CN106741861A - A kind of bipolar direct drive valve actuator current protection strategy - Google Patents
A kind of bipolar direct drive valve actuator current protection strategy Download PDFInfo
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- CN106741861A CN106741861A CN201611126452.XA CN201611126452A CN106741861A CN 106741861 A CN106741861 A CN 106741861A CN 201611126452 A CN201611126452 A CN 201611126452A CN 106741861 A CN106741861 A CN 106741861A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
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- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The present invention relates to a kind of bipolar direct drive valve actuator current protection strategy, the force motor state for controlling Servo-controller in flight control system, including first：Signal acquisition, second：Signal transacting and voting, the 3rd：The condition criterion and the 4th that current protection starts：The condition criterion of current protection.Bipolar direct drive valve actuator current protection strategy of the invention causes aircraft in ground maintenance; the current protection that Servo-controller can be automatically performed starts; avoid because servo current protection does not start caused by artificial maloperation or possibility of forgetting; the force motor of Servo-controller is caused to fail; ensure the security of Servo-controller current protection; lifting maintenance efficiency, meets the demand of aircraft flight control system internal field, flight-line service.
Description
Technical field
The invention belongs to aircraft control technology field, more particularly to a kind of bipolar direct drive valve actuator current protection plan
Slightly.
Background technology
Flight control system increases surely from control, develops into fax (FBW) flight control system, and pass (FBL) winged control towards this light
The direction of system is developed；Actuator develops into fax combined type servo actuator also accordingly from hydaulic redundancy actuator, and towards
Flashlight passes power-by-wire (PBW) actuator direction to be developed.Develop to power-by-wire actuator in fax combined type actuator
During, occur in that direct drive valve (DDV) formula actuator, mainly solve combined type fax servo actuator complex structure, into
The problem of this height, reliability and maintainability difference.With developing rapidly for digital technology, system design is urgent with debugging flexibility
It is required that, the need for modern advanced control theory practical application, and high reliability Digital Transmission demand；It is required that actuator is watched
Dress system is developed from traditional analog servo system to redundancy digital type servo-drive system.
At present, domestic and international aircraft generally uses the electro-hydraulic combination servo actuator of servo valve (EHV) formula.In such combination servo
In actuator, electrohydraulic servo valve is a main source of trouble.If replacing watching using power or torque-motor direct drive mode
The hydraulic pressure amplifying stage of valve is taken, combination servo actuator structure will be greatly simplified, can significantly improve reliability.Therefore, it is understanding
Certainly the problem of EHV formulas combination servo actuator complex structure, high cost, reliability and maintainability difference, occurs in that direct drive valve
(DDV) formula actuator, and it is widely used in various Advanced Aircrafts.
The content of the invention
It is in order to avoid bipolar it is an object of the invention to provide a kind of bipolar direct drive valve actuator current protection strategy
There is steering wheel force motor in ground maintenance because high temperature causes O-ring seal and coil electric insulating properties in direct drive valve actuator
Failure so that Design of Flight Control has " force motor current protecting function ".
To reach above-mentioned purpose, the technical solution adopted by the present invention is：A kind of bipolar direct drive valve actuator electric current is protected
Shield strategy, the force motor state for controlling Servo-controller in flight control system, it is characterised in that including
1st step：Signal acquisition
1.1) each remaining of redundance flight control systems computer gathers connected dynamic pressure signal, wheel and carries letter first
Number, hydraulic pressure good signal and force motor current signal；
Wherein, the dynamic pressure signal is divided into dynamic pressure more than dynamic pressure threshold values state and dynamic pressure less than or equal to dynamic pressure threshold values shape
State, the wheel carrying signal is divided into wheel loaded state and not loaded state, and it is good that the hydraulic pressure good signal is divided into hydraulic pressure
State and not kilter, the force motor current signal are divided into force motor electric current more than current threshold state and force motor electric current
Less than or equal to current threshold state；
1.2) redundance flight control systems computer carries out signal cross transmission；By the Cross transfer of flight-control computer
Afterwards, each remaining of flight-control computer is made to obtain the signal such as including dynamic pressure signal and hydraulic pressure good signal；
2nd step：Signal is decided by vote and is processed
2.1) flight-control computer of each remaining is put to the vote to dynamic pressure signal and wheel carrying signal, raw after voting
Into current protection entry condition each group state value；
2.2) state processing is carried out to the dynamic pressure signal after voting；
3rd step：The condition criterion that current protection starts
Each remaining passage flight-control computer of On A Redundant Flight Control System works as current protection entry condition state value
State：Dynamic pressure signal condition be dynamic pressure less than or equal to dynamic pressure threshold status and wheel carrying signal be wheel loaded state simultaneously
When meeting, Cutoff current protection entry condition meets, into the 4th step；Otherwise, it is determined that current protection entry condition is unsatisfactory for；
4th step：The condition criterion of current protection
4.1) when any remaining passage flight-control computer of On A Redundant Flight Control System meets current protection trip bar
Part, the remaining passage flight control system enters current protection program；If wheel carrying signal is wheel loaded state, dynamic pressure
Signal condition is that dynamic pressure is less than or equal to dynamic pressure threshold status, and force motor current signal is that force motor electric current is more than current threshold
State of value, hydraulic pressure good signal are that four conditions of kilter do not meet hydraulic pressure simultaneously, and the state continues the first pre- timing
Between T1, then the force motor for cutting off the Servo-controller of the remaining passage flight control system powers；
4.2) after certain remaining passage flight control system enters current protection program, following any one condition occur expires
Foot；Wheel carrying signal is that loaded state, dynamic pressure signal condition are not that dynamic pressure is well believed more than dynamic pressure threshold status, hydraulic pressure to wheel
Number it is hydraulic pressure kilter, or force motor current signal continuous second scheduled time T2Force motor electric current is to be less than or equal to
During current threshold state, then the remaining passage flight control system exits current protection, and Servo-controller enters normal control state.
Further, in the 3rd step, voting is to carry out computing and according to certain rules output result to multiple signals or state
The process made decision, for general discrete magnitude, voting algorithm is effectively monitored using majority voting, four remaining RSTs,
Monitoring voting algorithm is as follows：Signal voting algorithm is：
If 1) itself and be " 4 ", all four remaining signals effectively, vote value be " 1 ", fault-free signal；
If 2) itself and be " 3 ", vote value is " 1 ", and " 0 " value signal is fault-signal；
If 3) itself and be " 1 ", vote value is " 0 ", and " 0 " value signal is fault-signal；
4)) if itself and be " 0 ", all four remaining signals effectively, vote value be " 0 ", fault-free signal.
Further, first scheduled time T1It is no less than 10 minutes.
Further, second scheduled time T2It is no less than 100 milliseconds.
Bipolar direct drive valve actuator current protection strategy of the invention causes that aircraft, can be automatic in ground maintenance
The current protection for completing Servo-controller starts, it is to avoid because servo current protection is not caused by artificial maloperation or possibility of forgetting
Start, cause the force motor of Servo-controller to fail, it is ensured that the security of Servo-controller current protection, lift maintenance efficiency, meet
Aircraft flight control system internal field, the demand of flight-line service.
Brief description of the drawings
Accompanying drawing herein is merged in specification and constitutes the part of this specification, shows and meets implementation of the invention
Example, and be used to explain principle of the invention together with specification.
Fig. 1 is bipolar direct drive valve actuator current protection strategic process figure of the invention.
Specific embodiment
To make the purpose, technical scheme and advantage of present invention implementation clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary type, it is intended to used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of the work of creation type is not made, belongs to the scope of protection of the invention.Under
Face is described in detail with reference to accompanying drawing to embodiments of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward " are based on accompanying drawing institute
The orientation or position relationship for showing, are for only for ease of the description present invention and simplify description, rather than the dress for indicating or implying meaning
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The limitation of scope.
The operation principle of bipolar direct drive valve actuator current protection strategy of the invention is：Protected using automatic electric current
Shield startup method so that aircraft prevents the force motor superheating phenomenon that may occur in ground maintenance, improves Servo-controller electric current
The security of protection, meets the demand of aircraft flight control system internal field, flight-line service.When aircraft is in ground maintenance, fly
Row control computer carries out the condition judgment of current protection startup according to dynamic pressure signal condition, wheel carrying signal, by obtaining
Each cond value of servo current protection, judges whether the power horse of the Servo-controller of excision this remaining passage flight control system
Up to power supply.
It is as shown in Figure 1 bipolar direct drive valve actuator current protection strategic process figure of the invention, rhombus is sentenced in figure
" ＆＆ in disconnected step " is logical operation "AND", " | | " it is logical operation "or".
Bipolar direct drive valve actuator current protection strategy of the invention includes
The first step：Signal acquisition
Each remaining of a, first four redundance flight control systems computers gathers connected dynamic pressure signal, wheel and carries letter
Number, hydraulic pressure good signal and force motor current signal；
Wheel carrying signal is divided into wheel loaded state and wheel not loaded state --- for characterizing the state of ground, hydraulic pressure
Good signal is divided into hydraulic pressure kilter and hydraulic pressure not kilter --- for characterizing servo pressurized strut hydraulic energy source state, power
Motor current signal is divided into force motor electric current more than current threshold state and force motor electric current less than or equal to current threshold state,
Dynamic pressure signal condition is divided into dynamic pressure and is less than or equal to dynamic pressure threshold status more than certain dynamic pressure threshold status and dynamic pressure --- it is used for
Characterize air speed；
B, four redundance flight control systems computers carry out signal cross transmission；By the intersection of four redundance flight control systems computers
After transmission, each remaining of four redundance flight control systems computers is set to obtain dynamic pressure signal and wheel carrying signal of 4 remainings etc.；
Second step：Signal is decided by vote and is processed
Voting is that multiple signals (or state) are carried out with computing and the according to certain rules process of output result (making decision).
For general discrete magnitude, voting algorithm is effectively monitored using majority voting.
Four remaining RSTs, monitoring voting algorithm is as follows：
If 1) itself and be " 4 ", all four remaining signals effectively, vote value be " 1 ", fault-free signal；
If 2) itself and be " 3 ", effectively, vote value is " 1 " to triplex redundance signal, and " 0 " value signal is fault-signal；
If 3) itself and be " 1 ", effectively, vote value is " 0 " to a remaining signal, and " 1 " value signal is fault-signal；
If 4) itself and be " 0 ", without remaining signal effectively, then all four remaining signals effectively, vote value be " 0 ", without reason
Barrier signal；
It should be noted that during when it and for " 2 ", that is, showing that two remaining signals are effective, it is impossible to judged, i.e., do not carried out
Voting.
Note：" and " implication be exactly that numeral 1 is designated as when certain signal is effective, multiple signals have many numbers when effective
Word 1, by the work of multiple numeral 1 and as in the present invention " and ".
C, the flight-control computer of each remaining are put to the vote to the dynamic pressure signal and wheel carrying signal of 4 remainings, table
Current protection entry condition each group state value is generated after certainly；
D, state processing is carried out to the dynamic pressure signal after voting, dynamic pressure signal condition is divided into dynamic pressure more than dynamic pressure threshold status
Dynamic pressure threshold status are less than or equal to dynamic pressure；
3rd step：The condition criterion that current protection starts
Each remaining passage flight-control computer of four On A Redundant Flight Control Systems works as current protection entry condition state
Value meets simultaneously：Dynamic pressure signal condition is that dynamic pressure is that wheel carries shape less than or equal to dynamic pressure threshold status, wheel carrying signal
During state, Cutoff current protection entry condition meets, then into the 4th step；Otherwise, it is determined that current protection entry condition is unsatisfactory for；
4th step：The condition criterion of current protection
E, current protection trip bar is met when certain remaining passage flight-control computer of four On A Redundant Flight Control Systems
Part, the remaining passage flight control system enters current protection program；If wheel carrying signal is wheel loaded state, dynamic pressure
Signal condition is that dynamic pressure is that force motor electric current is more than current threshold shape less than or equal to dynamic pressure threshold status, force motor current signal
State, hydraulic pressure good signal be hydraulic pressure not four conditions of kilter simultaneously meet, and the state continue 10 minutes (first make a reservation for
Time), the force motor for cutting off the horizontal tail Servo-controller of this remaining passage flight control system is powered；
F, after certain remaining passage flight control system enters current protection program, following any one condition occur expires
Foot；Wheel carrying signal is that loaded state, dynamic pressure signal condition are not that dynamic pressure is well believed more than dynamic pressure threshold status, hydraulic pressure to wheel
Number be hydraulic pressure kilter, continuous 100 milliseconds of force motor current signal (second scheduled time) be force motor electric current be less than or wait
When current threshold state, the remaining passage flight control system exits current protection.
Bipolar direct drive valve actuator current protection strategy of the invention causes that aircraft, can be automatic in ground maintenance
The current protection for completing Servo-controller starts, it is to avoid because servo current protection is not caused by artificial maloperation or possibility of forgetting
Start, cause the force motor of Servo-controller to fail, it is ensured that the security of Servo-controller current protection, lift maintenance efficiency, meet
Aircraft flight control system internal field, the demand of flight-line service.
The above, optimal specific embodiment only of the invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can be readily occurred in,
Should all be included within the scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Enclose and be defined.
Claims (5)
1. a kind of bipolar direct drive valve actuator current protection strategy, the power for controlling Servo-controller in flight control system
Motor condition, it is characterised in that including
1st step：Signal acquisition
1.1) first each remaining of redundance flight control systems computer gather connected dynamic pressure signal, wheel carrying signal,
Hydraulic pressure good signal and force motor current signal；
Wherein, the dynamic pressure signal is divided into dynamic pressure more than dynamic pressure threshold values state and dynamic pressure less than or equal to dynamic pressure threshold values state, institute
State wheel carrying signal and be divided into wheel loaded state and not loaded state, the hydraulic pressure good signal be divided into hydraulic pressure kilter and
Not kilter, the force motor current signal be divided into force motor electric current be less than more than current threshold state and force motor electric current or
Equal to current threshold state；
1.2) redundance flight control systems computer carries out signal cross transmission；By after the Cross transfer of flight-control computer, making
Each remaining of flight-control computer obtains including dynamic pressure signal, hydraulic pressure good signal and force motor current signal signal；
2nd step：Signal is decided by vote and is processed
2.1) flight-control computer of each remaining is put to the vote to dynamic pressure signal and wheel carrying signal, and electricity is generated after voting
Stream protection entry condition each group state value；
2.2) state processing is carried out to the dynamic pressure signal after voting；
3rd step：The condition criterion that current protection starts
Each remaining passage flight-control computer of On A Redundant Flight Control System works as current protection entry condition state state of value：
Dynamic pressure signal condition is dynamic pressure less than or equal to dynamic pressure threshold status and wheel carrying signal is that wheel loaded state meets simultaneously
When, Cutoff current protection entry condition meets, into the 4th step；Otherwise, it is determined that current protection entry condition is unsatisfactory for；
4th step：The condition criterion of current protection
4.1) when any remaining passage flight-control computer of On A Redundant Flight Control System meets current protection entry condition, should
Remaining passage flight control system enters current protection program；If wheel carrying signal is wheel loaded state, dynamic pressure signal
State is that dynamic pressure is less than or equal to dynamic pressure threshold status, and force motor current signal is that force motor electric current is more than current threshold shape
State, hydraulic pressure good signal are that four conditions of kilter do not meet hydraulic pressure simultaneously, and the state continues the first scheduled time T1,
The force motor for then cutting off the Servo-controller of the remaining passage flight control system is powered；
4.2) after certain remaining passage flight control system enters current protection program, there is following any one condition and meet；
Wheel carrying signal is that loaded state, dynamic pressure signal condition are not that dynamic pressure is more than dynamic pressure threshold status, hydraulic pressure good signal to wheel
It is hydraulic pressure kilter, or force motor current signal continuous second scheduled time T2Force motor electric current is less than or equal to electricity
During stream threshold status, then the remaining passage flight control system exits current protection, and Servo-controller enters normal control state.
2. bipolar direct drive valve actuator current protection strategy according to claim 1, it is characterised in that the 3rd step
In, voting is to multiple signals or state carries out computing and output result is made decision according to certain rules process, for general
Discrete magnitude, voting algorithm is effectively monitored using majority voting, and four remaining RSTs, monitoring voting algorithm is as follows
Signal voting algorithm is：
If 1) itself and be " 4 ", all four remaining signals effectively, vote value be " 1 ", fault-free signal；
If 2) itself and be " 3 ", vote value is " 1 ", and " 0 " value signal is fault-signal；
If 3) itself and be " 1 ", vote value is " 0 ", and " 0 " value signal is fault-signal；
4)) if itself and be " 0 ", all four remaining signals effectively, vote value be " 0 ", fault-free signal.
3. bipolar direct drive valve actuator current protection strategy according to claim 2, it is characterised in that if itself and be
" 2 ", do not put to the vote.
4. bipolar direct drive valve actuator current protection strategy according to claim 1, it is characterised in that described first
Scheduled time T1It is no less than 10 minutes.
5. bipolar direct drive valve actuator current protection strategy according to claim 1, it is characterised in that described second
Scheduled time T2It is no less than 100 milliseconds.
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| CN201611075312 | 2016-11-29 | ||
| CN2016110753124 | 2016-11-29 |
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| CN106741861B CN106741861B (en) | 2019-06-28 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111532418A (en) * | 2020-05-20 | 2020-08-14 | 中国商用飞机有限责任公司 | Aircraft high lift system |
| CN114002943A (en) * | 2021-09-30 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Architecture of backup system of telex flight control system |
| CN115145140A (en) * | 2022-06-07 | 2022-10-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Ground non-hydraulic protection logic algorithm for servo steering engine |
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| CN104743125A (en) * | 2015-03-09 | 2015-07-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Single-stage DDV steering engine current protecting strategy |
| CN105159373A (en) * | 2015-08-27 | 2015-12-16 | 北京精密机电控制设备研究所 | Power source switching circuit for multistage aerospace craft |
| CN105564637A (en) * | 2014-11-06 | 2016-05-11 | 申久祝 | Four-redundant direct current steering engine control system based on DSP |
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| US20110190965A1 (en) * | 2006-01-17 | 2011-08-04 | Gulfstream Aerospace Corporation | System and Method for an Integrated Backup Control System |
| CN105564637A (en) * | 2014-11-06 | 2016-05-11 | 申久祝 | Four-redundant direct current steering engine control system based on DSP |
| CN104743125A (en) * | 2015-03-09 | 2015-07-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Single-stage DDV steering engine current protecting strategy |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111532418A (en) * | 2020-05-20 | 2020-08-14 | 中国商用飞机有限责任公司 | Aircraft high lift system |
| CN111532418B (en) * | 2020-05-20 | 2021-09-24 | 中国商用飞机有限责任公司 | Aircraft high lift system |
| CN114002943A (en) * | 2021-09-30 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Architecture of backup system of telex flight control system |
| CN114002943B (en) * | 2021-09-30 | 2024-05-24 | 中航通飞华南飞机工业有限公司 | Framework of backup system of fly-by-wire control system |
| CN115145140A (en) * | 2022-06-07 | 2022-10-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Ground non-hydraulic protection logic algorithm for servo steering engine |
| CN115145140B (en) * | 2022-06-07 | 2025-02-18 | 中国航空工业集团公司沈阳飞机设计研究所 | A logic method for ground non-hydraulic protection of servo steering gear |
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| CN106741861B (en) | 2019-06-28 |
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