CN108415238A - A kind of electricity trim monitoring switch method - Google Patents
A kind of electricity trim monitoring switch method Download PDFInfo
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- CN108415238A CN108415238A CN201810105985.2A CN201810105985A CN108415238A CN 108415238 A CN108415238 A CN 108415238A CN 201810105985 A CN201810105985 A CN 201810105985A CN 108415238 A CN108415238 A CN 108415238A
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- trim
- signal
- input signal
- discrete magnitude
- failure
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B9/00—Safety arrangements
- G05B9/02—Safety arrangements electric
- G05B9/03—Safety arrangements electric with multiple-channel loop, i.e. redundant control systems
Abstract
The present invention relates to a kind of electric trim monitoring switch methods, are controlled for realizing the voting of electric trim signal, the monitoring method includes：It is first added the discrete magnitude signal of four remainings, obtains possible result；If addition result is " 4 ", then vote value is " 1 ", discrete magnitude signal does not occur as failure, if addition result is " 3 ", then vote value is " 1 ", discrete magnitude signal is that the input signal of " 0 " is fault-signal, if addition result is " 1 ", then vote value is " 1 ", discrete magnitude signal is that the input signal of " 1 " is fault-signal, if addition result is " 0 ", then vote value is " 0 ", discrete magnitude signal does not occur as failure, if addition result is " 2 ", it is then unusual failure, input signal takes safety value, four input signals are fault-signal.The present invention realizes electric trim switch realizes monitoring voting under the layout configuration of reasonable remaining, has higher reliability and fault-tolerant ability.
Description
Technical field
The invention belongs to aviation flight control technology field more particularly to a kind of electric trim monitoring switch methods.
Background technology
Trim switch is control mechanism on control stick, can by a small margin be adjusted to aspect, and when use is clicked
Trim switch can act aircraft by a small margin, if pinning trim switch when not putting, rudder face persistently rotates, and trim is switched and can be kept away
Exempt from pilot's long-time operation.
However be necessary for the redundancy management of electric trim switch, redundancy management is to multiplicated system operating mechanism
It prepares and the processing to remaining problem, mission reliability and flight safety can be improved to greatest extent, made in normal work
Effec-tive Function when making, after failure, reduced performance are minimum, and provide protection to failure transient.
Invention content
The object of the present invention is to provide a kind of electric trim monitoring switch methods, solve the electric trim switch in the case of redundance
Control problem.
In order to achieve the above objectives, the technical solution adopted by the present invention is：A kind of electricity trim monitoring switch method, the electricity are matched
Pass is opened flat using electrical four remaining, the single redundancy architecture of machinery, electric trim switch input signal is discrete magnitude signal, the discrete magnitude
Signal is 0 and 1, and the monitoring method includes：
A, discrete magnitude signal is made to be added, the result that four remaining signals are likely to be obtained is 0,1,2,3,4；
If b, addition result is " 4 ", all four remaining signals are effective, and input signal vote value is " 1 ", fault-free letter
Number；
If c, addition result is " 3 ", input signal vote value is " 1 ", and discrete magnitude signal is that the input signal of " 0 " is failure
Signal；
If d, addition result is " 1 ", input signal vote value is " 0 ", and discrete magnitude signal is that the input signal of " 1 " is failure
Signal；
If e, addition result is " 0 ", all four remaining signals are effective, and input signal vote value is " 0 ", fault-free letter
Number；
If f, addition result is " 2 ", for unusual failure, input signal takes safety value, and four input signals are failure
Signal.
In the above scheme, the input signal includes face upward trim, nutation trim, left-leaning trim, Right deviation trim, left
In being returned to rudder trim, right direction rudder with gentle trim.
In the above scheme, when unusual failure, the safety value of input signal is：Trim of facing upward takes trim of not facing upward, nutation
Trim takes that not nutation trim, that left-leaning trim takes not left-leaning trim, Right deviation trim that not Right deviation trim, left direction rudder trim is taken to take is not left
Rudder trim, right direction rudder trim take not right direction rudder with gentle trim return in take not trim return in.
In the above scheme, the discrete magnitude signal is equipped with time threshold, and the selection of time threshold should be according to signal intensity
Speed situation, redundant configurations and failure rank select different time thresholds, guarantee system to be correctly isolated different faults
Processing ensures system safety.
The electric trim monitoring switch method of the present invention realizes electric trim and switchs the monitoring under redundancy management, can be maximum
Its reliability and flight safety of the raising of limit makes its Effec-tive Function in normal work, after failure, performance drop
Low minimum, and provide protection to failure transient.
Description of the drawings
The drawings herein are incorporated into the specification and forms part of this specification, and shows the implementation for meeting the present invention
Example, and be used to explain the principle of the present invention together with specification.
Fig. 1 is that Vehicle Management System decides by vote monitoring face.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the present invention is 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.
The present invention is to realize the redundancy management of electric trim switch, provides a kind of electric trim monitoring switch method.The present invention
The input signal remaining basic grade of middle electricity trim switch is using electrical four remaining, the single remaining of machinery.
In electric trim switch control, electric trim signal is discrete magnitude signal, and discrete magnitude signal is a kind of, and there are two types of shapes
The signal of the amount of state, state are respectively 0 and 1.
As shown in Figure 1, during electric trim switch control, DIO is passed through in discrete magnitude input (electric trim signal) first
(Digital Input/Output) discrete magnitude input/output interface enters safe machine internal bus, and passes to CPU carry out tables
It definitely calculates, CPU obtains a vote value according to four remaining signals, and vote value is exported to control mechanism and then controlled after logical operation
The posture of aircraft processed, completes the operation of aircraft, and table 1 is that the aspect that is used for of electric trim switch control adjusts component names.
The electric trim switching signal redundant configurations of table 1
For the discrete magnitude input signal of electric trim switch：It faces upward trim, nutation trim, left-leaning trim, Right deviation trim, a left side
Rudder trim, right direction rudder have been all made of the Systems Redundancy Management of majority voting in being returned with gentle trim, and failure prison is arranged
Time delay is controlled, failure safe value is set after there is ambiguity failure.
It is as follows for the monitoring voting algorithm of discrete magnitude input signal：
A, four remaining discrete input quantities are added, the result that four remaining signals are likely to be obtained is 4,3,2,1,0；
If b, be added after itself and be " 4 ", show all four remaining signals it is effective, the vote value of discrete magnitude input signal
For " 1 ", fault-free signal；
If after c, being added itself and be " 3 ", the vote value of discrete magnitude input signal is " 1 ", is all had in four remaining signals
Signal is failure all the way, and discrete magnitude input signal values are that the signal of " 0 " is fault-signal；
If after d, being added itself and be " 1 ", the vote value of discrete magnitude input signal is " 0 ", is all had in four remaining signals
Signal is failure all the way, and discrete magnitude input signal values are that the signal of " 1 " is fault-signal；
If e, be added after itself and be " 0 ", show all four remaining signals it is effective, the vote value of discrete magnitude input signal is
" 0 ", fault-free signal；
If f, be added after itself and be " 2 ", be 2：2 unusual failures, discrete magnitude input signal take preset safety value,
And judge that four discrete magnitude input signals are fault-signal.
For unusual failure, the measure that electric trim switching signal is taken is as shown in table 2.
The electric trim switching signal redundant configurations of table 2
The selection of the setting time thresholding in discrete magnitude input process, discrete magnitude time threshold should be according to signal intensity speed
Situation, redundant configurations and failure rank select different time thresholds, guarantee system to carry out being correctly isolated processing to different faults,
Guarantee system safety.
Table 3 be the present invention in an embodiment discrete magnitude monitor time threshold recommended value, but need to disturb it is bright, rear
Adjustment can be optimized to time threshold in continuous system test and Flight.
3 discrete magnitude monitor time threshold of table
| Signal name | 1 fault time thresholding | 2 fault time thresholdings | 3 times/unusual fault time thresholding |
| Automatic trim | 600ms | 600ms | 400ms |
In the present invention, electric trim switch realizes monitoring voting under the layout configuration of reasonable remaining, can effectively improve electricity
The reliability and flight safety of trim switch make system Effec-tive Function in normal work, after failure, reduced performance
Minimum, and provide protection to failure transient.The method of the present invention can ensure this critical component secondary failure work of rate gyroscope
Make, three times the fault-tolerant ability of failure safe.
The above, only optimal specific implementation mode of the invention, but scope of protection of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
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 (4)
1. a kind of electricity trim monitoring switch method, which is characterized in that the electricity trim switch is using electrical four remaining, machinery Dan Yu
Structure is spent, electric trim switch input signal is discrete magnitude signal, and the discrete magnitude signal is 0 and 1, and the monitoring method includes：
A, discrete magnitude signal is made to be added, the result that four remaining signals are likely to be obtained is 0,1,2,3,4；
If b, addition result is " 4 ", all four remaining signals are effective, and input signal vote value is " 1 ", fault-free signal；
If c, addition result is " 3 ", input signal vote value is " 1 ", and discrete magnitude signal is that the input signal of " 0 " is failure letter
Number；
If d, addition result is " 1 ", input signal vote value is " 0 ", and discrete magnitude signal is that the input signal of " 1 " is failure letter
Number；
If e, addition result is " 0 ", all four remaining signals are effective, and input signal vote value is " 0 ", fault-free signal；
If f, addition result is " 2 ", for unusual failure, input signal takes safety value, and four input signals are fault-signal.
2. electricity trim monitoring switch method according to claim 1, which is characterized in that the input signal includes facing upward to match
During flat, nutation trim, left-leaning trim, Right deviation trim, the trim of left direction rudder, right direction rudder are returned with gentle trim.
3. electricity trim monitoring switch method according to claim 2, which is characterized in that when unusual failure, input signal
Safety value is：Trim of facing upward takes trim of not facing upward, nutation trim that not nutation trim, left-leaning trim is taken to take not left-leaning trim, Right deviation
Trim take not Right deviation trim, left direction rudder trim take not left direction rudder trim, right direction rudder trim take not right direction rudder with gentle
Trim takes not trim to return in returning in.
4. electricity trim monitoring switch method according to claim 1, which is characterized in that the discrete magnitude signal is equipped with the time
The selection of thresholding, time threshold should select different time gates according to signal intensity speed situation, redundant configurations and failure rank
Limit, guarantee system carry out different faults to be correctly isolated processing, ensure system safety.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810105985.2A CN108415238A (en) | 2018-02-02 | 2018-02-02 | A kind of electricity trim monitoring switch method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810105985.2A CN108415238A (en) | 2018-02-02 | 2018-02-02 | A kind of electricity trim monitoring switch method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110134552A (en) * | 2019-05-09 | 2019-08-16 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of fault-tolerance approach based on empirical learning |
| CN112346331A (en) * | 2020-11-18 | 2021-02-09 | 西安爱生技术集团公司 | Channel selection method of three-redundancy flight control computer |
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Application publication date: 20180817 |
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