CN102923116A - Electromechanical brake driver of aircraft - Google Patents
Electromechanical brake driver of aircraft Download PDFInfo
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- CN102923116A CN102923116A CN2012104703613A CN201210470361A CN102923116A CN 102923116 A CN102923116 A CN 102923116A CN 2012104703613 A CN2012104703613 A CN 2012104703613A CN 201210470361 A CN201210470361 A CN 201210470361A CN 102923116 A CN102923116 A CN 102923116A
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Abstract
The invention provides an electromechanical brake driver of an aircraft. A power supply part supplies power to a force sensor, a position sensor, a control circuit and a driving circuit in an isolated way; and the control circuit receives an instruction brake force signal, a force feedback signal of the force sensor and a motor rotor position signal transmitted from the position sensor and outputs 6-path PWM signals to the driving circuit, so as to achieve substantial rotation and over-current protection control of a brushless direct current motor. The electromechanical brake driver of the aircraft, provided by the invention, has the advantages that electromagnetic compatibility of the brake driver is enhanced, mature principle and high technical maturity are obtained and the reliability of the brake driver is enhanced.
Description
Technical field
The present invention relates to a kind of brake actuator, specifically a kind of brake actuator of realizing the electrical actuation brake.
Background technology
Present generation aircraft uses digital fly-by-wire hydraulic actuation brake system more, and the brake pressure execution unit is comprised of electro-hydraulic pressure servovalve and electromagnetic valve etc. in the typical airplane brake system.Basic principle of work is: pilot control brake pedal, antiskid braking control box is according to instruction and speed sensor signal in the brake system, the output control signal makes it open to connect electro-hydraulic pressure servovalve oil-feed path to electromagnetic valve, and the anti-skidding electric current of output brake is to the electro-hydraulic pressure servovalve, regulation output is to the brake pressure of brake wheel, produce suitable lock torque, the brake of realization aircraft and anti-skidding.
In the prior art, the adjusting of brake pressure is to be realized by hydraulic units such as electro-hydraulic pressure servovalve and electromagnetic valves in the brake system, but the quality of electro-hydraulic pressure servovalve, electromagnetic valve and hydraulic tubing is heavy, complicated capacity weight and the maintainability that has all reduced aircraft of installing/dismounting, and the fault of the parts such as servovalve and electromagnetic valve is difficult for monitoring and exist hydraulic fluid leak burning equivalent risk to make it affect the safety of aircraft.
Summary of the invention
In order to overcome the deficiencies in the prior art, the invention provides a kind of brake actuator of electrical actuation brake, testability, maintainability and the safety that can improve aircraft.
The technical solution adopted for the present invention to solve the technical problems is: comprise power circuit, control circuit and driving circuit.
Described power unit comprises power filter and DC-DC power module, and 15V and 5V power supply are provided, and is power sensor, position transduser, control circuit and driving circuit isolation power supply.
Described control circuit comprises control chip DSP and CPLD, DSP receives the force feedback signal of instruction brake weight signal and power sensor, and these two kinds of signals are carried out comprehensive rear by classical PI control algorithm, output pwm signal and motor steering signal be to CPLD, and DSP also gathers self-test signal and breakdown signal to finish the detection to driving circuit, power sensor and position transduser simultaneously; Carry out logic synthesis behind pwm signal, enable signal, motor positive and inverse signal and the overcurrent protection acquisition of signal of the motor rotor position signal that the CPLD device is sent position transduser, DSP output; export 6 road pwm signals and offer driving circuit, and then realize basic rotation and the overcurrent protection control of brshless DC motor.
Described driving circuit comprises the three phase full bridge inverter circuit that drives chip and MOSFET composition, and described driving chip internal adopts bootstrap technique to form the high pressure side power supply that suspends.
The invention has the beneficial effects as follows:
This actuator power supply partial design has been taked sensor, control circuit and driving circuit isolation power supply, has reduced electromagnetic interference, has strengthened the electromagnetic compatibility of brake actuator.
Control circuit has adopted the high dsp processor of calculated performance and CPLD combination, and this control circuit principle is ripe, and technology maturity is high.CPLD can realize above-mentioned functions fast on hardware, effectively shared the computing pressure of DSP, for processor resource has been saved in the execution of control algorithm.In addition CPLD also can realize some specific functions, arranges such as system initial state setting and brake done state etc.
Driving circuit has been taked classical three-phase bridge circuit, and this circuit engineering is ripe, and reliability is high, thereby has strengthened the reliability of brake actuator.The inner bootstrap technique of integrated drive chips forms the high pressure side power supply that suspends, thereby only can drive six MOSFET of three-phase inverter bridge circuit median generatrix with one road power supply, greatly reduces the complexity of circuit layout, has improved the reliability of brake actuator.
Description of drawings
Fig. 1 is brake driver control signal diagram.
Fig. 2 is brake drive power supply block diagram.
Fig. 3 is brake driver drives part block diagram.
The specific embodiment
The present invention is comprised of power circuit, control circuit, driving circuit.The actuator that it is characterized in that braking has substituted electro-hydraulic pressure servovalve in the hydraulic brake system and electromagnetic valve fully and changed brake does flowing mode.
Power unit is comprised of power filter and DC-DC power module in the brake actuator, for control desk and brake main wheel upper sensor, the driving circuit of brake actuator provides 15V, 5V power supply, and the operating voltage of 15V is provided.
The control part main circuit will be comprised of control chip DSP minimum system and CPLD device, the main function of DSP is the force feedback signal that receives instruction brake weight signal and power sensor, DSP carries out comprehensive rear by classical PI control algorithm to these two kinds of signals, output is used for the pwm signal of control brshless DC motor and motor steering signal to the CPLD device, and DSP also gathers self-test signal and breakdown signal to finish the detection to driving circuit, power sensor and position transduser in addition.The CPLD device mainly is to being to carry out logic synthesis behind pwm signal, enable signal, motor positive and inverse signal and the overcurrent protection acquisition of signal of motor rotor position signal, DSP output; export 6 road pwm signals and offer the driving chip, and then realize basic rotation and the overcurrent protection control of brshless DC motor.CPLD can realize above-mentioned functions fast on hardware, effectively shared the computing pressure of DSP, for processor resource has been saved in the execution of control algorithm.In addition CPLD also can realize some specific functions, arranges such as system initial state setting and brake done state etc.
The three phase full bridge inverter circuit that is comprised of driving chip and MOSFET in the driving circuit consists of, as shown in Figure 3.The inner bootstrap technique of integrated drive chips forms the high pressure side power supply that suspends, thereby only can drive six MOSFET of three-phase inverter bridge circuit median generatrix with one road power supply, greatly reduces the complexity of circuit layout, has improved the reliability of brake actuator.
The present invention is further described below in conjunction with drawings and Examples.
The electric brake system that present embodiment type machine is supporting.Present embodiment is only changed the software of brake actuator and can be realized purpose of the present invention under the prerequisite that does not change electric brake brake system original design theory of constitution.
Present embodiment comprises 1. control circuit boards, 2. power supply circuit boards, 3. drive circuit boards
In the enforcement: power supply circuit board provides 15V, 5V power supply, and the operating voltage of 15V is provided with brake main wheel upper sensor, driving circuit for the control desk of brake actuator.Control circuit board is for receiving the feedback current signal from power sensor on antiskid braking control box antiskid brake current signal in the brake system and the brake main wheel, after the circuit conditioning, send into DSP control chip AD input port, the DSP control chip to brake instruction current and feedback current gather with relatively after, to CPLD device in the control circuit board, the CPLD device is finished the driving circuit of exporting to after the distribution of the commutation logic of motor and pwm pulse on the power driving device by classical PI electric machine control algorithm output motor turn sign and pwm signal.Control circuit board is also finished the fault detection of circuit and main wheel upper sensor and drive circuit board in the brake actuator.The control signal of drive circuit board reception control circuit plate utilizes integrated drive chips to finish control to 6 inverters, and then the brake weight that requires of drive motor output.
Claims (1)
1. the dynamo-electric brake of an aircraft actuator comprises power circuit, control circuit and driving circuit, it is characterized in that:
Described power unit comprises power filter and DC-DC power module, and 15V and 5V power supply are provided, and is power sensor, position transduser, control circuit and driving circuit isolation power supply;
Described control circuit comprises control chip DSP and CPLD, DSP receives the force feedback signal of instruction brake weight signal and power sensor, and these two kinds of signals are carried out comprehensive rear by classical PI control algorithm, output pwm signal and motor steering signal be to CPLD, and DSP also gathers self-test signal and breakdown signal to finish the detection to driving circuit, power sensor and position transduser simultaneously; Carry out logic synthesis behind pwm signal, enable signal, motor positive and inverse signal and the overcurrent protection acquisition of signal of the motor rotor position signal that the CPLD device is sent position transduser, DSP output, export 6 road pwm signals and offer driving circuit, and then realize basic rotation and the overcurrent protection control of brshless DC motor;
Described driving circuit comprises the three phase full bridge inverter circuit that drives chip and MOSFET composition, and described driving chip internal adopts bootstrap technique to form the high pressure side power supply that suspends.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104703613A CN102923116A (en) | 2012-11-19 | 2012-11-19 | Electromechanical brake driver of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104703613A CN102923116A (en) | 2012-11-19 | 2012-11-19 | Electromechanical brake driver of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102923116A true CN102923116A (en) | 2013-02-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012104703613A Pending CN102923116A (en) | 2012-11-19 | 2012-11-19 | Electromechanical brake driver of aircraft |
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| CN (1) | CN102923116A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103248290A (en) * | 2013-05-23 | 2013-08-14 | 西北工业大学 | Grey sliding mode control method for dual-redundancy brushless direct current motor of electric brake of airplane |
| CN107863911A (en) * | 2017-10-27 | 2018-03-30 | 北京精密机电控制设备研究所 | A kind of isolated high power three-phase brushless motor driver module of numeral |
| CN114301344A (en) * | 2022-01-08 | 2022-04-08 | 图湃(北京)医疗科技有限公司 | Motor driving circuit, system and motor driving method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1095834A2 (en) * | 1999-11-01 | 2001-05-02 | Toyota Jidosha Kabushiki Kaisha | Braking torque control apparatus |
| JP2001239929A (en) * | 2000-02-28 | 2001-09-04 | Hitachi Ltd | Brake device |
| CN102700542A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Dual-redundancy electric brake device of airplane and control method for dual-redundancy electric brake device |
-
2012
- 2012-11-19 CN CN2012104703613A patent/CN102923116A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1095834A2 (en) * | 1999-11-01 | 2001-05-02 | Toyota Jidosha Kabushiki Kaisha | Braking torque control apparatus |
| JP2001239929A (en) * | 2000-02-28 | 2001-09-04 | Hitachi Ltd | Brake device |
| CN102700542A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Dual-redundancy electric brake device of airplane and control method for dual-redundancy electric brake device |
Non-Patent Citations (1)
| Title |
|---|
| 文延: "飞机全电刹车系统控制器设计", 《中国优秀硕士学位论文全文数据库 工程科技II辑》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103248290A (en) * | 2013-05-23 | 2013-08-14 | 西北工业大学 | Grey sliding mode control method for dual-redundancy brushless direct current motor of electric brake of airplane |
| CN107863911A (en) * | 2017-10-27 | 2018-03-30 | 北京精密机电控制设备研究所 | A kind of isolated high power three-phase brushless motor driver module of numeral |
| CN114301344A (en) * | 2022-01-08 | 2022-04-08 | 图湃(北京)医疗科技有限公司 | Motor driving circuit, system and motor driving method |
| CN114301344B (en) * | 2022-01-08 | 2024-04-09 | 图湃(北京)医疗科技有限公司 | Motor driving circuit, system and motor driving method |
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Application publication date: 20130213 |