CN107061026B - A kind of helicopter accelerator linkage mechanism control method - Google Patents
A kind of helicopter accelerator linkage mechanism control method Download PDFInfo
- Publication number
- CN107061026B CN107061026B CN201611156467.0A CN201611156467A CN107061026B CN 107061026 B CN107061026 B CN 107061026B CN 201611156467 A CN201611156467 A CN 201611156467A CN 107061026 B CN107061026 B CN 107061026B
- Authority
- CN
- China
- Prior art keywords
- semaphore
- linkage mechanism
- signal
- accelerator linkage
- control signal
- Prior art date
- 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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Links
- 238000000034 method Methods 0.000 title claims abstract description 9
- 239000000523 sample Substances 0.000 claims abstract description 9
- 239000013642 negative control Substances 0.000 claims abstract description 4
- 239000013641 positive control Substances 0.000 claims abstract description 4
- 230000008450 motivation Effects 0.000 claims description 5
- 230000005764 inhibitory process Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D29/00—Controlling engines, such controlling being peculiar to the devices driven thereby, the devices being other than parts or accessories essential to engine operation, e.g. controlling of engines by signals external thereto
- F02D29/02—Controlling engines, such controlling being peculiar to the devices driven thereby, the devices being other than parts or accessories essential to engine operation, e.g. controlling of engines by signals external thereto peculiar to engines driving vehicles; peculiar to engines driving variable pitch propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/02—Circuit arrangements for generating control signals
- F02D41/14—Introducing closed-loop corrections
- F02D41/1401—Introducing closed-loop corrections characterised by the control or regulation method
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/02—Circuit arrangements for generating control signals
- F02D41/14—Introducing closed-loop corrections
- F02D41/1401—Introducing closed-loop corrections characterised by the control or regulation method
- F02D2041/1409—Introducing closed-loop corrections characterised by the control or regulation method using at least a proportional, integral or derivative controller
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D2200/00—Input parameters for engine control
- F02D2200/02—Input parameters for engine control the parameters being related to the engine
- F02D2200/10—Parameters related to the engine output, e.g. engine torque or engine speed
- F02D2200/101—Engine speed
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Throttle Valves Provided In The Intake System Or In The Exhaust System (AREA)
Abstract
The present invention relates to a kind of helicopter accelerator linkage mechanism control methods, including central controller MCU, accelerator linkage mechanism, engine speed sensor, rotor speed probe, pitch signal transducer and compensated torque controller；Step 1: central controller MCU receives rotating speed of target signal, and control signal is issued to accelerator linkage mechanism according to rotating speed of target signal；Step 2: pitch signal transducer acquires real-time pitch signal, compensated torque controller compares the semaphore of the semaphore at current time and last moment, if the semaphore at current time is greater than the semaphore of last moment, negative control signal is issued to accelerator linkage mechanism；If the semaphore at current time is less than the semaphore of last moment, positive control signal is issued to accelerator linkage mechanism；If the semaphore at current time is equal to the semaphore of last moment, control signal is not issued to accelerator linkage mechanism.The speed feedback for realizing rotor revolving speed by means of the present invention is control, improves the control accuracy of rotor revolving speed.
Description
Technical field
Helicopter engine control technology field
Background technique
Currently, there are no linkage mechanism, i.e., non-linkage control modes for the throttle of domestic helicopter.
Summary of the invention
The technical scheme is that
A kind of helicopter accelerator linkage mechanism control method, including central controller MCU, accelerator linkage mechanism, hair are provided
Motivation speed probe, rotor speed probe, pitch signal transducer and compensated torque controller；
Accelerator linkage mechanism is inputted with two path control signal；
Pitch signal transducer acquisition pitch position signal is simultaneously sent to compensated torque controller；Compensated torque controller energy
Enough variation tendencies according to pitch position signal, issue the control signal of accelerator linkage mechanism all the way；
Central controller MCU is PID controller；Central controller MCU, accelerator linkage mechanism, engine speed sensor
And rotor speed probe constitutes the PID control system of accelerator linkage mechanism；Central controller MCU issues another way door linkage
The control signal of mechanism；
Step 1: central controller MCU receives rotating speed of target signal, and according to rotating speed of target signal to accelerator linkage mechanism
Issue control signal；
Step 2: pitch signal transducer acquires real-time pitch signal, compensated torque controller is by the signal at current time
It measures and is compared with the semaphore of last moment, if the semaphore at current time is greater than the semaphore of last moment, to oil
Door linking mechanism issues negative control signal；If the semaphore at current time is less than the semaphore of last moment, join to throttle
Motivation structure issues positive control signal；If the semaphore at current time is equal to the semaphore of last moment, not to throttle linkage
Mechanism issues control signal.
Further, in step 2, current time semaphore and the difference of last moment semaphore are bigger, then issue control
The semaphore absolute value of signal is also bigger.
Technical effect
The linkage control of helicopter throttle is realized, and the control method can be realized excessive inhibition, so that control is more
Add reliable.The speed feedback for realizing rotor revolving speed by means of the present invention is control, improves the control essence of rotor revolving speed
Exactness.
Detailed description of the invention
Fig. 1 is the principle of the present invention figure.
Specific embodiment
A kind of helicopter accelerator linkage mechanism control method, including central controller MCU, accelerator linkage mechanism, hair are provided
Motivation speed probe, rotor speed probe, pitch signal transducer and compensated torque controller；
Accelerator linkage mechanism is inputted with two path control signal；
Pitch signal transducer acquisition pitch position signal is simultaneously sent to compensated torque controller；Compensated torque controller energy
Enough variation tendencies according to pitch position signal, issue the control signal of accelerator linkage mechanism all the way；
Central controller MCU is PID controller；Central controller MCU, accelerator linkage mechanism, engine speed sensor
And rotor speed probe constitutes the PID control system of accelerator linkage mechanism；Central controller MCU issues another way door linkage
The control signal of mechanism；
Step 1: central controller MCU receives rotating speed of target signal, and according to rotating speed of target signal to accelerator linkage mechanism
Issue control signal；
Step 2: pitch signal transducer acquires real-time pitch signal, compensated torque controller is by the signal at current time
It measures and is compared with the semaphore of last moment, if the semaphore at current time is greater than the semaphore of last moment, to oil
Door linking mechanism issues negative control signal；If the semaphore at current time is less than the semaphore of last moment, join to throttle
Motivation structure issues positive control signal；If the semaphore at current time is equal to the semaphore of last moment, not to throttle linkage
Mechanism issues control signal.
Further, in step 2, current time semaphore and the difference of last moment semaphore are bigger, then issue control
The semaphore absolute value of signal is also bigger.
Claims (2)
1. a kind of helicopter accelerator linkage mechanism control method, including central controller MCU, accelerator linkage mechanism, engine turn
Fast sensor, rotor speed probe, pitch signal transducer and compensated torque controller；
Accelerator linkage mechanism is inputted with two path control signal；
Pitch signal transducer acquisition pitch position signal is simultaneously sent to compensated torque controller；Compensated torque controller being capable of root
According to the variation tendency of pitch position signal, the control signal of accelerator linkage mechanism all the way is issued；
Central controller MCU is PID controller；Central controller MCU, accelerator linkage mechanism, engine speed sensor and
The PID control system of rotor speed probe composition accelerator linkage mechanism；Central controller MCU issues another way door linking mechanism
Control signal；
Step 1: central controller MCU receives rotating speed of target signal, and issued according to rotating speed of target signal to accelerator linkage mechanism
Control signal；
Step 2: pitch signal transducer acquires real-time pitch signal, compensated torque controller by the semaphore at current time with
The semaphore of last moment compares, if the semaphore at current time is greater than the semaphore of last moment, joins to throttle
Motivation structure issues negative control signal；If the semaphore at current time is less than the semaphore of last moment, to throttle linkage machine
Structure issues positive control signal；If the semaphore at current time is equal to the semaphore of last moment, not to accelerator linkage mechanism
Issue control signal.
2. a kind of helicopter accelerator linkage mechanism control method according to claim 1, it is characterised in that: in step 2,
Current time semaphore and the difference of last moment semaphore are bigger, then the semaphore absolute value for issuing control signal is also bigger.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611156467.0A CN107061026B (en) | 2016-12-14 | 2016-12-14 | A kind of helicopter accelerator linkage mechanism control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611156467.0A CN107061026B (en) | 2016-12-14 | 2016-12-14 | A kind of helicopter accelerator linkage mechanism control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107061026A CN107061026A (en) | 2017-08-18 |
| CN107061026B true CN107061026B (en) | 2019-10-18 |
Family
ID=59619061
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611156467.0A Active CN107061026B (en) | 2016-12-14 | 2016-12-14 | A kind of helicopter accelerator linkage mechanism control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107061026B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113669165B (en) * | 2020-05-15 | 2022-09-20 | 中航西飞民用飞机有限责任公司 | Turboprop aircraft automatic throttle instruction balancing method |
| CN114294115B (en) * | 2021-12-15 | 2023-03-14 | 中国航空工业集团公司成都飞机设计研究所 | Servo accelerator control method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0446897A (en) * | 1990-06-12 | 1992-02-17 | Yamaha Motor Co Ltd | Flight control for unmanned helicopter |
| JPH1193812A (en) * | 1997-09-25 | 1999-04-06 | Yamaha Motor Co Ltd | Engine starter of unmanned helicopter |
| CN1358650A (en) * | 2002-01-29 | 2002-07-17 | 北京航空航天大学 | Remote control system for axle-shared double-rotary wing pilotless helicopter |
| CN105620767A (en) * | 2014-10-28 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Method for using throttle lever for comprehensively controlling engine and propeller |
| CN105736156A (en) * | 2016-03-24 | 2016-07-06 | 深圳清华大学研究院 | Control method and control system of unmanned helicopter engine constant rotation speed |
| CN106005398A (en) * | 2016-05-20 | 2016-10-12 | 程靖 | Automatic matching control method for variable propeller pitch rotorcraft accelerator propeller pitch |
| CN205779276U (en) * | 2016-05-31 | 2016-12-07 | 西京学院 | A kind of depopulated helicopter engine control system |
-
2016
- 2016-12-14 CN CN201611156467.0A patent/CN107061026B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0446897A (en) * | 1990-06-12 | 1992-02-17 | Yamaha Motor Co Ltd | Flight control for unmanned helicopter |
| JPH1193812A (en) * | 1997-09-25 | 1999-04-06 | Yamaha Motor Co Ltd | Engine starter of unmanned helicopter |
| CN1358650A (en) * | 2002-01-29 | 2002-07-17 | 北京航空航天大学 | Remote control system for axle-shared double-rotary wing pilotless helicopter |
| CN105620767A (en) * | 2014-10-28 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Method for using throttle lever for comprehensively controlling engine and propeller |
| CN105736156A (en) * | 2016-03-24 | 2016-07-06 | 深圳清华大学研究院 | Control method and control system of unmanned helicopter engine constant rotation speed |
| CN106005398A (en) * | 2016-05-20 | 2016-10-12 | 程靖 | Automatic matching control method for variable propeller pitch rotorcraft accelerator propeller pitch |
| CN205779276U (en) * | 2016-05-31 | 2016-12-07 | 西京学院 | A kind of depopulated helicopter engine control system |
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| Publication number | Publication date |
|---|---|
| CN107061026A (en) | 2017-08-18 |
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