CN103303466B - A kind of aircraft rudder surface lock error protection electric control method and system thereof - Google Patents
A kind of aircraft rudder surface lock error protection electric control method and system thereof Download PDFInfo
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- CN103303466B CN103303466B CN201210061052.0A CN201210061052A CN103303466B CN 103303466 B CN103303466 B CN 103303466B CN 201210061052 A CN201210061052 A CN 201210061052A CN 103303466 B CN103303466 B CN 103303466B
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Abstract
The present invention relates to a kind of aircraft rudder surface lock error-preventive design method, specifically, be about consider aircraft main rudder face ground, take off before handling characteristics, carry out electrical design, be cross-linked with multisystem, design circuit interlocking and sound, light alarm mode, carry out error-preventive design, guarantee the lower safe handling of aircraft main rudder face the locking and unlocking state.Compared with prior art, the invention has the beneficial effects as follows: aircraft is liftoff rear automatic disconnection rudder face lock control power supply, prevent aerial rudder face to lock by mistake; The non-released state of rudder face, adopt light in conjunction with the method prompting chaufeur of sound, protection face is complete, prevents not unlock and takes off by mistake.
Description
Technical field
The invention relates to a kind of aircraft rudder surface lock error-preventive design method, specifically, be about consider aircraft main rudder face ground, take off before handling characteristics, carry out electrical design, be cross-linked with multisystem, design circuit interlocking and sound, light alarm mode, carry out error-preventive design, guarantee the lower safe handling of aircraft main rudder face the locking and unlocking state.
Background technology
Aircraft, when ground is parked, makes main rudder face swing in order to avoid blowing, cause the transmission device damaging rudder face and maneuvering system, and elevating rudder, yaw rudder and aileron pin fixing by rudder face lock system, should not affect rudder face free motion in the air.The locking in the main rudder face of large and medium-sized flight control system generally adopts mechanical locking or electromechanical locking devices, the error-preventive design that electromechanical locking devices is formed generally arranges indicator lamp near rudder face lock system electrification switch, after prompting aircraft rudder surface is removed and is limited, necessary artificial parting system power supply before taking off; Rudder face locking indicator lamp, rudder face unblock indicator lamp are set near rudder face lock control switch; Taking off on annunciator, rudder face is being set and does not unlock completely indicator lamp; Rudder face does not unlock completely and brakes and do not turn off, and carries out sound alarm after pushing away throttle lever.Its weak point, before taking off, rudder face lock system works power supply needs people to be off, and there is the possibility of maloperation; Only have light when rudder face does not unlock completely in visual range alarm, full crew can not be taken into account, there is the possibility of maloperation.
A kind of aircraft rudder surface lock error protection electrical control error-preventive design, takes decision circuit to be cross-linked with airplane wheel load bearing component, realizes aircraft and leaves ground and automatically disconnect rudder face lock Systematical control power supply afterwards, avoid to miss in the air and pinned by aircraft rudder surface; Alarm components is cross-linked to take decision circuit and sound light display to show, when rudder face lock does not unlock completely, except visual range light prompt, and shows that alarm components carries out sound alarm to all crews of driving compartment by sound light display.Consider that aircraft is on ground, rudder face unlocked time is longer and sound alarm is clear and melodious, devises alerting tone releasing parts and can remove sound alarm.Be cross-linked with throttle lever, if rudder face lock does not unlock completely, sound light display shows that alarm components carries out the alarm of sound light, after pressing alerting tone removes parts releasing sound alarm, after pushing away throttle lever, can toggle sound alarm again, operation alerting tone removes parts, then can not remove sound alarm, prompting must carry out rudder face unblock.
Summary of the invention
The technical problem to be solved in the present invention:
Instant invention overcomes the deficiency of existing dynamo-electric rudder face blocking device " rudder face is locked by mistake ", " rudder face non-released state light prompt visual range is incomplete " in the air, provide a kind of error-preventive design method.
Technical scheme of the present invention:
In order to solve the problems of the technologies described above, the present invention is achieved by the following technical solutions: adopt decision circuit and wheel load bearing component crosslinked, aircraft is liftoff rear automatic cut-out rudder face lock control power supply, prevents aerial rudder face from locking by mistake; Adopt decision circuit and sound light display to show that alarm components is cross-linked, realize the prompting of sound light combination, point out all crews to understand non-released state, before guaranteeing to take off, rudder face unlocks completely.
A kind of aircraft rudder surface lock error-preventive design method, comprises the following steps:
The first step, connects aircraft rudder surface lock system power supply;
Second step, decision circuit judges wheel load bearing component, if do not carry, namely aircraft is liftoff, then perform the 3rd step, if carrying, namely aircraft is in ground, then perform the 6th step;
3rd step, rudder face lock control power supply is cut off;
4th step, sound light display shows that alarm components is carried out rudder face and unlocked light prompt;
5th step, now pilot control motor drive mechanism function unit, cannot send instruction of locking, flow process terminates;
6th step, chaufeur judges to take off or park, if park, performs the 7th step, if take off, performs the 11 step;
7th step, decision circuit judges whether rudder face lock status locks, if locking, performs the 8th step, if non-locking, performs the 9th step;
8th step, sound light display shows that alarm components carries out rudder face locking light prompt, and flow process terminates;
9th step, decision circuit triggers sound light display and shows alarm components display rudder face non-locking;
Tenth step, pilot control motor drive mechanism function unit carries out rudder face and locks, and performs the 7th step;
11 step, decision circuit judges whether rudder face lock unlocks, if unlock, performs the 12 step, if do not unlock, performs the 13 step;
12 step, sound light display shows that alarm components is carried out rudder face and unlocked light prompt, and flow process terminates.
13 step, to sound light display, decision circuit shows that alarm components sends sound light alarm command, sound light display shows that alarm components carries out the alarm of sound light, and prompting chaufeur carries out rudder face releasing;
14 step, decision circuit judges whether chaufeur operates alerting tone and remove parts, if do not operate, performs the 15 step, if operation, performs the 16 step;
15 step, pilot control motor drive mechanism function unit carries out rudder face unblock, performs the 11 step;
16 step, decision circuit removes sound alarm, and still send light alarm command, sound light display shows that alarm components only carries out light alarm, and prompting chaufeur carries out rudder face releasing;
17 step, decision circuit judges whether chaufeur pushes away throttle lever, if do not push away throttle lever, performs the 15 step, if push away throttle lever, performs the 18 step;
18 step, decision circuit toggle sound alarm again, sound light display shows that alarm components only carries out the alarm of sound light, and prompting chaufeur carries out rudder face releasing;
19 step, driver's operation alerting tone removes parts cannot remove sound alarm, perform the 15 step.
A kind of aircraft rudder surface lock error protection electric control system, comprising: function unit, wheel load bearing component 3, decision circuit 4, throttle lever 5, execution unit 6 and sound light display show alarm components 7; Wherein,
Function unit comprises motor drive mechanism function unit 1 and alerting tone and removes parts 2, motor drive mechanism function unit be used for pilot control send lock, unlock command, alerting tone is removed parts and is used for pilot control and removes sound alarm;
Wheel load bearing component provides wheel whether carrying signal to decision circuit;
Decision circuit judges whether wheel load bearing component carries, judge rudder face lock status, send sound light alarm command triggers sound light display and shows that alarm components carries out the display of rudder face lock status and alarm prompt, judgement throttle lever position;
Throttle lever provides throttle lever position to decision circuit;
The instruction of execution unit receive logic circuit, carries out rudder face unblock, locks, and by rudder face lock status feedback logic circuit;
Sound light display shows the instruction of alarm components receive logic circuit, carries out the display of rudder face lock status and alarm prompt.
Beneficial effect of the present invention:
Compared with prior art, advantage of the present invention is: aircraft is liftoff rear automatic disconnection rudder face lock control power supply, prevents aerial rudder face to lock by mistake; The non-released state of rudder face, adopt light in conjunction with the method prompting chaufeur of sound, protection face is complete, prevents not unlock and takes off by mistake.
Accompanying drawing explanation
Fig. 1 is the diagram of circuit of this aircraft rudder surface lock error protection electric control method;
Fig. 2 is the functional block diagram of this aircraft rudder surface lock error protection electric control system.
Detailed description of the invention
Below in conjunction with accompanying drawing and detailed description of the invention, the present invention is described in further detail:
A kind of aircraft rudder surface lock error protection electric control system, comprising: function unit, wheel load bearing component 3, decision circuit 4, throttle lever 5, execution unit 6 and sound light display show alarm components 7; Wherein,
Function unit comprises motor drive mechanism function unit 1 and alerting tone and removes parts 2, motor drive mechanism function unit be used for pilot control send lock, unlock command, alerting tone is removed parts and is used for pilot control and removes sound alarm;
Wheel load bearing component provides wheel whether carrying signal to decision circuit;
Decision circuit judges whether wheel load bearing component carries, judge rudder face lock status, send sound light alarm command triggers sound light display and shows that alarm components carries out the display of rudder face lock status and alarm prompt, judgement throttle lever position;
Throttle lever provides throttle lever position to decision circuit;
The instruction of execution unit receive logic circuit, carries out rudder face unblock, locks, and by rudder face lock status feedback logic circuit;
Sound light display shows the instruction of alarm components receive logic circuit, carries out the display of rudder face lock status and alarm prompt.
After aircraft is liftoff, wheel load bearing component provides wheel non-carrying signal to decision circuit, and decision circuit cuts off the rudder face lock control power supply of motor drive mechanism function unit, ensures that aerial rudder face cannot be locked.
Before taking off, rudder face lock status is supplied to decision circuit by execution unit, decision circuit judges whether rudder face lock unlocks, when not unlocking, decision circuit sends sound light alarm command, sound light display shows that alarm components carries out the alarm of sound light, prompting chaufeur carries out rudder face releasing, chaufeur removes sound alarm by alerting tone, but can not remove light alarm, if rudder face unlocks not yet completely, chaufeur pushes away throttle lever and takes off, decision circuit toggle sound alarm again, rudder face must unlock by prompting chaufeur completely.
Claims (2)
1. an aircraft rudder surface lock error-preventive design method, it is characterized in that, this method comprises the following steps:
The first step, the power-supply system of aircraft rudder surface lock system is connected;
Second step, decision circuit judges wheel load bearing component, if do not carry, namely aircraft is liftoff, then perform the 3rd step, if carrying, namely aircraft is in ground, then perform the 6th step;
3rd step, rudder face lock control power supply is cut off;
4th step, sound light display shows that alarm components is carried out rudder face and unlocked light prompt;
5th step, now pilot control motor drive mechanism function unit, cannot send instruction of locking, flow process terminates;
6th step, chaufeur judges to take off or park, if park, performs the 7th step, if take off, performs the 11 step;
7th step, decision circuit judges whether rudder face lock status locks, if locking, performs the 8th step, if non-locking, performs the 9th step;
8th step, sound light display shows that alarm components carries out rudder face locking light prompt, and flow process terminates;
9th step, decision circuit triggers sound light display and shows alarm components display rudder face non-locking;
Tenth step, pilot control motor drive mechanism function unit carries out rudder face and locks, and performs the 7th step;
11 step, decision circuit judges whether rudder face lock unlocks, if unlock, performs the 12 step, if do not unlock, performs the 13 step;
12 step, sound light display shows that alarm components is carried out rudder face and unlocked light prompt, and flow process terminates;
13 step, to sound light display, decision circuit shows that alarm components sends sound light alarm command, sound light display shows that alarm components carries out the alarm of sound light, and prompting chaufeur carries out rudder face releasing;
14 step, decision circuit judges whether chaufeur operates alerting tone and remove parts, if do not operate, performs the 15 step, if operation, performs the 16 step;
15 step, pilot control motor drive mechanism function unit carries out rudder face unblock, performs the 11 step;
16 step, decision circuit removes sound alarm, and still send light alarm command, sound light display shows that alarm components only carries out light alarm, and prompting chaufeur carries out rudder face releasing;
17 step, decision circuit judges whether chaufeur pushes away throttle lever, if do not push away throttle lever, performs the 15 step, if push away throttle lever, performs the 18 step;
18 step, decision circuit toggle sound alarm again, sound light display shows that alarm components only carries out the alarm of sound light, and prompting chaufeur carries out rudder face releasing;
19 step, driver's operation alerting tone removes parts cannot remove sound alarm, perform the 15 step.
2. an aircraft rudder surface lock error protection electric control system, it is characterized in that, native system comprises: function unit, wheel load bearing component (3), decision circuit (4), and throttle lever (5), execution unit (6) and sound light display show alarm components (7); Wherein,
Function unit comprises motor drive mechanism function unit (1) and alerting tone removes parts (2), motor drive mechanism function unit be used for pilot control send lock, unlock command, alerting tone remove parts be used for pilot control remove sound alarm;
Wheel load bearing component provides wheel whether carrying signal to decision circuit;
Decision circuit judges whether wheel load bearing component carries, judge rudder face lock status, send sound light alarm command triggers sound light display and shows that alarm components carries out the display of rudder face lock status and alarm prompt, judgement throttle lever position;
Throttle lever provides throttle lever position to decision circuit;
The instruction of execution unit receive logic circuit, carries out rudder face unblock, locks, and by rudder face lock status feedback logic circuit;
Sound light display shows the instruction of alarm components receive logic circuit, carries out the display of rudder face lock status and alarm prompt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210061052.0A CN103303466B (en) | 2012-03-09 | 2012-03-09 | A kind of aircraft rudder surface lock error protection electric control method and system thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210061052.0A CN103303466B (en) | 2012-03-09 | 2012-03-09 | A kind of aircraft rudder surface lock error protection electric control method and system thereof |
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| Publication Number | Publication Date |
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| CN103303466A CN103303466A (en) | 2013-09-18 |
| CN103303466B true CN103303466B (en) | 2016-03-30 |
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| CN201210061052.0A Active CN103303466B (en) | 2012-03-09 | 2012-03-09 | A kind of aircraft rudder surface lock error protection electric control method and system thereof |
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| CN109521750B (en) * | 2018-03-16 | 2021-12-03 | 陕西飞机工业（集团）有限公司 | Shutdown brake control system |
| CN112255476A (en) * | 2020-09-22 | 2021-01-22 | 兰州万里航空机电有限责任公司 | Automatic control circuit applied to aircraft rudder surface lock |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| GB1105201A (en) * | 1965-03-31 | 1968-03-06 | Bendix Corp | Monitoring and testing system for a fail operative control system of an aircraft |
| US4807516A (en) * | 1987-04-23 | 1989-02-28 | The Boeing Company | Flight control system employing three controllers operating a dual actuator |
| FR2738796B1 (en) * | 1995-09-15 | 1997-12-05 | Aerospatiale | METHOD AND DEVICE FOR CONTROLLING THE STEERING GOVERNOR OF AN AIRCRAFT |
| US5911391A (en) * | 1996-05-28 | 1999-06-15 | Russ; Richard T. | Apparatus for locking aircraft controls |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |