CN106877292A - A kind of control method of Servo-controller current protection - Google Patents
A kind of control method of Servo-controller current protection Download PDFInfo
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- CN106877292A CN106877292A CN201510924628.5A CN201510924628A CN106877292A CN 106877292 A CN106877292 A CN 106877292A CN 201510924628 A CN201510924628 A CN 201510924628A CN 106877292 A CN106877292 A CN 106877292A
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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
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- 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
The invention belongs to the safety Design technology of flight control system; it is related to a kind of control method of Servo-controller current protection; when hydraulic system breaks down on machine, it is caused to damage or fail, it is necessary to the force motor for cutting off horizontal tail Servo-controller is powered for the force motor for preventing horizontal tail Servo-controller is overheated：Signal sampling and processing is carried out first, obtains dynamic pressure signal, wheel carrying signal, hydraulic pressure good signal and force motor current signal, and carry out Cross transfer and signal voting；The condition criterion of current protection startup is carried out, under conditions of dynamic pressure signal vote value is smaller or wheel carries vote value to carry, starting current protection, otherwise not starting current protection；The condition criterion of current protection is carried out, if occurring the amplitude of force motor electric current and duration during hydraulic fault more than regulation requirement, the force motor for cutting off horizontal tail Servo-controller is powered.
Description
Technical field
The invention belongs to flight control system safety Design technology, it is related to flight control system
The improvement of the current protection strategy of horizontal tail Servo-controller.
Background technology
Horizontal tail Servo-controller in aircraft flight control system is watched using direct drive valve type
Steering wheel is taken, wherein, direct drive valve is driven as servo-controlled core component by force motor
It is dynamic, and force motor is driven by SERVO CONTROL power output motor current.When aircraft in the air and ground
When face is normally run, the horizontal tail servo of flight control system realizes closed-loop control, and force motor only can
There is of short duration electric current；And work as aircraft and occur hydraulic pressure good signal in ground maintenance and be continuously liquid
When pressing not kilter, the horizontal tail servo of flight control system cannot realize closed-loop control, power horse
Up to lasting high current occurs, causing force motor to overheat causes it to damage or fail, and now needs
Increase current protection method, the force motor for cutting off horizontal tail Servo-controller is powered.
The condition that conventional current protection starts is by manually operated, when aircraft is tieed up in ground
, it is necessary to ensure wheel carrying signal for wheel loaded state by ground maintenance personnel during shield, with this
Starting current is protected.This conventional current protection Starting mode can not meet the Gao An of aircraft
Entirely, highly reliable working service requirement, it has the disadvantage：Firstth, attended operation is complicated, efficiency
Difference is, it is necessary to artificial control wheel carrying signal for wheel loaded state, it is ensured that meet current protection
The condition of startup；Secondth, safety and reliability is poor, manually carries out current protection entry condition
Control when, artificial maloperation or possibility of forgetting cause the current protection of horizontal tail servo not start,
Cause the force motor of horizontal tail Servo-controller to overheat, influence the security of horizontal tail Servo-controller.
The content of the invention
The purpose of the present invention is：The present invention proposes a kind of controlling party of Servo-controller current protection
Method is reliable, effective, it is to avoid artificial maloperation or possibility of forgetting are led when aircraft is in ground maintenance
The horizontal tail servo current protection of cause does not start, and causes the force motor of horizontal tail Servo-controller to fail, and protects
The security of horizontal tail Servo-controller current protection is demonstrate,proved, maintenance efficiency is lifted, aircraft flight control is met
System internal field processed, the demand of flight-line service.
The technical scheme is that：
The step of a kind of control method of Servo-controller current protection, this method is：
Step 1,
Each remaining of four redundance flight control systems computers gathers connected dynamic pressure signal, machine
Wheel carrying signal, hydraulic pressure good signal and force motor current signal；Wheel carrying signal is divided into machine
Loaded state and wheel not loaded state are taken turns, hydraulic pressure good signal is divided into hydraulic pressure kilter and liquid
Pressure not kilter, force motor current signal be divided into force motor electric current more than current threshold state and
Force motor electric current is less than or equal to current threshold state；
Dynamic pressure signal, wheel carrying letter that the flight-control computer of each remaining itself will be gathered
Number, hydraulic pressure good signal and force motor current signal Cross transfer give other 3 flight control meters
Calculation machine, makes each remaining of four redundance flight control systems computers obtain the dynamic pressure signal of 4 remainings
With wheel carrying signal；
Step 2,
The flight-control computer of each remaining carries letter to the dynamic pressure signal and wheel of 4 remainings
Number put to the vote, current protection entry condition each group state value is generated after voting, wheel carries letter
The full method with consistent voting of number use, provides voting result for wheel loaded state or wheel
Not loaded state；Dynamic pressure signal is entered using the method for majority voting to the dynamic pressure signal after voting
Row state processing, dynamic pressure signal condition be divided into dynamic pressure be less than more than dynamic pressure threshold status and dynamic pressure or
Equal to dynamic pressure threshold status；
Step 3,
Certain redundance flight control systems computer of four On A Redundant Flight Control Systems is opened when current protection
Dynamic cond value meets：Dynamic pressure signal condition be dynamic pressure less than or equal to dynamic pressure threshold status or
When person's wheel carrying signal is wheel loaded state, the electricity of the redundance flight control systems computer is judged
Stream protection entry condition meets, into step 4；Otherwise, it is determined that the redundance flight control systems are calculated
The current protection entry condition of machine is unsatisfactory for；
Step 4,
Protected when certain redundance flight control systems computer of four On A Redundant Flight Control Systems meets electric current
Shield entry condition, the On A Redundant Flight Control System enters current protection program：If wheel is carried
Signal is wheel loaded state or dynamic pressure signal condition for dynamic pressure is less than or equal to dynamic pressure threshold value
State, force motor current signal are that force motor electric current is well believed more than current threshold state, hydraulic pressure
Number for hydraulic pressure, three conditions of kilter do not meet simultaneously, and the state continues 10 minutes,
The force motor for cutting off the horizontal tail Servo-controller of this On A Redundant Flight Control System is powered；
After certain On A Redundant Flight Control System enters current protection program, occur it is following any one
Condition meets：Wheel carrying signal is that loaded state, dynamic pressure signal condition are not that dynamic pressure is big to wheel
In dynamic pressure threshold status, hydraulic pressure good signal be hydraulic pressure kilter, force motor current signal connect
Continuous 100 milliseconds when being that force motor electric current is less than or equal to current threshold state, the redundant flight control
System processed exits current protection；
Wherein, the full method with consistent voting of signal is in step 2：When four remainings are discrete defeated
The state for entering signal is consistent, and vote value takes the state value of the remaining discrete input signal；When four
As long as remaining discrete input signal has a signal condition for remaining different from other remainings, judge
The remaining is faulty, and vote value takes failure safe value, and the failure safe value of wheel carrying signal is
Wheel not loaded state.
It is an advantage of the invention that：The invention enables aircraft in ground maintenance, can be automatically performed
The current protection of horizontal tail Servo-controller starts, it is to avoid because artificial maloperation or possibility of forgetting are led
The horizontal tail servo current protection of cause does not start, and causes the force motor of horizontal tail Servo-controller to fail, and protects
The security of horizontal tail Servo-controller current protection is demonstrate,proved, maintenance efficiency is lifted, aircraft flight control is met
System internal field processed, the demand of flight-line service.
Specific embodiment
Operation principle of the invention is：Method is started using automatic current protection so that aircraft
The force motor superheating phenomenon that may occur is prevented in ground maintenance, horizontal tail servorudder is improved electromechanical
The security of protection is flowed, the demand of aircraft flight control system internal field, flight-line service is met.When
When aircraft is in ground maintenance, flight-control computer is carried according to dynamic pressure signal condition, wheel
Signal, carries out the condition judgment of current protection startup, by obtaining what horizontal tail servo current was protected
Each cond value, judges whether to cut off the horizontal tail servorudder of this remaining passage flight control system
The force motor of machine is powered.
The step of a kind of control method of Servo-controller current protection, this method is：
Step 1,
Each remaining of four redundance flight control systems computers gathers connected dynamic pressure signal, machine
Wheel carrying signal, hydraulic pressure good signal and force motor current signal；Wheel carrying signal is divided into machine
Loaded state and wheel not loaded state are taken turns, hydraulic pressure good signal is divided into hydraulic pressure kilter and liquid
Pressure not kilter, force motor current signal be divided into force motor electric current more than current threshold state and
Force motor electric current is less than or equal to current threshold state；
Dynamic pressure signal, wheel carrying letter that the flight-control computer of each remaining itself will be gathered
Number, hydraulic pressure good signal and force motor current signal Cross transfer give other 3 flight control meters
Calculation machine, makes each remaining of four redundance flight control systems computers obtain the dynamic pressure signal of 4 remainings
With wheel carrying signal；
Step 2,
The flight-control computer of each remaining carries letter to the dynamic pressure signal and wheel of 4 remainings
Number put to the vote, current protection entry condition each group state value is generated after voting, wheel carries letter
The full method with consistent voting of number use, provides voting result for wheel loaded state or wheel
Not loaded state；Dynamic pressure signal is entered using the method for majority voting to the dynamic pressure signal after voting
Row state processing, dynamic pressure signal condition be divided into dynamic pressure be less than more than dynamic pressure threshold status and dynamic pressure or
Equal to dynamic pressure threshold status；The detailed content of majority voting may refer to《Fax flight control system
System》, author：Song Xianggui, Zhang Xinguo, publish, National Defense Industry Press for 2003.
Step 3,
Certain redundance flight control systems computer of four On A Redundant Flight Control Systems is opened when current protection
Dynamic cond value meets：Dynamic pressure signal condition be dynamic pressure less than or equal to dynamic pressure threshold status or
When person's wheel carrying signal is wheel loaded state, the electricity of the redundance flight control systems computer is judged
Stream protection entry condition meets, into step 4；Otherwise, it is determined that the redundance flight control systems are calculated
The current protection entry condition of machine is unsatisfactory for；
Step 4,
Protected when certain redundance flight control systems computer of four On A Redundant Flight Control Systems meets electric current
Shield entry condition, the On A Redundant Flight Control System enters current protection program：If wheel is carried
Signal is wheel loaded state or dynamic pressure signal condition for dynamic pressure is less than or equal to dynamic pressure threshold value
State, force motor current signal are that force motor electric current is well believed more than current threshold state, hydraulic pressure
Number for hydraulic pressure, three conditions of kilter do not meet simultaneously, and the state continues 10 minutes,
The force motor for cutting off the horizontal tail Servo-controller of this On A Redundant Flight Control System is powered；
After certain On A Redundant Flight Control System enters current protection program, occur it is following any one
Condition meets：Wheel carrying signal is that loaded state, dynamic pressure signal condition are not that dynamic pressure is big to wheel
In dynamic pressure threshold status, hydraulic pressure good signal be hydraulic pressure kilter, force motor current signal connect
Continuous 100 milliseconds when being that force motor electric current is less than or equal to current threshold state, the redundant flight control
System processed exits current protection；
Wherein, the full method with consistent voting of signal is in step 2：When four remainings are discrete defeated
The state for entering signal is consistent, and vote value takes the state value of the remaining discrete input signal；When four
As long as remaining discrete input signal has a signal condition for remaining different from other remainings, judge
The remaining is faulty, and vote value takes failure safe value, and the failure safe value of wheel carrying signal is
Wheel not loaded state.
Embodiment
The step of a kind of control method of Servo-controller current protection, this method is：
1st step, the acquisition of signal：
Each remaining of four redundance flight control systems computers gathers connected dynamic pressure signal, machine
Wheel carrying signal, hydraulic pressure good signal and force motor current signal；Wheel carrying signal is divided into machine
Loaded state and wheel not loaded state are taken turns, hydraulic pressure good signal is divided into hydraulic pressure kilter and liquid
Pressure not kilter, force motor current signal be divided into force motor electric current more than current threshold state and
Force motor electric current is less than or equal to current threshold state；
Dynamic pressure signal, wheel carrying letter that the flight-control computer of each remaining itself will be gathered
Number, hydraulic pressure good signal and force motor current signal Cross transfer give other 3 flight control meters
Calculation machine, makes each remaining of four redundance flight control systems computers obtain the dynamic pressure signal of 4 remainings
With wheel carrying signal；
During specific implementation, wheel carrying signal is divided into " 0 " and " 1 " two states：State " 0 "
Represent that wheel is not carried, state " 1 " represents that wheel is carried；Hydraulic pressure good signal is divided into " 0 "
" 1 " two states：State " 0 " represents hydraulic pressure not kilter, and state " 1 " is represented
Hydraulic pressure kilter；Force motor current signal is divided into " 0 " and " 1 " two states：State " 0 "
Represent that force motor electric current is less than or equal to current threshold state, state " 1 " represents force motor electricity
Stream is more than current threshold state；
Now, the flight-control computer of each remaining obtains the wheel carrying signal of 4 remainings
It is " 0 "；The flight-control computer of each remaining obtains the dynamic pressure signal of 4 remainings, respectively
900、950、800、850；A, B, C, D remaining of four redundance flight control systems computers fly
The hydraulic pressure good signal that row control computer is obtained is respectively " 0 ", " 1 ", " 1 ", " 1 "；Four
The power horse that A, B, C, D redundance flight control systems computer of redundance flight control systems computer are obtained
" 1 ", " 0 ", " 0 ", " 0 " are respectively up to current signal；
The voting and treatment of the 2nd step, signal：
The flight-control computer of each remaining carries letter to the dynamic pressure signal and wheel of 4 remainings
Number put to the vote, current protection entry condition each group state value is generated after voting, wheel carries letter
The full method with consistent voting of number use, provides voting result for wheel loaded state or wheel
Not loaded state；Dynamic pressure signal is entered using the method for majority voting to the dynamic pressure signal after voting
Row state processing, dynamic pressure signal condition be divided into dynamic pressure be less than more than dynamic pressure threshold status and dynamic pressure or
Equal to dynamic pressure threshold status；
Complete being embodied as with consistent voting：
Four remaining wheel carrying signals of the flight-control computer of each remaining are state
" 0 ", provides voting result for " 0 " represents that wheel is not carried；
Majority voting is embodied as：
The dynamic pressure signal of 4 remainings of the flight-control computer of each remaining, respectively 900,
950th, 800,850, majority voting is carried out to this 4 signals, wherein, monitoring threshold value is 100,
Signal vote value chooses the average of second largest value and sub-minimum under the conditions of four remainings, provides dynamic pressure signal
Vote value be 875；
State processing is carried out to the dynamic pressure signal after voting, during specific implementation, dynamic pressure signal is divided into
" 0 " and " 1 " two states：State " 0 " represents that dynamic pressure is less than or equal to dynamic pressure threshold value,
State " 1 " represents that dynamic pressure is more than dynamic pressure threshold value；Dynamic pressure threshold value is 1000；Now, more than each
The dynamic pressure signal condition of the flight-control computer of degree is " 0 "；
Step 3,
Certain redundance flight control systems computer of four On A Redundant Flight Control Systems is opened when current protection
Dynamic cond value meets：Dynamic pressure signal condition be dynamic pressure less than or equal to dynamic pressure threshold status or
When person's wheel carrying signal is wheel loaded state, the electricity of the redundance flight control systems computer is judged
Stream protection entry condition meets, into step 4；Otherwise, it is determined that the redundance flight control systems are calculated
The current protection entry condition of machine is unsatisfactory for；
During specific implementation, each redundance flight control systems computer of four On A Redundant Flight Control Systems
Wheel carrying signal is " 0 " and represents that wheel is not carried；Four On A Redundant Flight Control Systems it is every
The dynamic pressure signal condition of individual redundance flight control systems computer is that " 0 " represents that dynamic pressure is less than or equal to
Dynamic pressure threshold value；Therefore, four On A Redundant Flight Control Systems are satisfied by current protection aerodynamic conditions；
Step 4,
Protected when certain redundance flight control systems computer of four On A Redundant Flight Control Systems meets electric current
Shield entry condition, the On A Redundant Flight Control System enters current protection program：If wheel is carried
Signal is wheel loaded state or dynamic pressure signal condition for dynamic pressure is less than or equal to dynamic pressure threshold value
State, force motor current signal are that force motor electric current is well believed more than current threshold state, hydraulic pressure
Number for hydraulic pressure, three conditions of kilter do not meet simultaneously, and the state continues 10 minutes,
The force motor for cutting off the horizontal tail Servo-controller of this On A Redundant Flight Control System is powered；
After certain On A Redundant Flight Control System enters current protection program, occur it is following any one
Condition meets：Wheel carrying signal is that loaded state, dynamic pressure signal condition are not that dynamic pressure is big to wheel
In dynamic pressure threshold status, hydraulic pressure good signal be hydraulic pressure kilter, force motor current signal connect
Continuous 100 milliseconds when being that force motor electric current is less than or equal to current threshold state, the redundant flight control
System processed exits current protection.
During specific implementation, four On A Redundant Flight Control Systems enter current protection program：Four remainings
The hydraulic pressure good signal difference that the A redundance flight control systems computer of flight-control computer is obtained
It is " 0 ", the power horse of the A redundance flight control systems computer acquisition of four redundance flight control systems computers
It is respectively " 1 " up to current signal, and the state continues 10 minutes, therefore excision A remainings
The force motor of the horizontal tail Servo-controller of flight control system is powered；
The liquid that B, C, D redundance flight control systems computer of four redundance flight control systems computers are obtained
Pressure good signal is respectively " 1 ", " 1 ", " 1 "；The B of four redundance flight control systems computers, C,
The force motor current signal that D redundance flight control systems computer is obtained is respectively " 0 ", " 0 ", " 0 ",
The condition of current protection is unsatisfactory for, therefore B, C, D On A Redundant Flight Control System exit electric current guarantor
Shield.
Claims (2)
1. a kind of control method of Servo-controller current protection, it is characterised in that this method
Step is：
Step 1,
Each remaining of four redundance flight control systems computers gathers connected dynamic pressure signal, machine
Wheel carrying signal, hydraulic pressure good signal and force motor current signal；Wheel carrying signal is divided into machine
Loaded state and wheel not loaded state are taken turns, hydraulic pressure good signal is divided into hydraulic pressure kilter and liquid
Pressure not kilter, force motor current signal be divided into force motor electric current more than current threshold state and
Force motor electric current is less than or equal to current threshold state；
Dynamic pressure signal, wheel carrying letter that the flight-control computer of each remaining itself will be gathered
Number, hydraulic pressure good signal and force motor current signal Cross transfer give other 3 flight control meters
Calculation machine, makes each remaining of four redundance flight control systems computers obtain the dynamic pressure signal of 4 remainings
With wheel carrying signal；
Step 2,
The flight-control computer of each remaining carries letter to the dynamic pressure signal and wheel of 4 remainings
Number put to the vote, current protection entry condition each group state value is generated after voting, wheel carries letter
The full method with consistent voting of number use, provides voting result for wheel loaded state or wheel
Not loaded state；Dynamic pressure signal is entered using the method for majority voting to the dynamic pressure signal after voting
Row state processing, dynamic pressure signal condition be divided into dynamic pressure be less than more than dynamic pressure threshold status and dynamic pressure or
Equal to dynamic pressure threshold status；
Step 3,
Certain redundance flight control systems computer of four On A Redundant Flight Control Systems is opened when current protection
Dynamic cond value meets：Dynamic pressure signal condition be dynamic pressure less than or equal to dynamic pressure threshold status or
When person's wheel carrying signal is wheel loaded state, the electricity of the redundance flight control systems computer is judged
Stream protection entry condition meets, into step 4；Otherwise, it is determined that the redundance flight control systems are calculated
The current protection entry condition of machine is unsatisfactory for；
Step 4,
Protected when certain redundance flight control systems computer of four On A Redundant Flight Control Systems meets electric current
Shield entry condition, the On A Redundant Flight Control System enters current protection program：If wheel is carried
Signal is wheel loaded state or dynamic pressure signal condition for dynamic pressure is less than or equal to dynamic pressure threshold value
State, force motor current signal are that force motor electric current is well believed more than current threshold state, hydraulic pressure
Number for hydraulic pressure, three conditions of kilter do not meet simultaneously, and the state continues 10 minutes,
The force motor for cutting off the horizontal tail Servo-controller of this On A Redundant Flight Control System is powered；
After certain On A Redundant Flight Control System enters current protection program, occur it is following any one
Condition meets：Wheel carrying signal is that loaded state, dynamic pressure signal condition are not that dynamic pressure is big to wheel
In dynamic pressure threshold status, hydraulic pressure good signal be hydraulic pressure kilter, force motor current signal connect
Continuous 100 milliseconds when being that force motor electric current is less than or equal to current threshold state, the redundant flight control
System processed exits current protection.
2. a kind of control method of Servo-controller current protection as claimed in claim 1, its
It is characterised by, the full method with consistent voting of signal is in the 2nd step：When four remainings are discrete defeated
The state for entering signal is consistent, and vote value takes the state value of the remaining discrete input signal；When four
As long as remaining discrete input signal has a signal condition for remaining different from other remainings, judge
The remaining is faulty, and vote value takes failure safe value, and the failure safe value of wheel carrying signal is
Wheel not loaded state.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112731958A (en) * | 2020-12-01 | 2021-04-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne wheel-borne signal using method based on speed protection |
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| 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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| CN112731958A (en) * | 2020-12-01 | 2021-04-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne wheel-borne signal using method based on speed protection |
| 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 |
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