable, and the steel cable penetrates through a through hole in the upper part of the mounting support to be the choke valve control steel cable. The light aircraft engine control mechanism is convenient to use, good in hand feeling, accurate in control, attractive and elegant in appearance and has a large practical application value.
Description
Technical Field
The invention belongs to the general airplane power control technology, and particularly relates to a light airplane engine control mechanism.
Background
The light-duty general aircraft generally adopts piston engine, and piston engine need control throttle and choke valve respectively, and general piston engine adopts the axial straight line push-and-pull control structure commonly used to throttle and choke valve's control, and the shortcoming that this axial straight line push-and-pull control structure exists is: the appearance is simple and crude, the grade is not displayed, the use is inconvenient, and the control is not accurate.
Disclosure of Invention
The purpose of the invention is: the light aircraft engine control mechanism solves the problem that the travel of the control lever is limited, is convenient to use and has high control precision.
The technical scheme of the invention is as follows: the utility model provides a light aircraft engine operating mechanism, its includes throttle control lever handle 14, choke control lever handle 15, throttle control lever 13, choke control lever 1, erection support 8, installing support 9, cable wire 6, wherein, throttle control lever handle 14, choke control lever handle 15 set up respectively at throttle control lever 13, 1 operation end of choke control lever, installing support 9 sets up on erection support 8, 13 middle parts of throttle control lever pass installing support 9, and the lower extreme is connected with cable wire 6, and this cable wire passes 8 lower part through-holes of installing support and is the throttle control cable wire, 1 middle part rotation of choke control lever is fixed in installing support 9 side, and the lower extreme is connected with another cable wire 6, and this cable wire 6 passes 8 upper portion through-holes of installing support and is the choke control cable wire.
The throttle control lever 13 is connected with a pair of inner rotating bases 11, an outer rotating base 12 and a porous fixing plate 10, and is fixed on the control handle mounting bracket 9 through a screw, wherein the outer rotating base 12 and the porous fixing plate 10 are respectively arranged on the outer side and the inner side of the pair of inner rotating bases 11.
The choke valve control rod 1 is sleeved with a choke valve rod locking fixing disc 2, a wave ball screw 5 is screwed into a rotary supporting cylinder, and the choke valve control rod is connected with an operating handle mounting bracket 9 through the rotary supporting cylinder.
The steel cable 6 passes through an anti-wear sleeve stopper 7 arranged at a through hole of the mounting support 8 to realize fixation, and the head part of the steel cable is fixed on the plastic lantern ring 4 and is respectively fastened and connected on the throttle control lever 13 and the choke control lever 1 through bolts.
The wear sleeve stopper 7 is mounted in the through hole of the mounting support 8 by means of a nut.
The mounting support 8 is fixed to the central console of the aircraft.
The invention has the beneficial effects that: the control device of the invention arranges the rotation point in the middle of the control lever, and the control steel cable is arranged at the bottom of the control lever, thereby solving the design limitation of the control lever rotation stroke in the airplane design, having convenient use and good hand feeling, realizing more accurate control on the accelerator and the choke valve of the light airplane engine, having beautiful and elegant appearance, good driving experience and great economic benefit.
Drawings
FIG. 1 is a schematic structural view of a light aircraft engine control mechanism of the present invention;
figure 2 is an exploded view of the light aircraft engine handling mechanism of the present invention,
the anti-abrasion device comprises a choke valve control rod 1, a locking fixed disk 2, a plastic lantern ring 4, a ball screw 5, a steel cable 6, an anti-abrasion retainer 7, an installation support 8, an installation support 9, an installation support 10, a porous fixed plate 11, an inner rotating base 11, an outer rotating base 12, an accelerator control rod 13, an accelerator control rod handle 14 and an accelerator control rod handle 15.
Detailed Description
The present invention will be described in further detail with reference to examples, but the embodiments of the present invention are not limited thereto.
Referring to fig. 1 and 2, the light aircraft engine operating mechanism of the present invention includes a choke valve control lever 1, a locking fixing disk 2, a plastic collar 4, a wave ball screw 5, a steel cable 6, an anti-wear stopper 7, a mounting support 8, a mounting bracket 9, a porous fixing plate 10, an inner rotating base 11, an outer rotating base 12, an accelerator control lever 13, an accelerator control lever handle 14, and a choke valve control lever handle 15. The steel cable 6 is divided into an accelerator control steel cable and a choke valve control steel cable according to different connecting positions and functional functions. The throttle control lever handle 14 is arranged at the upper end of the throttle control lever 13, the middle part of the throttle control lever 13 is fixed on the operating handle mounting bracket and arranged at the upper end, the throttle control lever 13 is fixed on the operating handle mounting bracket 9 through a screw rod, and the throttle control cable connected with the lower part of the throttle control lever is driven to reciprocate through pushing and pulling the throttle control lever 13, so that the handle realizes the fixation of any rotation point in a friction mode. The choke valve control rod handle 15 is also arranged at the upper end of the choke valve control rod 1, the choke valve rod locking fixing disc 2 is sleeved on the choke valve control rod 1, and the wave ball screw 5 is screwed into the support cylinder. The choke valve control rod 1 is pushed and pulled to drive the choke valve connected with the lower part of the choke valve rod to control the steel cable to reciprocate, and the handle realizes multi-rotation-point fixation by additionally installing a wave ball screw.
The upper parts of the throttle control lever and the choke valve control lever are symmetrically designed, the appearance is attractive and elegant, the middle-lower part control handle penetrates through the control handle mounting support and is provided with a limiting groove, the length of the lower part of the throttle control lever is different from that of the lower part of the choke valve control lever, and synchronous control of the throttle control steel cable and the choke valve control steel cable in different strokes is achieved.
The friction mode of throttle control lever realizes the fixed of arbitrary rotation point, and it installs internal rotation base 11 (hard polyvinyl chloride) additional in throttle control lever both sides, installs outer rotating base 12 (metal) and porous fixed plate toward the outer layer additional again, and porous fixed plate and control handle installing support pass through bolt-up connection, through 16 adjustment frictional force sizes of self-locking nut, realize locking torque's adjustment.
The choke valve control rod is uniformly provided with limiting holes through the wave bead screws arranged on the handle locking fixing disc and the circular arcs on the control handle mounting bracket, when the handle rod is rotated back and forth to be pushed and pulled, the wave bead of the wave bead screws is stretched and matched with the circular arc uniform holes to fix multiple rotating points, and the self-locking nuts are used for adjusting the locking torque.
The choke valve control rod and the control handle mounting bracket are fixed in a way that: it is through the embedded choke valve control lever of choke valve pole rotation support section of thick bamboo to when supporting a section of thick bamboo embedding, toward extending 0.5mm outward, when making the choke valve control lever rotatory, do not have the tight friction of clamp, promote rotatory feeling, its connected mode makes choke valve control lever and control handle installing support fastening connection through the bolt.
The accelerator control steel cable and the choke valve control steel cable are fixedly installed in a mode that: the heads of the accelerator control steel cable and the choke valve control steel cable are respectively fixed on an accelerator control rod and a choke valve control rod through plastic lantern rings, and the heads of the accelerator control steel cable and the choke valve control steel cable pass through an operating handle mounting support provided with an anti-abrasion sleeve stopper to realize mounting and fixing.
The mounting support 8 is used for mounting the whole engine control mechanism and is fixed on a central control console of the airplane, the control steel cables of an engine throttle and a choke valve are mounted on the throttle control lever and the choke valve control lever, and the throttle control lever and the choke valve control lever can rotate around a fixed screw in the middle of the throttle control lever and control the steel cables to realize reciprocating push-pull movement. The adjustment accessible locking screw of throttle lever locking force adjusts, because the throttle lever is arranged in the rotating base of hard polyvinyl chloride structure for its frictional force distributes evenly, can stop in the optional position during rotation operation, and feels better, and the choke valve then adjusts through adjustment ripples pearl screw, because ripples pearl screw, ripples pearl stroke is great, therefore its live time is of a specified duration, before the ripples pearl mill damages, need not adjust, the bad back of wearing and tearing, then directly more changes new ripples pearl screw. The invention is different from the common axial linear push-pull control mechanism, the main mechanism is in an important control console, only the upper part of the control handle is exposed in the cabin so as to be convenient for control, the space utilization rate is high, the appearance is small and exquisite and beautiful, the grade is more obvious, the use is convenient, and the control is more accurate.
In one embodiment, the light aircraft engine control mechanism is implemented in an AG50 light sports aircraft, is installed in a central console of the aircraft, and forms an engine control system together with a control cable lock sleeve and a cable branching device, so that the engine control system can accurately control an engine throttle and a choke valve and has good hand feeling.
In conclusion, the light aircraft engine control mechanism is a light aircraft engine throttle and choke valve control mechanism which is convenient to use, good in hand feeling and more accurate in control, attractive and elegant in appearance and has a large practical application value.
Claims (5)
1. A light aircraft engine control mechanism is characterized by comprising an accelerator control lever handle (14), a choke valve control lever handle (15), an accelerator control lever (13), a choke valve control lever (1), a mounting support (8), a mounting support (9) and a steel cable (6), wherein the accelerator control lever handle (14) and the choke valve control lever handle (15) are respectively arranged at the operating ends of the accelerator control lever (13) and the choke valve control lever (1), the mounting support (9) is arranged on the mounting support (8), the middle part of the accelerator control lever (13) penetrates through the mounting support (9), the lower end of the accelerator control lever (13) is connected with the steel cable (6), the steel cable penetrates through a through hole at the lower part of the mounting support (8) to form the accelerator control steel cable, the middle part of the choke valve control lever (1) is rotatably fixed on the side surface of the mounting support (9), and the lower end of the choke control lever is connected, the steel cable (6) passes through a through hole at the upper part of the mounting support (8) to be a choke valve control steel cable;
the throttle control lever (13) is connected with four parts including the pair of inner rotating bases (11), the outer rotating base (12) and the porous fixing plate (10) and is fixed on the control handle mounting bracket (9) through a screw rod, wherein the outer rotating base (12) and the porous fixing plate (10) are respectively arranged on the outer side and the inner side of the pair of inner rotating bases (11).
2. The light aircraft engine control mechanism according to claim 1, characterized in that a choke rod locking fixing disc (2) is sleeved on the choke control rod (1), a wave ball screw (5) is screwed into a rotary supporting cylinder, and the choke control rod is connected with the control handle mounting bracket (9) through the rotary supporting cylinder.
3. A light aircraft engine operating mechanism according to claim 1, characterized in that the cable (6) is secured through a wear sleeve retainer (7) mounted in a through hole in the mounting bracket (8) and its head is secured to a plastic collar (4) and is bolted to the throttle lever (13) and the choke lever (1), respectively.
4. A light aircraft engine operating mechanism according to claim 3 characterised in that the wear sleeve retainer (7) is mounted in a through-bore in the mounting bracket (8) by means of a nut.
5. A light aircraft engine handling mechanism according to claim 1 characterised in that the mounting bracket (8) is fixed to the centre console of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811511236.6A CN109372641B (en) | 2018-12-11 | 2018-12-11 | Light aircraft engine control mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811511236.6A CN109372641B (en) | 2018-12-11 | 2018-12-11 | Light aircraft engine control mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109372641A CN109372641A (en) | 2019-02-22 |
| CN109372641B true CN109372641B (en) | 2020-09-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811511236.6A Active CN109372641B (en) | 2018-12-11 | 2018-12-11 | Light aircraft engine control mechanism |
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| Country | Link |
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| CN (1) | CN109372641B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112173135B (en) * | 2020-09-25 | 2023-04-11 | 中国直升机设计研究所 | Linear thickening steel cable control structure and control method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH057481Y2 (en) * | 1987-12-15 | 1993-02-25 | ||
| US5305729A (en) * | 1992-02-14 | 1994-04-26 | Chiuminatta Edward R | Method and apparatus for cutting wet concrete |
| JP3864027B2 (en) * | 2000-02-10 | 2006-12-27 | 株式会社共立 | Intake control mechanism |
| US6798160B2 (en) * | 2001-11-02 | 2004-09-28 | Honda Giken Kogyo Kabushiki Kaisha | Electric working machine |
| CN205779273U (en) * | 2016-04-29 | 2016-12-07 | 隆鑫通用动力股份有限公司 | Engine governed speed package base |
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| Publication number | Publication date |
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| CN109372641A (en) | 2019-02-22 |
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