CN106741861B - 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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- CN106741861B CN106741861B CN201611126452.XA CN201611126452A CN106741861B CN 106741861 B CN106741861 B CN 106741861B CN 201611126452 A CN201611126452 A CN 201611126452A CN 106741861 B CN106741861 B CN 106741861B
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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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Abstract
The present invention relates to a kind of bipolar direct drive valve actuator current protection strategies; for controlling the force motor state of Servo-controller in flight control system, including first: signal acquisition, second: signal processing and voting, third: the condition criterion and the 4th of current protection starting: the condition criterion of current protection.Bipolar direct drive valve actuator current protection strategy of the invention makes aircraft in ground maintenance; the current protection starting of Servo-controller can be automatically performed; the protection of the servo current as caused by artificial maloperation or possibility of forgetting is avoided not start; the force motor of Servo-controller is caused to fail; guarantee the safety of Servo-controller current protection; maintenance efficiency is promoted, meets the needs of aircraft flight control system internal field, flight-line service.
Description
Technical field
The invention belongs to aircraft control technical field more particularly to a kind of bipolar direct drive valve actuator current protection plans
Slightly.
Background technique
Flight control system increases surely from control, develops to fax (FBW) flight control system, and pass (FBL) towards this light and fly control
The direction of system is developed；Actuator develops to fax combined type servo actuator also accordingly from hydaulic redundancy actuator, and towards
Signal light, which passes power-by-wire (PBW) actuator direction, to be developed.Develop in fax combined type actuator to power-by-wire actuator
In the process, there is direct drive valve (DDV) formula actuator, mainly solve combined type fax servo actuator structure is complicated, at
The problem of this height, reliability and maintainability difference.With the rapid development of digital technology, system design is urgent with debugging flexibility
It is required that the needs of modern advanced control theory practical application and the demand of high reliability Digital Transmission；It is required that actuator is watched
Dress system is developed from traditional analog servo system to redundancy digital type servo-system.
Currently, aircraft generallys use the electro-hydraulic combination servo actuator of servo valve (EHV) formula both at home and abroad.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 amplifying stage for taking valve will greatly simplify combination servo actuator structure, reliability can be made to significantly improve.It therefore, is understanding
Certainly structure is complicated, the problem of at high cost, reliability and maintainability difference for EHV formula combination servo actuator, direct drive valve occurs
(DDV) formula actuator, and be widely used in various Advanced Aircrafts.
Summary of the invention
The object of the present invention is to provide a kind of bipolar direct drive valve actuator current protection strategies, are in order to avoid bipolar
Steering engine force motor occurs in ground maintenance for direct drive valve actuator because high temperature leads to sealing rubber ring and coil electric insulating properties
Failure, so that Design of Flight Control has " force motor current protecting function ".
In order to achieve the above objectives, the technical solution adopted by the present invention is that: a kind of bipolar direct drive valve actuator electric current is protected
Shield strategy, for controlling the force motor state of Servo-controller in On A Redundant Flight Control System, which is characterized in that including
Step 1: signal acquisition
1.1) firstly, the acquisition of each redundance flight control systems computer dynamic pressure signal connected to it, wheel carrying signal,
Hydraulic good signal and force motor current signal；
Wherein, the dynamic pressure signal is divided into dynamic pressure and is less than or equal to dynamic pressure threshold value shape greater than dynamic pressure threshold values state and dynamic pressure
State, the wheel carrying signal are divided into wheel loaded state and not loaded state, and the hydraulic good signal is divided into hydraulic good
State and not kilter, the force motor current signal are divided into force motor electric current greater 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；It is passed by the intersection of redundance flight control systems computer
After defeated, obtaining the remaining of each redundance flight control systems computer includes dynamic pressure signal, wheel carrying signal, hydraulic good letter
Number and force motor current signal；
Step 2: signal voting and processing
2.1) each redundance flight control systems computer puts to the vote to dynamic pressure signal and wheel carrying signal, generates after voting
Current protection entry condition each group state value；
2.2) state processing is carried out to the dynamic pressure signal after voting；
Step 3: the condition criterion of current protection starting
Each redundance flight control systems computer of On A Redundant Flight Control System works as current protection entry condition state state of value:
Dynamic pressure signal condition is that dynamic pressure is less than or equal to dynamic pressure threshold status and wheel carrying signal is wheel loaded state while meeting
When, Cutoff current protects entry condition to meet, into step 4；Otherwise, it is determined that current protection entry condition is unsatisfactory for；
Step 4: the condition criterion of current protection
It 4.1), should when any redundance flight control systems computer of On A Redundant Flight Control System meets current protection entry condition
On A Redundant Flight Control System enters current protection program；If it is wheel loaded state, dynamic pressure signal condition that wheel, which carries signal,
For dynamic pressure be less than or equal to dynamic pressure threshold status and force motor current signal be force motor electric current greater than current threshold state,
Hydraulic good signal is that four conditions of hydraulic not kilter meet simultaneously, and the state continues the first predetermined time T1, then
Cut off the force motor power supply of the Servo-controller of the On A Redundant Flight Control System；
4.2) 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 to wheel
For hydraulic kilter or the continuous second predetermined time T of force motor current signal2It is that force motor electric current is less than or equal to electricity
When flowing threshold status, then the On A Redundant Flight Control System exits current protection, and Servo-controller enters normal control state.
Further, in second step, voting is to carry out operation to multiple signals or state and export result according to certain rules
The process made decision, for general discrete magnitude, using majority voting effective monitoring voting algorithm, four remaining signal conditions,
It is as follows to monitor voting algorithm: signal voting algorithm are as follows:
If 1) itself and be " 4 ", all four remaining signals it is effective, vote value be " 1 ", fault-free signal；
If 2) itself and be " 3 ", vote value be " 1 ", " 0 " value signal be fault-signal；
If 3) itself and be " 1 ", vote value be " 0 ", " 0 " value signal be fault-signal；
4)) if itself and be " 0 ", all four remaining signals it is effective, vote value be " 0 ", fault-free signal.
Further, the first predetermined time T1To be no less than 10 minutes.
Further, the second predetermined time T2To be no less than 100 milliseconds.
Bipolar direct drive valve actuator current protection strategy of the invention makes aircraft in ground maintenance, can be automatic
The current protection starting for completing Servo-controller, avoids the protection of the servo current as caused by artificial maloperation or possibility of forgetting not
Starting, causes the force motor of Servo-controller to fail, and guarantees the safety of Servo-controller current protection, promotes maintenance efficiency, meets
Aircraft flight control system internal field, flight-line service demand.
Detailed description of the invention
The drawings herein are incorporated into the specification and forms part of this specification, and shows and meets implementation of the invention
Example, and be used to explain the principle of the present invention together with specification.
Fig. 1 is bipolar direct drive valve actuator current protection strategic process figure of the invention.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.Embodiment below with reference to attached drawing description is exemplary type, it is intended to be used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained under the premise of not making the labour of creation type, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
The working principle of bipolar direct drive valve actuator current protection strategy of the invention is: being protected using automatic electric current
Starting method is protected, so that aircraft prevents the force motor superheating phenomenon that may occur in ground maintenance, improves Servo-controller electric current
The safety of protection meets the needs of aircraft flight control system internal field, flight-line service.When aircraft is in ground maintenance, fly
Row control computer carries signal according to dynamic pressure signal condition, wheel, carries out the condition judgement of current protection starting, passes through acquisition
Each cond value of servo current protection judges whether that the force motor for the Servo-controller for cutting off this On A Redundant Flight Control System supplies
Electricity.
It is as shown in Figure 1 bipolar direct drive valve actuator current protection strategic process figure of the invention, diamond shape is sentenced in figure
" && in disconnected step " is logical operation "AND", " | | " is logical operation "or".
Bipolar direct drive valve actuator current protection strategy of the invention includes
Step 1: signal acquisition
A, each remaining acquisition dynamic pressure signal connected to it of four redundance flight control systems computers first, wheel carrying letter
Number, hydraulic good signal and force motor current signal；
Wheel carrying signal is divided into wheel loaded state and wheel not loaded state --- and it is hydraulic for characterizing the state of ground
Good signal is divided into hydraulic kilter and hydraulic not kilter --- for characterizing servo pressurized strut hydraulic energy source state, power
Motor current signal is divided into force motor electric current and is less than or equal to current threshold state greater than current threshold state and force motor electric current,
Dynamic pressure signal condition is divided into dynamic pressure and is less than or equal to dynamic pressure threshold status greater 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 made to obtain dynamic pressure signal and wheel carrying signal of 4 remainings etc.；
Step 2: signal voting and processing
Voting is the process for carrying out operation to multiple signals (or state) and exporting result (making decision) according to certain rules.
For general discrete magnitude, using majority voting effective monitoring voting algorithm.
Four remaining signal conditions, monitoring voting algorithm are as follows:
If 1) itself and be " 4 ", all four remaining signals it is effective, vote value be " 1 ", fault-free signal；
If 2) itself and be " 3 ", triplex redundance signal is effective, vote value be " 1 ", " 0 " value signal be fault-signal；
If 3) itself and be " 1 ", a remaining signal is effective, vote value be " 0 ", " 1 " value signal be fault-signal；
If 4) itself and be " 0 ", no remaining signal is effective, then all four remaining signals it is effective, vote value be " 0 ", without reason
Hinder signal；
It should be noted that show that two remaining signals are effective when it and when for " 2 ", can not be judged, i.e., without
Voting.
Note: the meaning of "and" is exactly that number 1 is denoted as when some signal is effective, and multiple signals have multiple numbers when effective
Word 1, by multiple digital 1 works and the "and" as in the present invention.
C, each redundance flight control systems computer 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；
D, state processing is carried out to the dynamic pressure signal after voting, dynamic pressure signal condition is divided into dynamic pressure greater than dynamic pressure threshold status
It is less than or equal to dynamic pressure threshold status with dynamic pressure；
Step 3: the condition criterion of current protection starting
Each redundance flight control systems computer of four On A Redundant Flight Control Systems is same when current protection entry condition state value
When meet: dynamic pressure signal condition is that dynamic pressure is less than or equal to dynamic pressure threshold status, wheel carrying signal when being wheel loaded state,
Cutoff current protects entry condition to meet, then enters the 4th step；Otherwise, it is determined that current protection entry condition is unsatisfactory for；
Step 4: the condition criterion of current protection
It e, should when some redundance flight control systems computer of four On A Redundant Flight Control Systems meets current protection entry condition
On A Redundant Flight Control System enters current protection program；If it is wheel loaded state, dynamic pressure signal condition that wheel, which carries signal,
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 four conditions of hydraulic not kilter meet simultaneously, and the state continues 10 minutes (the first predetermined time),
Cut off the force motor power supply of the horizontal tail Servo-controller of this On A Redundant Flight Control System；
F, after certain On A Redundant Flight Control System enters current protection program, there is any one following condition and meet；Machine
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 to wheel
Hydraulic kilter, continuous 100 milliseconds of force motor current signal (the second predetermined time) are less than or equal to electricity for force motor electric current
When flowing threshold status, which exits current protection.
Bipolar direct drive valve actuator current protection strategy of the invention makes aircraft in ground maintenance, can be automatic
The current protection starting for completing Servo-controller, avoids the protection of the servo current as caused by artificial maloperation or possibility of forgetting not
Starting, causes the force motor of Servo-controller to fail, and guarantees the safety of Servo-controller current protection, promotes maintenance efficiency, meets
Aircraft flight control system internal field, flight-line service demand.
The above, optimal specific embodiment only of the invention, but scope of protection of the present invention is not limited thereto,
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Subject to enclosing.
Claims (5)
1. a kind of bipolar direct drive valve actuator current protection strategy, for controlling Servo-controller in On A Redundant Flight Control System
Force motor state, which is characterized in that including
Step 1: signal acquisition
1.1) firstly, the acquisition of each redundance flight control systems computer dynamic pressure signal connected to it, wheel carrying signal, hydraulic
Good signal and force motor current signal；
Wherein, the dynamic pressure signal is divided into dynamic pressure and is less than or equal to dynamic pressure threshold status, institute greater than dynamic pressure threshold status and dynamic pressure
State wheel carrying signal and be divided into wheel loaded state and not loaded state, the hydraulic good signal be divided into hydraulic kilter with
Not kilter, the force motor current signal be divided into force motor electric current be less than greater 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 the Cross transfer of redundance flight control systems computer
Afterwards, obtaining the remaining of each redundance flight control systems computer includes dynamic pressure signal, wheel carrying signal, hydraulic good signal
With force motor current signal；
Step 2: signal voting and processing
2.1) each redundance flight control systems computer puts to the vote to dynamic pressure signal and wheel carrying signal, and electric current is generated after voting
Protect entry condition each group state value；
2.2) state processing is carried out to the dynamic pressure signal after voting；
Step 3: the condition criterion of current protection starting
Each redundance flight control systems computer of On A Redundant Flight Control System works as current protection entry condition state state of value: dynamic pressure
When signal condition is that dynamic pressure is less than or equal to dynamic pressure threshold status and wheel carrying signal is wheel loaded state while meeting, sentence
Constant current protects entry condition to meet, into step 4；Otherwise, it is determined that current protection entry condition is unsatisfactory for；
Step 4: the condition criterion of current protection
4.1) when any redundance flight control systems computer of On A Redundant Flight Control System meets current protection entry condition, the remaining
Flight control system enters current protection program；If wheel carrying signal is that wheel loaded state, dynamic pressure signal condition are
It is that force motor electric current is greater than current threshold state, hydraulic that pressure, which is less than or equal to dynamic pressure threshold status and force motor current signal,
Good signal is that four conditions of hydraulic not kilter meet simultaneously, and the state continues the first predetermined time T1, then cut off
The force motor of the Servo-controller of the On A Redundant Flight Control System is powered；
4.2) 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 or the continuous second predetermined time T of force motor current signal2It is that force motor electric current is less than or equal to current threshold
When state of value, then the On A Redundant 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, which is characterized in that the 2nd step
In, voting is to carry out operation to multiple signals or state and export the process that result is made decision according to certain rules, for general
Discrete magnitude, using majority voting effective monitoring voting algorithm, four remaining signal conditions, monitoring voting algorithm is as follows
Signal voting algorithm are as follows:
If 1) itself and be " 4 ", all four remaining signals it is effective, vote value be " 1 ", fault-free signal；
If 2) itself and be " 3 ", vote value be " 1 ", " 0 " value signal be fault-signal；
If 3) itself and be " 1 ", vote value be " 0 ", " 0 " value signal be fault-signal；
4)) if itself and be " 0 ", all four remaining signals it is effective, vote value be " 0 ", fault-free signal.
3. bipolar direct drive valve actuator current protection strategy according to claim 2, which is characterized in that if itself and be
" 2 ", without voting.
4. bipolar direct drive valve actuator current protection strategy according to claim 1, which is characterized in that described first
Predetermined time T1To be no less than 10 minutes.
5. bipolar direct drive valve actuator current protection strategy according to claim 1, which is characterized in that described second
Predetermined time T2To be no less than 100 milliseconds.
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| CN201611075312 | 2016-11-29 | ||
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| CN111532418B (en) * | 2020-05-20 | 2021-09-24 | 中国商用飞机有限责任公司 | Aircraft high lift 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 |
| 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 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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| Publication number | Priority date | Publication date | Assignee | Title |
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| BRPI0706593A2 (en) * | 2006-01-17 | 2011-04-05 | Gulfstream Aerospace Corp | system and method for an integrated backup control system |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
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