CN202608760U - Airplane double-redundancy electric-brake device - Google Patents
Airplane double-redundancy electric-brake device Download PDFInfo
- Publication number
- CN202608760U CN202608760U CN 201220252649 CN201220252649U CN202608760U CN 202608760 U CN202608760 U CN 202608760U CN 201220252649 CN201220252649 CN 201220252649 CN 201220252649 U CN201220252649 U CN 201220252649U CN 202608760 U CN202608760 U CN 202608760U
- Authority
- CN
- China
- Prior art keywords
- unit
- brake pressure
- current
- remaining
- power
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Control Of Multiple Motors (AREA)
Abstract
The utility model discloses an airplane double-redundancy electric-brake device and a control method. A redundancy driving controller portion receives brake pressure given signals and drives a brake actuator to work, so that brake pressure applied on a braked airplane wheel follows the brake pressure given signal. By adopting redundancy technology, an easily damaged mechanism in an airplane brake driving device is subjected to hot backup, so that corresponding parts can work at power one second of the rated power in normal working condition, and the service life of the driving device is prolonged and reliability thereof is improved. When one redundancy of the driving device is in fault, fault points can be detected in real time and separated, a motor in fault drops out working, so that the driving device is switched to run in a single-channel mode, and reliability of an airplane brake system is improved.
Description
Technical field
The present invention relates to a kind of pair of remaining Electric Braking Devices Using, the two remaining Electric Braking Devices Using of especially a kind of aircraft.
Background technology
Airplane brake system is the subsystem that has relatively independent function on the aircraft, and its effect is static weight, dynamic impulsion load of carrying aircraft and the kinetic energy when absorbing aircraft landing, realizes the braking of taking off, land, slide, turning and the control of aircraft.
At present, electric brake control system achievement in research has: publication number is that the patent " aircraft electrical brake control system architecture " of CN101117155 and patent " the depowering pattern of aircraft electric brake system " that publication number is CN101568458 are two kinds of technology of Boeing's research.The article " full electric brake design of Driver of aircraft and Study on Key Technique " that is published in " computer measurement and control " is that a kind of designs C PLD and DSP are the technology of the controller of brake system major control chip.These electric brakes all do not adopt redundancy, and reliability is not high.The present invention adopts two redundancy technology designs, improves the reliability of whole brake system.
Summary of the invention
In order to improve the reliability of airplane brake system, the invention provides a kind of two remaining actuating devices of aircraft electric brake, under normal circumstances; Can accomplish normal aircraft brake; When actuating device one remaining breaks down, can detect the trouble point in real time and isolate, under single channel; Accomplish brake function, thereby improve the reliability of airplane brake system.
The technical solution adopted for the present invention to solve the technical problems is: comprise redundant drive controller, braking action device and the wheel of being stopped.The redundant drive controller partly receives the given signal of brake pressure, drives the work of braking action device, makes the brake pressure that is applied on the wheel of being stopped follow the given signal of brake pressure.
Wherein, the redundant drive controller partly comprises brake pressure feedback conditioning unit, the given receiving element of brake pressure, DSP unit, CPLD unit, buffer circuit unit, power drive unit, current acquisition unit, overcurrent protection auxiliary unit and power-supply system unit.The given receiving element of brake pressure is converted into voltage signal with the given signal of brake pressure; Input DSP unit; Input DSP unit after the two-way brake pressure feedback signal amplification filtering that brake pressure feedback conditioning unit records two remaining pressure sensors, the duty cycle signals of two windings of braking action device is controlled in the output of DSP unit respectively.The CPLD unit carries out logic operation with duty cycle signals and braking action device two cover hall signals, and the modulation commutation signal of two winding runnings of output control braking action device through buffer circuit unit and power drive unit, is controlled the operation of braking action device respectively.Gather the bus current of two margin brushless DC motors at power drive unit; Through overcurrent protection auxiliary unit, with bus current and predefined overcurrent threshold, if bus current is greater than predefined overcurrent threshold value; Then over-current signal is low; If bus current is smaller or equal to predefined overcurrent threshold value, then over-current signal is high, and over-current signal is sent in the DSP unit.When over current fault appearred in motor, it was low that the DSP unit detects over-current signal, then turn-offs duty cycle signals, thereby got rid of over current fault.The bus current and the phase current of two margin brushless DC machine winding on the power drive unit gathered in the current acquisition unit, and with input DSP unit after bus current and the phase current filtering.The power-supply system unit receives two control power supplys; Through diode two power supplys are connected in parallel; To brake pressure feedback conditioning unit, the given receiving element of brake pressure, DSP unit, CPLD unit, buffer circuit unit, power drive unit, current acquisition unit, the power supply of overcurrent protection auxiliary unit; The power-supply system unit receives two driving powers, supplies power to power drive unit.
The braking action device adopts two margin brushless DC motors.Wherein, The stator winding of two margin brushless DC motors be two be enclosed within 30 ° of electric angles of mutual deviation on the space Y type bonded assembly winding constitute; Two cover windings are isolated from each other on electric, magnetic field coupling on the space, remaining each other each other, the shared PM rotor of two margin brushless DC motors.Every cover winding of two margin brushless DC motors has separately independently Hall element, and two cover Hall elements are remaining each other, closes to be called two remaining Hall elements.The signal that two remaining Hall elements send is called two remaining hall signals.
When working, the present invention may further comprise the steps:
The first step: gather two-way brake pressure feedback signal, and carry out the AD conversion.
Second step: if two-way brake pressure feedback signal less than predefined error threshold, then got into for the 4th step, otherwise got into for the 3rd step.
The 3rd step: if one road brake pressure feedback signal is greater than the range maxim of pressure sensor; Or, then diagnose this road pressure sensor failure less than its range minimum value, give pressure feedback with the brake pressure feedback signal assignment of another road pressure sensor; Got into for the 5th step, otherwise got into for the 4th step.
The 4th step: pressure feedback equals two-way brake pressure feedback signal sum divided by two.
The 5th step: gather two remaining Hall element signals,, then diagnose this road Hall element fault, otherwise got into for the 6th step if one road Hall element signal is 000 or 111.
The 6th step: gather each remaining winding bus current and phase current.
The 7th step: if one road winding bus current greater than predefined short circuit threshold value, then begins the short circuit timing, greater than predefined short circuit upper limit threshold, then diagnosing this road winding is short trouble, gets into for the tenth step as if the short circuit timing.If one road winding bus current is greater than the motor minimum working current; And less than predefined standard 0 digit current lower limit, then begin the timing of opening circuit, if open circuit timing greater than the predefined upper limit threshold that opens circuit; Then diagnosing this road winding is open circuit fault, gets into for the tenth step.Otherwise got into for the 8th step.
The 8th step: gather the given signal of brake pressure, and carry out the AD conversion.
The 9th step: if the value of pressure ring counting machine greater than the pressure ring Ct value, then with the pressure ring counter O reset, is carried out pressure ring PID calculating according to brake pressure is given with the brake pressure feedback, the value with the pressure ring counting machine adds 1 then; Otherwise directly the value with the pressure ring counting machine adds 1.
The tenth step: if one road short circuit in winding fault or open circuit fault or cooresponding this road Hall element fault then are changed to 0 with this road dutycycle, another road electric current loop is given as pressure ring output; Be fed back to another road bus current; Carry out electric current loop PID computing, DSP is passed in electric current loop PID computing output, produces sky and compares signal; Return the first step, otherwise got into for the 11 step.
The 11 step: given the half the of pressure ring output that be respectively of two-way electric current loop, be fed back to bus current separately, through electric current loop PID computing separately, operation result input DSP produces duty cycle signals separately respectively, returns the first step.
The invention has the beneficial effects as follows: the present invention adopts redundancy; The mechanism that damages easily in the aircraft brake actuating device has been carried out hot spare; Under normal operation, make corresponding parts be operated in the half the of rated power operation, improved the life-span and the reliability of actuating device.When the some remainings of actuating device break down, can make actuating device switch to operation under the single, guarantee the aircraft safety brake.
Below in conjunction with accompanying drawing and embodiment the present invention is further specified.
Description of drawings
Fig. 1 is brake redundant drive apparatus structure.
Among the figure, 1-redundant drive controller, 2-braking action device, the 3-wheel of being stopped
Fig. 2 is the redundant drive controller architecture
Among the figure, 4-two margin brushless DC motors, 5-brake pressure feedback conditioning unit; The given receiving element of 6-brake pressure, 7-DSP unit, 8-current acquisition unit; 9-overcurrent protection auxiliary unit, 10-power-supply system unit, 11-CPLD unit; 12-buffer circuit unit, 13-power drive unit.
The specific embodiment
As shown in Figure 1, the present invention includes redundant drive controller 1, braking action device 2 and the wheel 3 of being stopped.Redundant drive controller 1 receives the given signal of brake pressure, through control method control, drives two margin brushless DC motors 4 work in the braking action device 2, makes the brake pressure that is applied on the wheel 3 of being stopped follow the given signal of brake pressure.In the present invention, will control power supply, driving power, machine winding, motor Hall element, pressure sensor, power drive unit and back up design.
Wherein, redundant drive controller 1 comprises the given receiving element in brake pressure feedback conditioning unit 5, brake pressure 6, DSP unit 7, CPLD unit 11, buffer circuit unit 12, power drive unit 13, current acquisition unit 8, overcurrent protection auxiliary unit 9 and power-supply system unit 10.(0～40mA) is converted into 0～3V voltage signal through resistance to the given receiving element 6 of brake pressure with the given signal of brake pressure; The AD port of input DSP unit 7; Carry out analogue to digital conversion, brake pressure feedback conditioning unit 5 is with brake pressure feedback signal (the two-way 0～20mV differential pressure signal that is recorded by two remaining pressure sensors) amplification filtering to 0～3V voltage signal, the AD port of input DSP unit 7; Carry out analogue to digital conversion; Regulate through control program, the task manager through DSP unit 7, output is the duty cycle signals of two 4 two windings of margin brushless DC motor of control respectively.CPLD unit 11 carries out logic operation with 4 liang of covers of duty cycle signals and two margin brushless DC motors hall signal; The modulation commutation signal of two windings runnings of two margin brushless DC motors 4 is controlled in output respectively; Through the buffer circuit unit 12 with power drive unit 13, two margin brushless DC motors 4 operations of control.At power drive unit 13, gather the bus current of two margin brushless DC motors 4, through overcurrent protection auxiliary unit 9; With bus current and predefined overcurrent threshold; If bus current is greater than predefined overcurrent threshold value, then over-current signal is low, if bus current is smaller or equal to predefined overcurrent threshold value; Then over-current signal is high, and over-current signal is sent in the DSP unit 7.When over current fault appearred in motor, it was low that DSP unit 7 detects over-current signal, then turn-offs duty cycle signals, thereby got rid of over current fault.Bus current and phase current that two margin brushless DC motor 4 windings on the power drive unit 13 are gathered in current acquisition unit 8, and with input DSP unit 7 after bus current and the phase current filtering.Power-supply system unit 10 receives two control power supplys; Through diode two power supplys are connected in parallel; To the given receiving element in brake pressure feedback conditioning unit 5, brake pressure 6, DSP unit 7, CPLD unit 11, buffer circuit unit 12, power drive unit 13, current acquisition unit 8,9 power supplies of overcurrent protection auxiliary unit; Power-supply system unit 10 receives two driving powers, gives power drive unit 13 power supplies.
Braking action device 2 is made up of two margin brushless DC electric motor units 4 and reductor and ball-screw.Wherein, The stator winding of two margin brushless DC motors 4 be two be enclosed within 30 ° of electric angles of mutual deviation on the space Y type bonded assembly winding constitute; Two cover windings are isolated from each other on electric, magnetic field coupling on the space, remaining each other each other, the shared PM rotor of two margin brushless DC motors.Every cover winding of two margin brushless DC motors has separately independently Hall element, and two cover Hall elements are remaining each other, closes to be called two remaining Hall elements.The signal that two remaining Hall elements send is called two remaining hall signals.
Control method of the present invention is:
The first step: gather the brake pressure feedback signal, and carry out the AD conversion.Got into for second step.
Second step: if | remaining 1 brake pressure feedback-remaining 2 brake pressures feedback | < predefined error threshold (in this model machine, predefined error threshold is 500N) then got into for the 7th step, otherwise got into for the 3rd step.
The 3rd step: if remaining 1 brake pressure feeds back greater than range maxim (15000N), or remaining 1 rudder face pressure feedback got into for the 4th step less than range minimum value (100N).Otherwise got into for the 5th step.
The 4th step: be diagnosed as remaining 1 pressure sensor failure, remaining 2 brake pressure values of feedback are composed to pressure feedback.Got into for the 8th step.
The 5th step: if remaining 2 brake pressures feed back greater than range maxim (15000N), or remaining 2 brake pressures feedback got into for the 6th step less than range minimum value (100N).Otherwise got into for the 7th step.
The 6th step: be diagnosed as remaining 2 pressure sensor failures, remaining 1 brake pressure value of feedback is composed to pressure feedback.Got into for the 8th step.
The 7th step: pressure feedback=(remaining 1 brake pressure feedback+remaining 2 brake pressures feedback)/2 got into for the 8th step.
The 8th step: gather two remaining Hall element signals.Got into for the 9th step.
The 9th step:, then got into for the tenth step, otherwise got into for the 11 step if remaining 1 hall signal is 000 or 111.
The tenth step: be diagnosed as remaining 1 Hall element fault.Got into for the 11 step.
The 11 step:, then got into for the 12 step, otherwise got into for the 13 step if remaining 2 hall signals are 000 or 111.
The 12 step: be diagnosed as remaining 2 Hall element faults.Got into for the 13 step.
The 13 step: gather each remaining winding bus current and phase current.Got into for 14 steps.
The 14 step: if remaining 1 winding bus current greater than predefined short circuit threshold value (in this model machine, predefined short circuit threshold value is 2A), then got into for the 15 step, otherwise got into for the 18 step.
The 15 step: remaining 1 short circuit counting machine adds 1.Got into for the 16 step.
The 16 step: if remaining 1 short circuit counting machine greater than predefined short circuit upper limit threshold (in this model machine, predefined short circuit upper limit threshold is 10), then got into for the 17 step, otherwise got into for the 18 step.
The 17 step: be diagnosed as remaining 1 short circuit in winding fault.Got into for the 22 step.
The 18 step: if remaining 2 winding bus currents greater than predefined short circuit threshold value (in this model machine, predefined short circuit threshold value is 2A), then got into for the 19 step, otherwise got into for the 22 step.
The 19 step: remaining 2 short circuit counting machines add 1.Got into for the 20 step.
The 20 step: if remaining 2 short circuit counting machines greater than predefined short circuit upper limit threshold (in this model machine, predefined short circuit upper limit threshold is 10), then got into for the 21 step, otherwise got into for the 22 step.
The 21 step: be diagnosed as remaining 2 short circuit in winding faults.Got into for the 22 step.
The 22 the step: if remaining 1 winding bus current greater than motor minimum working current lower limit (in this model machine; Be limited to 50mA under the motor minimum working current) or remaining 2 winding bus currents greater than motor minimum working current lower limit (in this model machine; Be limited to 50mA under the motor minimum working current); Then got into for the 23 step, otherwise got into for the 31 step.
The 23 step: if remaining 1 winding phase current less than predefined standard 0 digit current lower limit (in this model machine, being limited to 30mA under predefined standard 0 digit current), then getting into for the 24 step, otherwise got into for the 27 step.
The 24 step: the remaining 1 winding counting machine that opens circuit adds 1, gets into for the 25 step.
The 25 step: the value of counting machine then got into for the 26 step, otherwise got into for the 27 step greater than the predefined upper limit threshold that opens circuit (in this model machine, the predefined upper limit threshold that opens circuit is 10) if remaining 1 winding opens circuit.
The 26 step: be diagnosed as remaining 1 winding open circuit fault.Got into for the 31 step.
The 27 step: if remaining 2 winding phase currents less than predefined standard 0 digit current lower limit (in this model machine, being limited to 30mA under predefined standard 0 digit current), then getting into for the 28 step, otherwise got into for the 31 step.
The 28 step: the remaining 2 windings counting machine that opens circuit adds 1, gets into for the 29 step.
The 29 step: the value of counting machine then got into for the 30 step, otherwise got into for the 31 step greater than the predefined upper limit threshold that opens circuit (in this model machine, the predefined upper limit threshold that opens circuit is 10) if remaining 2 windings open circuit.
The 30 step: be diagnosed as remaining 2 winding open circuit faults.Got into for the 31 step.
The 31 step: gather the given signal of brake pressure, and carry out the AD conversion.Got into for the 32 step.
The 32 step: if the value of pressure ring counting machine then got into for the 33 step greater than pressure ring Ct value (in this model machine, the pressure ring Ct value is 1ms).Otherwise got into for the 34 step.
The 33 step: the pressure ring counter O reset, carry out pressure ring PID calculating according to brake pressure is given with the brake pressure feedback.Got into for the 34 step.
The 34 step: the value of pressure ring counting machine adds 1, gets into for the 35 step.
The 35 step: if remaining 1 short circuit in winding fault or remaining 1 winding open circuit fault or remaining 1 Hall element fault then got into for the 36 step.Otherwise got into for the 37 step.
The 36 step: remaining 1 dutycycle is changed to 0, and remaining 2 electric current loops are given as pressure ring output, are fed back to remaining 2 bus currents, carry out remaining 2 electric current loop PID computings, and the task manager of DSP is passed in remaining 2 electric current loop PID output, produces remaining 2 duty cycle signals.Get into the first step.
The 37 step: if remaining 2 short circuit in winding faults or remaining 2 winding open circuit faults or remaining 2 Hall element faults then got into for the 38 step.Otherwise got into for the 39 step.
The 38 step: remaining 2 dutycycles are changed to 0, and remaining 1 electric current loop is given as pressure ring output, is fed back to remaining 1 bus current, carries out remaining 1 electric current loop PID computing, and the task manager of DSP is passed in remaining 1 electric current loop PID output, produces remaining 1 duty cycle signals.Get into the first step.
The 39 step: remaining 1 and given the half the of pressure ring output that be respectively of remaining 2 electric current loops; Be fed back to the bus current of remaining separately; Through the electric current loop PID computing of remaining separately, operation result is imported DSP task manager separately, produces the duty cycle signals of remaining 1 and remaining 2 respectively.Get into the first step.
Claims (2)
1. two remaining Electric Braking Devices Using of an aircraft; Comprise redundant drive controller, braking action device and the wheel of being stopped; It is characterized in that: the redundant drive controller partly receives the given signal of brake pressure; Drive the work of braking action device, make the brake pressure that is applied on the wheel of being stopped follow the given signal of brake pressure; Wherein, the redundant drive controller partly comprises brake pressure feedback conditioning unit, the given receiving element of brake pressure, DSP unit, CPLD unit, buffer circuit unit, power drive unit, current acquisition unit, overcurrent protection auxiliary unit and power-supply system unit; The given receiving element of brake pressure is converted into voltage signal with the given signal of brake pressure; Input DSP unit; Input DSP unit after the two-way brake pressure feedback signal amplification filtering that brake pressure feedback conditioning unit records two remaining pressure sensors, the duty cycle signals of two windings of braking action device is controlled in the output of DSP unit respectively; The CPLD unit carries out logic operation with duty cycle signals and braking action device two cover hall signals, and the modulation commutation signal of two winding runnings of output control braking action device through buffer circuit unit and power drive unit, is controlled the operation of braking action device respectively; Gather the bus current of two margin brushless DC motors at power drive unit; Through overcurrent protection auxiliary unit, with bus current and predefined overcurrent threshold, if bus current is greater than predefined overcurrent threshold value; Then over-current signal is low; If bus current is smaller or equal to predefined overcurrent threshold value, then over-current signal is high, and over-current signal is sent in the DSP unit; When over current fault appearred in motor, it was low that the DSP unit detects over-current signal, then turn-offs duty cycle signals, thereby got rid of over current fault; The bus current and the phase current of two margin brushless DC machine winding on the power drive unit gathered in the current acquisition unit, and with input DSP unit after bus current and the phase current filtering; The power-supply system unit receives two control power supplys; Through diode two power supplys are connected in parallel; To brake pressure feedback conditioning unit, the given receiving element of brake pressure, DSP unit, CPLD unit, buffer circuit unit, power drive unit, current acquisition unit, the power supply of overcurrent protection auxiliary unit; The power-supply system unit receives two driving powers, supplies power to power drive unit.
2. the two remaining Electric Braking Devices Using of aircraft according to claim 1 is characterized in that: described braking action device adopts two margin brushless DC motors; Wherein, The stator winding of two margin brushless DC motors be two be enclosed within 30 ° of electric angles of mutual deviation on the space Y type bonded assembly winding constitute; Two cover windings are isolated from each other on electric, magnetic field coupling on the space, remaining each other each other, the shared PM rotor of two margin brushless DC motors; Every cover winding of two margin brushless DC motors has separately independently Hall element, and two cover Hall elements are remaining each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220252649 CN202608760U (en) | 2012-05-31 | 2012-05-31 | Airplane double-redundancy electric-brake device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220252649 CN202608760U (en) | 2012-05-31 | 2012-05-31 | Airplane double-redundancy electric-brake device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202608760U true CN202608760U (en) | 2012-12-19 |
Family
ID=47342484
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220252649 Expired - Fee Related CN202608760U (en) | 2012-05-31 | 2012-05-31 | Airplane double-redundancy electric-brake device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202608760U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102700530A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Redundant driving electric brake of airplane and control method for redundant driving electric brake |
| 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 |
| CN104002784A (en) * | 2014-05-14 | 2014-08-27 | 西安航空制动科技有限公司 | Brake control system of multi-wheel-train brake machine wheel |
| CN108871670A (en) * | 2018-07-09 | 2018-11-23 | 西北工业大学 | Electrical Break System of Aircraft pressure sensor failure detection method |
| CN107650892B (en) * | 2017-09-13 | 2019-09-17 | 西安航空制动科技有限公司 | More train Electric Brake System of Aircraft electromechanics driving frameworks and brake force control method |
-
2012
- 2012-05-31 CN CN 201220252649 patent/CN202608760U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102700530A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Redundant driving electric brake of airplane and control method for redundant driving electric brake |
| 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 |
| CN102700542B (en) * | 2012-05-31 | 2014-06-11 | 西北工业大学 | Dual-redundancy electric brake device of airplane and control method for dual-redundancy electric brake device |
| CN102700530B (en) * | 2012-05-31 | 2014-11-05 | 西北工业大学 | Redundant driving electric brake of airplane and control method for redundant driving electric brake |
| CN104002784A (en) * | 2014-05-14 | 2014-08-27 | 西安航空制动科技有限公司 | Brake control system of multi-wheel-train brake machine wheel |
| CN104002784B (en) * | 2014-05-14 | 2017-01-11 | 西安航空制动科技有限公司 | Brake control system of multi-wheel-train brake machine wheel |
| CN107650892B (en) * | 2017-09-13 | 2019-09-17 | 西安航空制动科技有限公司 | More train Electric Brake System of Aircraft electromechanics driving frameworks and brake force control method |
| CN108871670A (en) * | 2018-07-09 | 2018-11-23 | 西北工业大学 | Electrical Break System of Aircraft pressure sensor failure detection method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102700542B (en) | Dual-redundancy electric brake device of airplane and control method for dual-redundancy electric brake device | |
| CN102700530B (en) | Redundant driving electric brake of airplane and control method for redundant driving electric brake | |
| CN102700706A (en) | Dual-redundancy actuator system and control method | |
| CN202608760U (en) | Airplane double-redundancy electric-brake device | |
| US11059386B2 (en) | Construction and operation of electric or hybrid aircraft | |
| US8840070B2 (en) | Power supply and control device for actuators, corresponding acutation assembly, and aircraft comprising such a device | |
| CN104787311B (en) | A kind of Electrical Break System of Aircraft and Electric Brake System of Aircraft remaining control method | |
| CN202632110U (en) | Dual-redundancy steering engine system | |
| EP3743974A1 (en) | Electrical powering or drive system for a motor in an electrically driven aircraft | |
| CN104229126A (en) | High-reliability landing gear control system | |
| CN204750274U (en) | [electric] motor coach and electronic power -assisted steering system thereof | |
| CN207684680U (en) | Band-type brake coil control circuit, band-type brake control power-supply device and elevator | |
| CN104648660A (en) | Airplane dual-redundancy digital type undercarriage retraction/extension controller | |
| CN103437954A (en) | Wind power variable pitch control system and wind power variable pitch system | |
| CN113093618B (en) | Brake controller hardware architecture and control method | |
| CN104787024B (en) | Powering-on self-detecting method for electrical brake | |
| CN103640692A (en) | Handle-based autonomous control method of training plane undercarriage system | |
| CN105000172A (en) | Launch and recovery electrical control system of aircraft landing gear | |
| CN110963025A (en) | Aircraft brake system architecture | |
| CN104648684A (en) | Small-sized unmanned aerial vehicle (UAV) hoisting equipment and hoisting method | |
| CN103818263B (en) | A kind of braking control system and method | |
| CN103625506B (en) | A kind of driver controller brake command signal generating means | |
| Liu et al. | Study on electric brake system of civil aircraft | |
| CN115453853A (en) | Unmanned aerial vehicle flight management system steering wheel troubleshooting system | |
| CN102923116A (en) | Electromechanical brake driver of aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20121219 Termination date: 20140531 |