CN107061026A - A kind of helicopter accelerator linkage mechanism control method - Google Patents
A kind of helicopter accelerator linkage mechanism control method Download PDFInfo
- Publication number
- CN107061026A CN107061026A CN201611156467.0A CN201611156467A CN107061026A CN 107061026 A CN107061026 A CN 107061026A CN 201611156467 A CN201611156467 A CN 201611156467A CN 107061026 A CN107061026 A CN 107061026A
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 11
- 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
- 238000010586 diagram Methods 0.000 description 1
- 230000001629 suppression 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 method, 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 sent to accelerator linkage mechanism according to rotating speed of target signal；Step 2: pitch signal transducer gathers real-time pitch signal, compensated torque controller is contrasted the semaphore of the semaphore at current time and last moment, if the semaphore at current time is more than the semaphore of last moment, negative control signal is sent to accelerator linkage mechanism；If the semaphore at current time is less than the semaphore of last moment, positive control signal is sent to accelerator linkage mechanism；If the semaphore at current time is equal to the semaphore of last moment, control signal is not sent to accelerator linkage mechanism.By being control The inventive method achieves the speed feedback of rotor rotating speed, the control accuracy of rotor rotating speed is improved.
Description
Technical field
Helicopter engine control technology field
Background technology
At present, the throttle of domestic helicopter is also without link gear, i.e., non-coordinated signals mode.
The content 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 has two path control signal input；
Pitch signal transducer gathers pitch position signal and is sent to compensated torque controller；Compensated torque controller energy
Enough variation tendencies according to pitch position signal, send 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 sends another road 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
Send control signal；
Step 2: pitch signal transducer gathers real-time pitch signal, compensated torque controller is by the signal at current time
The semaphore measured with last moment is contrasted, if the semaphore at current time is more than the semaphore of last moment, to oil
Door linking mechanism sends negative control signal；If the semaphore at current time is less than the semaphore of last moment, join to throttle
Motivation structure sends positive control signal；If the semaphore at current time is equal to the semaphore of last moment, not to throttle linkage
Mechanism sends control signal.
Further, in step 2, the difference of current time semaphore and last moment semaphore is bigger, then sends control
The semaphore absolute value of signal is also bigger.
Technique effect
The coordinated signals of helicopter throttle are realized, and the control method can realize excessive suppression so that control is more
Plus it is reliable.By being control The inventive method achieves the speed feedback of rotor rotating speed, the control essence of rotor rotating speed is improved
Exactness.
Brief description of the drawings
Fig. 1 is schematic diagram of the invention.
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 has two path control signal input；
Pitch signal transducer gathers pitch position signal and is sent to compensated torque controller；Compensated torque controller energy
Enough variation tendencies according to pitch position signal, send 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 sends another road 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
Send control signal；
Step 2: pitch signal transducer gathers real-time pitch signal, compensated torque controller is by the signal at current time
The semaphore measured with last moment is contrasted, if the semaphore at current time is more than the semaphore of last moment, to oil
Door linking mechanism sends negative control signal；If the semaphore at current time is less than the semaphore of last moment, join to throttle
Motivation structure sends positive control signal；If the semaphore at current time is equal to the semaphore of last moment, not to throttle linkage
Mechanism sends control signal.
Further, in step 2, the difference of current time semaphore and last moment semaphore is bigger, then sends 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 has two path control signal input；
Pitch signal transducer gathers pitch position signal and is 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 sent；
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 sends another road door linking mechanism
Control signal；
Step 1: central controller MCU receives rotating speed of target signal, and sent according to rotating speed of target signal to accelerator linkage mechanism
Control signal；
Step 2: pitch signal transducer gathers real-time pitch signal, compensated torque controller by the semaphore at current time with
The semaphore of last moment is contrasted, if the semaphore at current time is more than the semaphore of last moment, is joined to throttle
Motivation structure sends negative control signal；If the semaphore at current time is less than the semaphore of last moment, to throttle linkage machine
Structure sends positive control signal；If the semaphore at current time is equal to the semaphore of last moment, not to accelerator linkage mechanism
Send control signal.
2. a kind of helicopter accelerator linkage mechanism control method according to claim 1, it is characterised in that：In step 2,
The difference of current time semaphore and last moment semaphore is bigger, then the semaphore absolute value for sending 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 true CN107061026A (en) | 2017-08-18 |
| CN107061026B 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) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113669165A (en) * | 2020-05-15 | 2021-11-19 | 中航西飞民用飞机有限责任公司 | Turboprop aircraft automatic throttle instruction balancing method |
| CN114294115A (en) * | 2021-12-15 | 2022-04-08 | 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 |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113669165A (en) * | 2020-05-15 | 2021-11-19 | 中航西飞民用飞机有限责任公司 | Turboprop aircraft automatic throttle instruction balancing method |
| CN114294115A (en) * | 2021-12-15 | 2022-04-08 | 中国航空工业集团公司成都飞机设计研究所 | Servo accelerator control 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107061026B (en) | 2019-10-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103231798B (en) | A kind of control method utilizing digitalized electric steering engine control device | |
| CN103303454B (en) | A kind of electric steering gear device based on speed ring commutation and control method thereof | |
| CN107061026A (en) | A kind of helicopter accelerator linkage mechanism control method | |
| ATE422071T1 (en) | CONTROLLER STRUCTURE WITH A TORSION MODEL | |
| CN103116367A (en) | Automatic control method and system for tail gate water level in river model | |
| CN103607149A (en) | Ultrasonic motor rudder servo system and control method thereof | |
| CN103935395A (en) | Method for self-adaptation frictional compensation of electric power steering system and electric power steering system | |
| CN102672926B (en) | Molten gel back pressure control system and method for electrically controlled injection molding machine | |
| CN202544835U (en) | Left-right limit control system for mast of rotary drilling rig | |
| CN203822450U (en) | Air intake electronic supercharger for automobile engine | |
| CN203485766U (en) | Combined type electronic throttle pedal for electro-hydraulic hybrid electric automobile | |
| CN103174524A (en) | Electronic throttle valve control system | |
| CN108081272A (en) | Based on monolithic processor controlled synchronous robot | |
| CN104270046A (en) | Motor control method based on self-learning of rotating speed-current two-dimensional fuzzy model | |
| CN103684147B (en) | DC generator speed Derivative Feedback controls apparatus and method | |
| CN203562983U (en) | Multi-motor synchronous control system | |
| CN104314795B (en) | Apparatus for controlling pump, constant pressure speed-regulating control device, method and the micropump, water pump | |
| CN203614235U (en) | Digital electronic governor | |
| CN101510746B (en) | Method for recognizing control object parameter based on DC motor speed control | |
| CN104314897B (en) | A kind of control device and control method for offshore spilled oil oil fence automatic distributing and discharging | |
| CN203957401U (en) | A kind of linkage hydraulic press synchronous control system | |
| CN204610042U (en) | Digitizing freq-variable electronic speed regulator | |
| CN202863758U (en) | Steering engine with angle information feedback function | |
| CN206520213U (en) | A kind of injection ratio control system of injection machine | |
| CN202427560U (en) | Constant differential rotation speed control system of centrifugal machine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |