CN113756961A - Starting control method and system for universal aircraft engine starting integrated motor - Google Patents
Starting control method and system for universal aircraft engine starting integrated motor Download PDFInfo
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- CN113756961A CN113756961A CN202111088396.6A CN202111088396A CN113756961A CN 113756961 A CN113756961 A CN 113756961A CN 202111088396 A CN202111088396 A CN 202111088396A CN 113756961 A CN113756961 A CN 113756961A
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- 238000000034 method Methods 0.000 title claims abstract description 34
- 230000006835 compression Effects 0.000 claims abstract description 33
- 238000007906 compression Methods 0.000 claims abstract description 33
- 238000001514 detection method Methods 0.000 claims description 5
- 239000007858 starting material Substances 0.000 claims description 2
- 230000000977 initiatory effect Effects 0.000 claims 1
- 230000002349 favourable effect Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
- F02C7/275—Mechanical drives
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/34—Turning or inching gear
- F01D25/36—Turning or inching gear using electric motors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
Abstract
The invention discloses a starting control method and a system of a general aero-engine starting integrated motor, wherein the starting control method comprises the steps of firstly controlling a motor to reversely rotate to drive the motor to enable an engine to be positioned at a top dead center of a compression stroke but not to step beyond the top dead center of the compression stroke, so that compression resilience force is formed; and then the motor is controlled to drive the engine to rotate forwards, the compression resilience force formed by the engine during reverse rotation driving can be utilized to push the engine and the longest stroke of forward rotation driving in the forward rotation driving process to drive the engine to rotate forwards, the engine is favorable to step over the first forward rotation compression top dead center, and therefore the purpose of improving the starting success rate of starting the all-in-one motor is achieved.
Description
Technical Field
The invention relates to a starting control method and a starting control system for a universal aircraft engine starting integrated motor.
Background
The starting of the current navigation internal combustion engine is mainly divided into two starting modes:
1. starting a starting motor: as shown in fig. 1, the battery controls the start relay through the start switch to drive the start motor (dc brush motor), further driving the transmission gear set, and driving the motor to start the engine. There are currently two ways to start up:
(1) the motor is not separated from the engine after starting, so that the weight of the whole motor is heavy, the mechanical abrasion is large during starting, the starting noise is large, the starting motor is a brush motor, and the service life is short.
(2) The starting is carried out on the ground, and the engine is separated after the starting, so that the starting is very inconvenient, and the engine cannot be restarted after the air fault occurs. Meanwhile, the mechanical wear is large during starting, the starting noise is large, the starting motor is a brush motor, and the service life is short.
2. Starting the inspiration integrated control: as shown in fig. 2, the motor is a brushless motor, and the motor can generate power and start. On the basis of the motor, the wire diameter is increased, the size of the stator is increased, and high-performance magnetic steel and the like are used. The motor is required to output a certain torque to drive the engine to a certain rotating speed.
The method can cancel a starting relay, start a motor and a transmission gear to realize weight reduction, but because the application scene is a general aviation engine, the general aviation engine undergoes two strokes of air suction compression-power application and exhaust in one revolution, the speed change is large in one revolution, the characteristic of the engine is not utilized to control the motor when a direct current brushless motor control strategy is used, the starting success rate of the scheme is low at present, and smooth starting is difficult.
Disclosure of Invention
The invention aims to provide a starting control method and a starting control system for a universal starting integrated motor of an aircraft engine, and aims to solve the problem that the starting success rate of the existing starting integrated motor is low.
In order to solve the technical problem, the invention provides a starting control method of a universal aircraft engine starting integrated motor, which comprises the following steps: the motor is driven to rotate reversely, and when the motor drives the engine to enable the engine to be located at the top dead center of the compression stroke, the rotation direction of the motor is switched to enable the motor to drive forwards, and the engine is started. The motor is controlled to rotate reversely to drive the motor, so that the engine is positioned at the top dead center of a compression stroke but cannot move past the top dead center of the compression stroke, and compression resilience force is formed; and then the motor is controlled to drive the engine to rotate forwards, and the compression resilience force formed by the engine during reverse rotation driving can be utilized to push the engine and the longest stroke of forward rotation driving in the forward rotation driving process to drive the engine to rotate forwards, so that the first forward rotation compression top dead center is favorably stepped, and the starting success rate of the starting integrated motor is improved.
Further, when the motor is driven in the forward direction, whether the rotating speed of the motor is greater than a preset threshold value is judged; if yes, the motor is controlled to be switched from the 120-degree driving mode to the 180-degree driving mode. In the process of forward rotation driving, when the rotating speed is higher than a certain rotating speed (three-three conduction rotating speed), the 120-degree phase change driving is quickly switched to 180-degree phase change driving, so that torque pulsation can be reduced to a certain extent, the current waveform is approximate to a sine wave, and the first forward rotation compression top dead center is more favorably stepped during starting.
Further, when the motor is driven to rotate reversely, the driving PWM duty ratio of the motor is calculated according to the target current by using a PI algorithm. The target current is used for PI operation to control PWM output, so that the phenomenon that the motor shakes too much due to overlarge initial change rate of the current can be avoided.
Further, the method for determining that the engine is at the top dead center of the compression stroke comprises the following steps: and (3) carrying out Hall detection in the process of the reverse rotation of the motor, and judging that the engine is positioned at the top dead center of the compression stroke when detecting that the current Hall value HALL (n) is equal to the second Hall value HALL (n-2) before. The progress of the motor can be accurately positioned by adopting the Hall element, and the accurate reversing driving is ensured to realize the maximum torque.
In addition, the invention also provides a starting control system of the universal aircraft engine starting integrated motor, which comprises a motor stroke positioning unit and a starting controller; the motor stroke positioning unit is used for acquiring motor stroke positioning information; the starting controller is used for acquiring the motor stroke positioning information detected by the motor stroke positioning unit and then controlling the motor to start the engine according to the starting control method of the general aero-engine starting integrated motor. In the starting process, the motor is controlled to be driven reversely through the starting controller, and then the rotating direction of the motor is switched according to the motor stroke positioning information.
Further, the motor stroke positioning unit comprises a Hall element which is respectively connected with the motor and the starting controller. The Hall element has high detection precision which is better than 1% in a working temperature area, and has small volume, light weight and long service life.
The invention has the beneficial effects that: the motor is controlled to rotate reversely to drive the motor, so that the engine is positioned at the top dead center of a compression stroke but cannot move past the top dead center of the compression stroke, and compression resilience force is formed; and then the motor is controlled to drive the engine to rotate forwards, the compression resilience force formed by the engine during reverse rotation driving can be utilized to push the engine and the longest stroke of forward rotation driving in the forward rotation driving process to drive the engine to rotate forwards, the engine is favorable to step over the first forward rotation compression top dead center, and therefore the purpose of improving the starting success rate of starting the all-in-one motor is achieved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
FIG. 1 is a starting schematic diagram of a starter motor for a navigable internal combustion engine;
FIG. 2 is a schematic diagram of a heuristic integrated control start of a navigable internal combustion engine;
FIG. 3 is a flowchart of a starting control method of a general aero-engine starting integrated motor;
FIG. 4 is a schematic diagram of a starting control system of a general aircraft engine starting integrated motor.
Fig. 5 is a schematic diagram of the control of forward and reverse rotation of the motor according to one embodiment of the present invention.
Fig. 6 is a schematic diagram of a hall sensing scheme in accordance with one embodiment of the present invention.
Detailed Description
The starting control method of the general aero-engine starting integrated motor shown in fig. 3 comprises the following steps: the motor is driven to rotate reversely, the motor is driven reversely, when the motor drives the engine to enable the engine to be located at the top dead center of a compression stroke, the rotating direction of the motor is switched to enable the motor to drive forwards, when the rotating speed of the engine is increased to the ignition rotating speed, the ignition is successful, and the starting is completed. The motor is controlled to rotate reversely to drive the motor, so that the engine is positioned at the top dead center of a compression stroke but cannot step over the top dead center of the compression stroke, and compression resilience force is formed; and then the motor is controlled to drive the engine to rotate forwards, and the compression resilience force formed by the engine during reverse rotation driving can be utilized to push the engine and the longest stroke (1 rotation of 96 Hall commutations) of forward rotation driving in the forward rotation driving process to drive the engine to rotate forwards, so that the first forward rotation compression top dead center is favorably stepped, and the starting success rate of the starting integrated motor is improved. And when the rotating speed is increased to the ignition rotating speed subsequently, the ignition is successful, and the starting is finished.
According to one embodiment of the application, when the motor is driven in the forward direction, whether the rotating speed of the motor is greater than a preset threshold value is judged; if yes, the motor is controlled to be switched from the 120-degree driving mode to the 180-degree driving mode. In the forward rotation driving process, when the rotation speed is greater than a certain rotation speed (three-three conduction rotation speed), the 120-degree phase change driving is rapidly switched to 180-degree phase change driving, so that the torque pulsation can be reduced to a certain extent, the current waveform is approximate to a sine wave, and the first forward rotation compression top dead center is more favorably stepped during starting, as shown in fig. 6.
According to one embodiment of the application, during the reverse rotation process of the driving motor, the driving PWM duty ratio of the motor is calculated according to the target current by using a PI algorithm. The target current is used for PI operation to control PWM output, so that the phenomenon that the motor shakes too much due to overlarge initial change rate of the current can be avoided.
According to one embodiment of the application, the method for determining that the engine is at the top dead center of the compression stroke comprises the following steps: and (3) performing Hall detection in the process of the reverse rotation of the motor, as shown in FIG. 5, when detecting that the current Hall value HALL (n) is equal to the second Hall value HALL (n-2) before, determining that the engine is positioned at the top dead center of a compression stroke to form compression rebound, and switching to forward rotation driving at the moment.
The progress of the motor can be accurately positioned by adopting the Hall element, and the accurate reversing driving is ensured to realize the maximum torque.
The starting control system of the general aero-engine starting integrated motor shown in FIG. 4 comprises a motor stroke positioning unit and a starting controller; the motor stroke positioning unit is used for acquiring motor stroke positioning information; the starting controller is used for acquiring the motor stroke positioning information detected by the motor stroke positioning unit and then controlling the motor to start the engine according to the starting control method of the general aero-engine starting integrated motor. In the starting process, the motor is controlled to be driven reversely through the starting controller, and then the rotating direction of the motor is switched according to the motor stroke positioning information.
According to one embodiment of the application, the motor stroke positioning unit comprises a hall element connected with the motor and the start controller respectively. The Hall element has high detection precision which is better than 1% in a working temperature area, and has small volume, light weight and long service life.
The control method can be beneficial to the lightweight design of the control system and the reduction of the weight of the whole machine; the compression resilience force formed by the engine during reverse rotation driving is utilized to push the longest stroke of forward rotation driving to drive forward rotation, the success rate of starting the product is improved by adjusting the driving strategy of the motor, and the product can be started again when the product breaks down in the air.
Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.
Claims (6)
1. A starting control method of a general aviation engine starting integrated motor is characterized by comprising the steps of driving the motor to rotate reversely, switching the rotation direction of the motor when the motor drives the engine to enable the engine to be located at the top dead center of a compression stroke, enabling the motor to drive positively, and starting the engine.
2. The starting control method of the general aero-engine starter motor according to claim 1, wherein when the motor is driven in a forward direction, whether the rotating speed of the motor is greater than a preset threshold value is judged; if yes, the motor is controlled to be switched from the 120-degree driving mode to the 180-degree driving mode.
3. The starting control method of the general aero-engine starting integrated motor according to claim 1 or 2, wherein a driving PWM duty ratio of the motor is calculated according to a target current by using a PI algorithm in a reverse rotation process of the driving motor.
4. The method for controlling the starting of the general aero-engine starting integrated motor according to claim 1 or 2, wherein the method for determining that the engine is at the top dead center of the compression stroke comprises the following steps: and (3) carrying out Hall detection in the process of the reverse rotation of the motor, and judging that the engine is positioned at the top dead center of the compression stroke when detecting that the current Hall value HALL (n) is equal to the second Hall value HALL (n-2).
5. The utility model provides a general aeroengine starts control system of integrative motor of initiating which characterized in that includes:
the motor stroke positioning unit is used for acquiring motor stroke positioning information;
a start controller for acquiring the motor stroke positioning information detected by the motor stroke positioning unit and then controlling the motor to start the engine according to the start control method of any one of claims 1 to 4.
6. The start control system for the general aero-engine starting integrated motor according to claim 5, wherein the motor stroke positioning unit comprises a hall element connected to the motor and the start controller, respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111088396.6A CN113756961A (en) | 2021-09-16 | 2021-09-16 | Starting control method and system for universal aircraft engine starting integrated motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111088396.6A CN113756961A (en) | 2021-09-16 | 2021-09-16 | Starting control method and system for universal aircraft engine starting integrated motor |
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| Publication Number | Publication Date |
|---|---|
| CN113756961A true CN113756961A (en) | 2021-12-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111088396.6A Pending CN113756961A (en) | 2021-09-16 | 2021-09-16 | Starting control method and system for universal aircraft engine starting integrated motor |
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Citations (7)
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|---|---|---|---|---|
| WO2002027182A1 (en) * | 2000-09-28 | 2002-04-04 | Mitsuba Corporation | Engine starter |
| CN1459560A (en) * | 2002-05-22 | 2003-12-03 | 本田技研工业株式会社 | Engine starter |
| CN1466658A (en) * | 2000-09-28 | 2004-01-07 | 株式会社美姿把 | Engine starter |
| CN102045014A (en) * | 2010-11-29 | 2011-05-04 | 辽宁工业大学 | Brushless DC motor controller for four-wheel independently driven electric automobile and control method thereof |
| CN108386289A (en) * | 2017-11-15 | 2018-08-10 | 佛山市洛克威特科技有限公司 | A kind of engine ignitor |
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| CN110425071A (en) * | 2019-07-19 | 2019-11-08 | 重庆巩诚投资有限公司 | Engine start control method |
-
2021
- 2021-09-16 CN CN202111088396.6A patent/CN113756961A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2002027182A1 (en) * | 2000-09-28 | 2002-04-04 | Mitsuba Corporation | Engine starter |
| CN1466658A (en) * | 2000-09-28 | 2004-01-07 | 株式会社美姿把 | Engine starter |
| CN1459560A (en) * | 2002-05-22 | 2003-12-03 | 本田技研工业株式会社 | Engine starter |
| CN102045014A (en) * | 2010-11-29 | 2011-05-04 | 辽宁工业大学 | Brushless DC motor controller for four-wheel independently driven electric automobile and control method thereof |
| CN108386289A (en) * | 2017-11-15 | 2018-08-10 | 佛山市洛克威特科技有限公司 | A kind of engine ignitor |
| CN110277879A (en) * | 2019-06-14 | 2019-09-24 | 重庆巩诚投资有限公司 | The measuring system of engine crankshaft position |
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Application publication date: 20211207 |