CN106877292B - A control method for current protection of servo steering gear - Google Patents
A control method for current protection of servo steering gear Download PDFInfo
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- CN106877292B CN106877292B CN201510924628.5A CN201510924628A CN106877292B CN 106877292 B CN106877292 B CN 106877292B CN 201510924628 A CN201510924628 A CN 201510924628A CN 106877292 B CN106877292 B CN 106877292B
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- 238000000034 method Methods 0.000 title claims abstract description 27
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 88
- 238000012545 processing Methods 0.000 claims abstract description 7
- 238000012546 transfer Methods 0.000 claims description 4
- 238000013461 design Methods 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 description 9
- 239000007788 liquid Substances 0.000 description 6
- 239000008358 core component Substances 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
- H02H7/08—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors
- H02H7/085—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors against excessive load
- H02H7/0854—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors against excessive load responsive to rate of change of current, couple or speed, e.g. anti-kickback protection
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/44—Blade pitch-changing mechanisms electric
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
- H02H7/08—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors
- H02H7/0833—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors for electric motors with control arrangements
- H02H7/0844—Fail safe control, e.g. by comparing control signal and controlled current, isolating motor on commutation error
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
- H02H7/08—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors
- H02H7/085—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors against excessive load
- H02H7/0855—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors against excessive load avoiding response to transient overloads, e.g. during starting
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
- H02H7/08—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors
- H02H7/085—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors against excessive load
- H02H7/0856—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors against excessive load characterised by the protection measure taken
- H02H7/0857—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors against excessive load characterised by the protection measure taken by lowering the mechanical load of the motor
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
本发明属于飞行控制系统的安全性设计技术，涉及一种伺服舵机电流保护的控制方法，当机上液压系统出现故障时，为防止平尾伺服舵机的力马达过热导致其损毁或失效，需要切断平尾伺服舵机的力马达供电：首先进行信号采集和处理，获取动压信号、机轮承载信号、液压良好信号和力马达电流信号，并进行交叉传输和信号表决；进行电流保护启动的条件判定，在动压信号表决值较小或机轮承载表决值为承载的条件下，启动电流保护，否则不启动电流保护；进行电流保护的条件判定，如果在液压故障期间出现力马达电流的幅值和持续时间均超过规定要求，切除平尾伺服舵机的力马达供电。The invention belongs to the safety design technology of a flight control system, and relates to a control method for the current protection of a servo steering gear. When a hydraulic system on the aircraft fails, in order to prevent the force motor of the horizontal tail servo steering gear from being overheated and causing its damage or failure, it needs to be cut off. Power supply for the force motor of the horizontal tail servo steering gear: firstly, the signal acquisition and processing are carried out to obtain the dynamic pressure signal, the wheel bearing signal, the hydraulic good signal and the force motor current signal, and cross-transmission and signal voting are carried out; , under the condition that the voting value of the dynamic pressure signal is small or the voting value of the wheel load is the load, the current protection is activated, otherwise the current protection is not activated; the condition of the current protection is determined, if the amplitude of the force motor current occurs during the hydraulic fault and the duration exceeds the specified requirements, cut off the power supply of the force motor of the horizontal tail servo steering gear.
Description
Technical field
The invention belongs to flight control system safety Design technology, it is related to flight control system horizontal tail Servo-controller
The improvement of current protection strategy.
Background technique
Horizontal tail Servo-controller in aircraft flight control system, which uses, directly drives valve type Servo-controller, wherein straight
Driving valve is connect as servo-controlled core component, is driven by force motor, and force motor is by SERVO CONTROL output force motor electricity
Stream drives.When aircraft operates normally in the air and on the ground, the horizontal tail servo of flight control system realizes closed-loop control, power horse
Up to only will appear of short duration electric current；And hydraulic not kilter is continuously when hydraulic good signal occurs in ground maintenance in aircraft
When, the horizontal tail servo of flight control system cannot achieve closed-loop control, and force motor will appear lasting high current, cause force motor
Overheat causes it to damage or fail, and needs to increase current protection method, the force motor power supply of cutting horizontal tail Servo-controller at this time.
The condition of conventional current protection starting, when aircraft is in ground maintenance, is needed by ground by manual control
Face maintenance personnel ensures that wheel carrying signal is wheel loaded state, with the protection of this starting current.This conventional current protection
Starting mode has been unable to meet the high safety of aircraft, highly reliable working service requirement, the disadvantage is that: the first, attended operation is multiple
Miscellaneous, inefficient, needing manual control wheel carrying signal is wheel loaded state, it is ensured that meets the condition of current protection starting；
The second, safety and reliability is poor, and when manually carrying out the control of current protection entry condition, artificial maloperation or possibility of forgetting are led
It causes the current protection of horizontal tail servo not start, causes the force motor of horizontal tail Servo-controller to overheat, influence the peace of horizontal tail Servo-controller
Quan Xing.
Summary of the invention
The purpose of the present invention is: the present invention proposes a kind of control method of Servo-controller current protection, reliable, effective, keeps away
Exempt from when aircraft is in ground maintenance the protection of horizontal tail servo current caused by artificial maloperation or possibility of forgetting not start, causes horizontal tail
The force motor of Servo-controller fails, and guarantees the safety of horizontal tail Servo-controller current protection, promotes maintenance efficiency, meets aircraft and flies
Row control system internal field, flight-line service demand.
The technical scheme is that
A kind of the step of control method of Servo-controller current protection, this method, is:
Step 1,
Each remaining acquisition dynamic pressure signal connected to it, the wheel of four redundance flight control systems computers carry signal, liquid
Press good signal and force motor current signal；Wheel carrying signal is divided into wheel loaded state and wheel not loaded state, hydraulic
Good signal is divided into hydraulic kilter and hydraulic not kilter, and force motor current signal is divided into force motor electric current greater than electric current
Threshold status and force motor electric current are less than or equal to current threshold state；
The dynamic pressure signal itself acquired, wheel are carried signal, hydraulic good letter by the flight-control computer of each remaining
Number and force motor current signal Cross transfer give other 3 flight-control computers, make the every of four redundance flight control systems computers
A remaining all obtains the dynamic pressure signal and wheel carrying signal of 4 remainings；
Step 2,
The flight-control computer of each remaining puts to the vote to dynamic pressure signal and wheel the carrying signal of 4 remainings, decides by vote
Current protection entry condition each group state value is generated afterwards, and wheel carrying signal provides voting using the same method unanimously decided by vote entirely
It as a result is wheel loaded state or wheel not loaded state；The method that dynamic pressure signal uses majority voting, to dynamic after voting
Signal is pressed to carry out state processing, dynamic pressure signal condition is divided into dynamic pressure and is less than or equal to dynamic pressure threshold greater than dynamic pressure threshold status and dynamic pressure
State of value；
Step 3,
Some redundance flight control systems computer of four On A Redundant Flight Control Systems is full when current protection entry condition state value
Foot: dynamic pressure signal condition is that dynamic pressure is less than or equal to dynamic pressure threshold status or wheel carrying signal when being wheel loaded state,
Determine that the current protection entry condition of the redundance flight control systems computer meets, enters step 4；Otherwise, it is determined that the redundant flight
The current protection entry condition of control computer is unsatisfactory for；
Step 4,
When some redundance flight control systems computer of four On A Redundant Flight Control Systems meets current protection entry condition, this is remaining
Degree flight control system enters current protection program: if wheel carrying signal is wheel loaded state or dynamic pressure signal condition
Being less than or equal to dynamic pressure threshold status, force motor current signal for dynamic pressure is that force motor electric current is greater than current threshold state, hydraulic
Good signal is that three conditions of hydraulic not kilter meet simultaneously, and the state that three conditions meet simultaneously continues 10 points
Clock cuts off the force motor power supply of the horizontal tail Servo-controller of this On A Redundant Flight Control System；
After certain On A Redundant Flight Control System enters current protection program, there is any one following condition and meet: wheel
Carrying signal is that loaded state, dynamic pressure signal condition are not that dynamic pressure is greater than dynamic pressure threshold status, hydraulic good signal is liquid to wheel
Press kilter, continuous 100 milliseconds of force motor current signal for force motor electric current be less than or equal to current threshold state when, this is remaining
Degree flight control system exits current protection；
Wherein, in step 2 signal it is complete with the method unanimously decided by vote are as follows: when the state of four remaining discrete input signals is uniform
It causes, vote value takes the state value of the remaining discrete input signal；When as long as four remaining discrete input signals have the letter of a remaining
Number state is different from other remainings, determines that the remaining is faulty, and vote value takes failure safe value, and wheel carries the failure peace of signal
Total head is wheel not loaded state.
The invention has the advantages that the invention enables aircrafts in ground maintenance, horizontal tail Servo-controller can be automatically performed
Current protection starting avoids the protection of the horizontal tail servo current as caused by artificial maloperation or possibility of forgetting and does not start, causes
The force motor of horizontal tail Servo-controller fails, and guarantees the safety of horizontal tail Servo-controller current protection, promotes maintenance efficiency, meets and flies
Machine flight control system internal field, flight-line service demand.
Specific embodiment
The working principle of the invention is: starting method using automatic current protection, so that aircraft is prevented in ground maintenance
The force motor superheating phenomenon that may only occur, improves the safety of horizontal tail Servo-controller current protection, meets aircraft flight control
System internal field, flight-line service demand.When aircraft is in ground maintenance, flight-control computer according to dynamic pressure signal condition,
Wheel carries signal, the condition judgement of current protection starting is carried out, by each cond for obtaining the protection of horizontal tail servo current
Value judges whether the force motor power supply for cutting off the horizontal tail Servo-controller of this remaining channel flight control system.
A kind of the step of control method of Servo-controller current protection, this method, is:
Step 1,
Each remaining acquisition dynamic pressure signal connected to it, the wheel of four redundance flight control systems computers carry signal, liquid
Press good signal and force motor current signal；Wheel carrying signal is divided into wheel loaded state and wheel not loaded state, hydraulic
Good signal is divided into hydraulic kilter and hydraulic not kilter, and force motor current signal is divided into force motor electric current greater than electric current
Threshold status and force motor electric current are less than or equal to current threshold state；
The dynamic pressure signal itself acquired, wheel are carried signal, hydraulic good letter by the flight-control computer of each remaining
Number and force motor current signal Cross transfer give other 3 flight-control computers, make the every of four redundance flight control systems computers
A remaining all obtains the dynamic pressure signal and wheel carrying signal of 4 remainings；
Step 2,
The flight-control computer of each remaining puts to the vote to dynamic pressure signal and wheel the carrying signal of 4 remainings, decides by vote
Current protection entry condition each group state value is generated afterwards, and wheel carrying signal provides voting using the same method unanimously decided by vote entirely
It as a result is wheel loaded state or wheel not loaded state；The method that dynamic pressure signal uses majority voting, to dynamic after voting
Signal is pressed to carry out state processing, dynamic pressure signal condition is divided into dynamic pressure and is less than or equal to dynamic pressure threshold greater than dynamic pressure threshold status and dynamic pressure
State of value；The detailed content of majority voting may refer to " fly-by-wire flight control system ", author: Song Xianggui, Zhang Xinguo, and 2003
It publishes, National Defense Industry Press.
Step 3,
Some redundance flight control systems computer of four On A Redundant Flight Control Systems is full when current protection entry condition state value
Foot: dynamic pressure signal condition is that dynamic pressure is less than or equal to dynamic pressure threshold status or wheel carrying signal when being wheel loaded state,
Determine that the current protection entry condition of the redundance flight control systems computer meets, enters step 4；Otherwise, it is determined that the redundant flight
The current protection entry condition of control computer is unsatisfactory for；
Step 4,
When some redundance flight control systems computer of four On A Redundant Flight Control Systems meets current protection entry condition, this is remaining
Degree flight control system enters current protection program: if wheel carrying signal is wheel loaded state or dynamic pressure signal condition
Being less than or equal to dynamic pressure threshold status, force motor current signal for dynamic pressure is that force motor electric current is greater than current threshold state, hydraulic
Good signal is that three conditions of hydraulic not kilter meet simultaneously, and the state continues 10 minutes, cuts off this redundant flight
The force motor of the horizontal tail Servo-controller of control system is powered；
After certain On A Redundant Flight Control System enters current protection program, there is any one following condition and meet: wheel
Carrying signal is that loaded state, dynamic pressure signal condition are not that dynamic pressure is greater than dynamic pressure threshold status, hydraulic good signal is liquid to wheel
Press kilter, continuous 100 milliseconds of force motor current signal for force motor electric current be less than or equal to current threshold state when, this is remaining
Degree flight control system exits current protection；
Wherein, in step 2 signal it is complete with the method unanimously decided by vote are as follows: when the state of four remaining discrete input signals is uniform
It causes, vote value takes the state value of the remaining discrete input signal；When as long as four remaining discrete input signals have the letter of a remaining
Number state is different from other remainings, determines that the remaining is faulty, and vote value takes failure safe value, and wheel carries the failure peace of signal
Total head is wheel not loaded state.
Embodiment
A kind of the step of control method of Servo-controller current protection, this method, is:
The acquisition of step 1, signal:
Each remaining acquisition dynamic pressure signal connected to it, the wheel of four redundance flight control systems computers carry signal, liquid
Press good signal and force motor current signal；Wheel carrying signal is divided into wheel loaded state and wheel not loaded state, hydraulic
Good signal is divided into hydraulic kilter and hydraulic not kilter, and force motor current signal is divided into force motor electric current greater than electric current
Threshold status and force motor electric current are less than or equal to current threshold state；
The dynamic pressure signal itself acquired, wheel are carried signal, hydraulic good letter by the flight-control computer of each remaining
Number and force motor current signal Cross transfer give other 3 flight-control computers, make the every of four redundance flight control systems computers
A remaining all obtains the dynamic pressure signal and wheel carrying signal of 4 remainings；
When it is implemented, wheel carrying signal is divided into " 0 " and " 1 " two states: state " 0 " indicates that wheel does not carry, shape
State " 1 " indicates wheel carrying；Hydraulic good signal is divided into " 0 " and " 1 " two states: state " 0 " indicates hydraulic not kilter,
State " 1 " indicates hydraulic kilter；Force motor current signal is divided into " 0 " and " 1 " two states: state " 0 " indicates force motor
Electric current is less than or equal to current threshold state, and state " 1 " indicates that force motor electric current is greater than current threshold state；
At this point, the wheel carrying signal that the flight-control computer of each remaining obtains 4 remainings is " 0 "；Each remaining
Flight-control computer obtain 4 remainings dynamic pressure signal, respectively 900,950,800,850；Four redundance flight control systems calculate
The hydraulic good signal that A, B, C, D redundance flight control systems computer of machine obtain is respectively " 0 ", " 1 ", " 1 ", " 1 "；Four remainings fly
Row control computer A, B, C, D redundance flight control systems computer obtain force motor current signal be respectively " 1 ", " 0 ", " 0 ",
"0"；
The voting and processing of step 2, signal:
The flight-control computer of each remaining puts to the vote to dynamic pressure signal and wheel the carrying signal of 4 remainings, decides by vote
Current protection entry condition each group state value is generated afterwards, and wheel carrying signal provides voting using the same method unanimously decided by vote entirely
It as a result is wheel loaded state or wheel not loaded state；The method that dynamic pressure signal uses majority voting, to dynamic after voting
Signal is pressed to carry out state processing, dynamic pressure signal condition is divided into dynamic pressure and is less than or equal to dynamic pressure threshold greater than dynamic pressure threshold status and dynamic pressure
State of value；
The complete same specific implementation unanimously decided by vote are as follows:
The four remaining wheels carrying signal of the flight-control computer of each remaining is state " 0 ", provides voting result
Indicate that wheel does not carry for " 0 "；
The specific implementation of majority voting are as follows:
The dynamic pressure signal of 4 remainings of the flight-control computer of each remaining, respectively 900,950,800,850, to this 4
A signal carries out majority voting, wherein monitoring threshold value is 100, under the conditions of four remainings signal vote value choose second largest value with it is secondary small
The mean value of value, the vote value for providing dynamic pressure signal is 875；
State processing is carried out to the dynamic pressure signal after voting, when it is implemented, dynamic pressure signal is divided into " 0 " and " 1 " two shapes
State: state " 0 " indicates that dynamic pressure is less than or equal to dynamic pressure threshold value, and state " 1 " indicates that dynamic pressure is greater than dynamic pressure threshold value；Dynamic pressure threshold value is
1000；At this point, the dynamic pressure signal condition of the flight-control computer of each remaining is " 0 "；
Step 3,
Some redundance flight control systems computer of four On A Redundant Flight Control Systems is full when current protection entry condition state value
Foot: dynamic pressure signal condition is that dynamic pressure is less than or equal to dynamic pressure threshold status or wheel carrying signal when being wheel loaded state,
Determine that the current protection entry condition of the redundance flight control systems computer meets, enters step 4；Otherwise, it is determined that the redundant flight
The current protection entry condition of control computer is unsatisfactory for；
When it is implemented, the wheel carrying signal of each redundance flight control systems computer of four On A Redundant Flight Control Systems is equal
Indicate that wheel does not carry for " 0 "；The dynamic pressure signal condition of each redundance flight control systems computer of four On A Redundant Flight Control Systems
Indicate that dynamic pressure is less than or equal to dynamic pressure threshold value for " 0 "；Therefore, four On A Redundant Flight Control Systems are all satisfied the pneumatic item of current protection
Part；
Step 4,
When some redundance flight control systems computer of four On A Redundant Flight Control Systems meets current protection entry condition, this is remaining
Degree flight control system enters current protection program: if wheel carrying signal is wheel loaded state or dynamic pressure signal condition
Being less than or equal to dynamic pressure threshold status, force motor current signal for dynamic pressure is that force motor electric current is greater than current threshold state, hydraulic
Good signal is that three conditions of hydraulic not kilter meet simultaneously, and the state continues 10 minutes, cuts off this redundant flight
The force motor of the horizontal tail Servo-controller of control system is powered；
After certain On A Redundant Flight Control System enters current protection program, there is any one following condition and meet: wheel
Carrying signal is that loaded state, dynamic pressure signal condition are not that dynamic pressure is greater than dynamic pressure threshold status, hydraulic good signal is liquid to wheel
Press kilter, continuous 100 milliseconds of force motor current signal for force motor electric current be less than or equal to current threshold state when, this is remaining
Degree flight control system exits current protection.
When it is implemented, four On A Redundant Flight Control Systems enter current protection program: four redundance flight control systems computers
A redundance flight control systems computer obtain hydraulic good signal be respectively " 0 ", the A remaining of four redundance flight control systems computers
The force motor current signal that flight-control computer obtains is respectively " 1 ", and the state continues 10 minutes, therefore is cut off more than A
Spend the force motor power supply of the horizontal tail Servo-controller of flight control system；
The hydraulic good signal that B, C, D redundance flight control systems computers of four redundance flight control systems computers obtains is respectively
"1","1","1"；The force motor current signal that B, C, D redundance flight control systems computer of four redundance flight control systems computers obtain
Respectively " 0 ", " 0 ", " 0 " are unsatisfactory for the condition of current protection, therefore B, C, D On A Redundant Flight Control System exit current protection.
Claims (2)
1. a kind of control method of Servo-controller current protection, which is characterized in that the step of this method is:
Step 1,
Each remainings of four redundance flight control systems computers acquires dynamic pressure signal connected to it, wheel carrying signal, hydraulic good
Good signal and force motor current signal；Wheel carrying signal is divided into wheel loaded state and wheel not loaded state, hydraulic good
Signal is divided into hydraulic kilter and hydraulic not kilter, and force motor current signal is divided into force motor electric current greater than current threshold
State and force motor electric current are less than or equal to current threshold state；
The flight-control computer of each remaining by the dynamic pressure signal itself acquired, wheel carrying signal, hydraulic good signal and
Force motor current signal Cross transfer gives other 3 flight-control computers, keeps each of four redundance flight control systems computers remaining
Degree all obtains the dynamic pressure signal and wheel carrying signal of 4 remainings；
Step 2,
The flight-control computer of each remaining puts to the vote to dynamic pressure signal and wheel the carrying signal of 4 remainings, raw after voting
At current protection entry condition each group state value, wheel carrying signal provides voting result using the same method unanimously decided by vote entirely
For wheel loaded state or wheel not loaded state；The method that dynamic pressure signal uses majority voting believes the dynamic pressure after voting
Number state processing is carried out, dynamic pressure signal condition is divided into dynamic pressure and is less than or equal to dynamic pressure threshold value shape greater than dynamic pressure threshold status and dynamic pressure
State；
Step 3,
Some redundance flight control systems computer of four On A Redundant Flight Control Systems meets when current protection entry condition state value: dynamic
Pressure signal condition is that dynamic pressure is less than or equal to dynamic pressure threshold status or wheel carrying signal when being wheel loaded state, and determining should
The current protection entry condition of redundance flight control systems computer meets, and enters step 4；Otherwise, it is determined that the redundance flight control systems meter
The current protection entry condition of calculation machine is unsatisfactory for；
Step 4,
When some redundance flight control systems computer of four On A Redundant Flight Control Systems meets current protection entry condition, which flies
Row control system enters current protection program: if wheel carrying signal is that wheel loaded state or dynamic pressure signal condition are
Pressure is less than or equal to dynamic pressure threshold status, force motor current signal is that force motor electric current is greater than current threshold state, hydraulic good
Signal is that three conditions of hydraulic not kilter meet simultaneously, and the state that three conditions meet simultaneously continues 10 minutes, cuts
Except the force motor power supply of the horizontal tail Servo-controller of this On A Redundant Flight Control System；
After certain On A Redundant Flight Control System enters current protection program, there is any one following condition and meet: wheel carrying
Signal is that loaded state, dynamic pressure signal condition are not that dynamic pressure is greater than dynamic pressure threshold status, hydraulic good signal is hydraulic good to wheel
Continuous 100 milliseconds of good state, force motor current signal for force motor electric current be less than or equal to current threshold state when, the remaining fly
Row control system exits current protection.
2. a kind of control method of Servo-controller current protection as described in claim 1, which is characterized in that signal in step 2
It is complete with the method unanimously decided by vote are as follows: when the state of four remaining discrete input signals is consistent, vote value takes the remaining discrete defeated
Enter the state value of signal；As long as sentencing when four remaining discrete input signals have the signal condition of a remaining different from other remainings
The fixed remaining is faulty, and vote value takes failure safe value, and the failure safe value that wheel carries signal is wheel not loaded state.
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| CN201510924628.5A CN106877292B (en) | 2015-12-11 | 2015-12-11 | A control method for current protection of servo steering gear |
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| CN201510924628.5A CN106877292B (en) | 2015-12-11 | 2015-12-11 | A control method for current protection of servo steering gear |
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| CN112731958B (en) * | 2020-12-01 | 2023-07-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for using wheel bearing signal based on speed protection |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102602382A (en) * | 2011-04-14 | 2012-07-25 | 中南大学 | Anti-skid braking controller for airplane |
| CN103516351A (en) * | 2012-06-18 | 2014-01-15 | 中国航空工业集团公司西安飞机设计研究所 | A four-redundancy simulation signal hardware voting circuit |
| CN103879552A (en) * | 2014-03-06 | 2014-06-25 | 西安邮电大学 | Current equalization control device of four-redundancy steering engine and current equalizing method thereof |
| CN105109671A (en) * | 2015-09-25 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Leading-edge flap control method |
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| WO2009025009A1 (en) * | 2007-08-21 | 2009-02-26 | Fujitsu Limited | Recording medium driver and method of measuring frictional characteristics |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102602382A (en) * | 2011-04-14 | 2012-07-25 | 中南大学 | Anti-skid braking controller for airplane |
| CN103516351A (en) * | 2012-06-18 | 2014-01-15 | 中国航空工业集团公司西安飞机设计研究所 | A four-redundancy simulation signal hardware voting circuit |
| CN103879552A (en) * | 2014-03-06 | 2014-06-25 | 西安邮电大学 | Current equalization control device of four-redundancy steering engine and current equalizing method thereof |
| CN105109671A (en) * | 2015-09-25 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Leading-edge flap control method |
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