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
- Publication number
- 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
- Authority
- CN
- China
- Prior art keywords
- sound
- component
- alarm
- control surface
- logic circuit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 17
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 230000000007 visual effect Effects 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Landscapes
- Emergency Alarm Devices (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
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 an anti-error design method for an aircraft control surface lock, in particular to an anti-error design method which comprehensively considers the use characteristics of an aircraft main control surface on the ground and before take-off, carries out electrical design, is crosslinked with multiple systems, designs a circuit interlocking and acoustic and optical alarm mode, carries out anti-error design and ensures the safe use of the aircraft main control surface in locking and unlocking states.
Background
When the airplane is parked on the ground, in order to avoid the situation that the main rudder surface swings due to wind blowing and the transmission mechanism of the control surface and the control system is damaged, the control surface locking system locks and fixes the elevator, the rudder and the ailerons, and the control surface free movement is not influenced in the air. The locking of the main rudder surface of large and medium-sized airplane control systems generally adopts a mechanical locking device or an electromechanical locking device, and an anti-error design formed by the electromechanical locking device generally arranges an indicator light near an electric switch on the rudder surface locking system to prompt that a system power supply must be manually disconnected before takeoff after the airplane rudder surface is relieved from limitation; a control surface locking indicator light and a control surface unlocking indicator light are arranged near the control surface lock control switch; on the takeoff signal board, an indicator light is arranged, wherein the control surface of the indicator light is not completely unlocked; the control surface is not completely unlocked and the brake is not turned off, and the voice alarm is given after the throttle lever is pushed. Before the airplane takes off, the working power supply of the control surface lock system needs to be manually disconnected, so that the possibility of misoperation exists; when the control surface is not completely unlocked, only the light alarms in a visible range, and the whole machine set personnel cannot be considered, so that the possibility of misoperation exists.
The design of the airplane control surface lock for preventing errors and electric control errors adopts a logic circuit to be crosslinked with a bearing component of an airplane wheel of an airplane, so that a control power supply of a control surface lock system is automatically disconnected after the airplane leaves, and the airplane control surface is prevented from being locked by mistake in the air; a logic circuit is adopted to be crosslinked with the sound and light display alarm component, when the control surface lock is not completely unlocked, the visual range light prompt is removed, and sound alarm is carried out on all crew members in the cockpit through the sound and light display alarm component. Considering that the airplane is on the ground, the control surface is unlocked for a long time and the sound alarm is clear and crisp, the alarm sound releasing component is designed to release the sound alarm. The alarm device is linked with the accelerator lever, if the control surface lock is not completely unlocked, the sound and light display alarm device gives a sound and light alarm, the alarm sound releasing device is pressed to release the sound alarm, the accelerator lever is pushed, the sound alarm can be triggered again, and the alarm sound releasing device is operated, so that the sound alarm cannot be released, and the control surface unlocking is prompted.
Disclosure of Invention
The technical problems to be solved by the invention are as follows:
the invention overcomes the defects of the prior electromechanical control surface locking device that the control surface is locked by mistake in the air and the control surface is not unlocked and the light prompts the visual range is not complete, and provides an error-proof design method.
The technical scheme of the invention is as follows:
in order to solve the technical problems, the invention is realized by the following technical scheme: a logic circuit is adopted to be crosslinked with the airplane wheel bearing component, and a control power supply of a control surface lock is automatically cut off after the airplane is lifted off the ground, so that the aerial control surface is prevented from being locked by mistake; and the logic circuit and the sound and light display alarm part are linked, so that the sound and light combined prompt is realized, all crew members are prompted to know the un-unlocked state, and the control surface is ensured to be completely unlocked before taking off.
An error-proof design method for an aircraft control surface lock comprises the following steps:
firstly, connecting a power supply of an airplane rudder surface lock system;
secondly, the logic circuit judges the airplane wheel bearing component, if the airplane wheel bearing component is not borne, namely the airplane is lifted off the ground, the third step is executed, and if the airplane wheel bearing component is borne, namely the airplane is on the ground, the sixth step is executed;
thirdly, cutting off a control power supply of the control surface lock;
fourthly, the sound and light display alarm component carries out control surface unlocking light prompt;
fifthly, at the moment, the driver operates the electric mechanism control component, the locking instruction cannot be sent, and the process is ended;
sixthly, judging whether the airplane takes off or is parked by the driver, executing the seventh step if the airplane is parked, and executing the eleventh step if the airplane takes off;
seventhly, judging whether the lock state of the control surface is locked by the logic circuit, if so, executing the eighth step, and if not, executing the ninth step;
eighthly, the sound and light display alarm part carries out the light prompt of the locking of the control surface, and the process is finished;
ninth, the logic circuit triggers the sound and light display alarm component to display that the control surface is unlocked;
tenth step, the driver operates the electric mechanism control component to lock the control surface, and the seventh step is executed;
step ten, the logic circuit judges whether the rudder surface lock is unlocked, if the rudder surface lock is unlocked, the twelfth step is executed, and if the rudder surface lock is not unlocked, the thirteenth step is executed;
and step twelve, the sound and light display alarm part carries out control surface unlocking light prompt, and the process is finished.
Step thirteen, the logic circuit sends out a sound and light alarm instruction to the sound and light display alarm component, and the sound and light display alarm component carries out sound and light alarm and prompts a driver to remove the control surface;
fourteenth, the logic circuit judges whether the driver operates the warning sound removing part, if not, the fifteenth step is executed, and if so, the sixteenth step is executed;
fifteenth step, the driver operates the electric mechanism control component to unlock the control surface, and the eleventh step is executed;
sixthly, the logic circuit releases the sound alarm and still sends a light alarm instruction, and the sound and light display alarm component only carries out light alarm and prompts a driver to release the control surface;
seventeenth, the logic circuit judges whether the driver pushes the throttle lever, if not, the fifteenth step is executed, and if the throttle lever is pushed, the eighteenth step is executed;
eighteen, the logic circuit triggers the sound alarm again, and the sound and light display alarm part only carries out sound and light alarm to prompt the driver to remove the control surface;
nineteenth step, the driver operates the warning sound releasing section so that the sound warning cannot be released, and fifteenth step is executed.
An aircraft control surface lock error protection electrical control system comprising: the control component, the wheel bearing component 3, the logic circuit 4, the throttle lever 5, the execution component 6 and the audio and visual display alarm component 7; wherein,
the control component comprises an electric mechanism control component 1 and an alarm sound relieving component 2, wherein the electric mechanism control component is used for a driver to operate and send locking and unlocking instructions, and the alarm sound relieving component is used for the driver to operate and relieve sound alarm;
the airplane wheel bearing component provides a signal for the logic circuit whether the airplane wheel bears or not;
the logic circuit judges whether the airplane wheel bearing component bears the weight, judges the lock state of the control surface, sends out an audio-optical alarm instruction to trigger an audio-optical display alarm component to display the lock state of the control surface and give an alarm prompt, and judges the position of the throttle lever;
the throttle lever provides the throttle lever position to the logic circuit;
the executive component receives the instruction of the logic circuit, unlocks and locks the control surface and feeds back the locking state of the control surface to the logic circuit;
and the sound and light display alarm part receives the logic circuit instruction and displays and gives an alarm for the locking state of the control surface.
The invention has the beneficial effects that:
compared with the prior art, the invention has the advantages that: the control power supply of the control surface lock is automatically disconnected after the airplane is off the ground, so that the control surface in the air is prevented from being locked by mistake; when the control surface is not unlocked, the driver is prompted by a method of combining light and sound, the coverage is complete, and the mistaken takeoff without unlocking is prevented.
Drawings
FIG. 1 is a flow chart of the error-proof electrical control method for the aircraft control surface lock;
fig. 2 is a schematic block diagram of the error-proof electrical control system of the aircraft rudder surface lock.
Detailed Description
The invention is described in further detail below with reference to the following detailed description and accompanying drawings:
an aircraft control surface lock error protection electrical control system comprising: the control component, the wheel bearing component 3, the logic circuit 4, the throttle lever 5, the execution component 6 and the audio and visual display alarm component 7; wherein,
the control component comprises an electric mechanism control component 1 and an alarm sound relieving component 2, wherein the electric mechanism control component is used for a driver to operate and send locking and unlocking instructions, and the alarm sound relieving component is used for the driver to operate and relieve sound alarm;
the airplane wheel bearing component provides a signal for the logic circuit whether the airplane wheel bears or not;
the logic circuit judges whether the airplane wheel bearing component bears the weight, judges the lock state of the control surface, sends out an audio-optical alarm instruction to trigger an audio-optical display alarm component to display the lock state of the control surface and give an alarm prompt, and judges the position of the throttle lever;
the throttle lever provides the throttle lever position to the logic circuit;
the executive component receives the instruction of the logic circuit, unlocks and locks the control surface and feeds back the locking state of the control surface to the logic circuit;
and the sound and light display alarm part receives the logic circuit instruction and displays and gives an alarm for the locking state of the control surface.
After the airplane is off the ground, the airplane wheel bearing component provides an airplane wheel non-bearing signal for the logic circuit, and the logic circuit cuts off a control surface lock control power supply of the electric mechanism control component to ensure that an aerial control surface cannot be locked.
Before the airplane takes off, the executing component provides the state of the control surface lock to the logic circuit, the logic circuit judges whether the control surface lock is unlocked, when the lock is not unlocked, the logic circuit sends out a sound and light alarm instruction, the sound and light display alarm component gives a sound and light alarm to prompt a driver to unlock the control surface, the driver can release the sound alarm through the alarm sound, but can not release the light alarm, if the control surface is not completely unlocked, the driver pushes the throttle stick to take off, the logic circuit triggers the sound alarm again to prompt the driver to completely unlock the control surface.
Claims (2)
1. An error-proof design method for an aircraft control surface lock is characterized by comprising the following steps:
firstly, switching on a power supply system of an aircraft control surface lock system;
secondly, the logic circuit judges the airplane wheel bearing component, if the airplane wheel bearing component is not borne, namely the airplane is lifted off the ground, the third step is executed, and if the airplane wheel bearing component is borne, namely the airplane is on the ground, the sixth step is executed;
thirdly, cutting off a control power supply of the control surface lock;
fourthly, the sound and light display alarm component carries out control surface unlocking light prompt;
fifthly, at the moment, the driver operates the electric mechanism control component, the locking instruction cannot be sent, and the process is ended;
sixthly, judging whether the airplane takes off or is parked by the driver, executing the seventh step if the airplane is parked, and executing the eleventh step if the airplane takes off;
seventhly, judging whether the lock state of the control surface is locked by the logic circuit, if so, executing the eighth step, and if not, executing the ninth step;
eighthly, the sound and light display alarm part carries out the light prompt of the locking of the control surface, and the process is finished;
ninth, the logic circuit triggers the sound and light display alarm component to display that the control surface is unlocked;
tenth step, the driver operates the electric mechanism control component to lock the control surface, and the seventh step is executed;
step ten, the logic circuit judges whether the rudder surface lock is unlocked, if the rudder surface lock is unlocked, the twelfth step is executed, and if the rudder surface lock is not unlocked, the thirteenth step is executed;
twelfth step, the sound and light display alarm part carries out control surface unlocking light prompt, and the process is finished;
step thirteen, the logic circuit sends out a sound and light alarm instruction to the sound and light display alarm component, and the sound and light display alarm component carries out sound and light alarm and prompts a driver to remove the control surface;
fourteenth, the logic circuit judges whether the driver operates the warning sound removing part, if not, the fifteenth step is executed, and if so, the sixteenth step is executed;
fifteenth step, the driver operates the electric mechanism control component to unlock the control surface, and the eleventh step is executed;
sixthly, the logic circuit releases the sound alarm and still sends a light alarm instruction, and the sound and light display alarm component only carries out light alarm and prompts a driver to release the control surface;
seventeenth, the logic circuit judges whether the driver pushes the throttle lever, if not, the fifteenth step is executed, and if the throttle lever is pushed, the eighteenth step is executed;
eighteen, the logic circuit triggers the sound alarm again, and the sound and light display alarm part only carries out sound and light alarm to prompt the driver to remove the control surface;
nineteenth step, the driver operates the warning sound releasing section so that the sound warning cannot be released, and fifteenth step is executed.
2. An error-proof electrical control system of an aircraft control surface lock is characterized by comprising: the airplane wheel control system comprises a control component, an airplane wheel bearing component (3), a logic circuit (4), an accelerator lever (5), an execution component (6) and an acousto-optic display alarm component (7); wherein,
the control component comprises an electric mechanism control component (1) and an alarm sound releasing component (2), wherein the electric mechanism control component is used for a driver to operate and send locking and unlocking instructions, and the alarm sound releasing component is used for the driver to operate and release sound alarm;
the airplane wheel bearing component provides a signal for the logic circuit whether the airplane wheel bears or not;
the logic circuit judges whether the airplane wheel bearing component bears the weight, judges the lock state of the control surface, sends out an audio-optical alarm instruction to trigger an audio-optical display alarm component to display the lock state of the control surface and give an alarm prompt, and judges the position of the throttle lever;
the throttle lever provides the throttle lever position to the logic circuit;
the executive component receives the instruction of the logic circuit, unlocks and locks the control surface and feeds back the locking state of the control surface to the logic circuit;
and the sound and light display alarm part receives the logic circuit instruction and displays and gives an alarm for the locking state of the control surface.
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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103303466A CN103303466A (en) | 2013-09-18 |
| CN103303466B true CN103303466B (en) | 2016-03-30 |
Family
ID=49129278
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103303466B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
-
2012
- 2012-03-09 CN CN201210061052.0A patent/CN103303466B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN103303466A (en) | 2013-09-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105644800B (en) | One kind is taken off warning system | |
| CN103303466B (en) | A kind of aircraft rudder surface lock error protection electric control method and system thereof | |
| EP3702273B1 (en) | Landing gear system operation | |
| RU2595231C2 (en) | System of counselling messages on location of aircraft not on ground | |
| CN110812732A (en) | Fire extinguishing method and system based on airplane platform | |
| CA2702266C (en) | Jettisonable armor | |
| CN204297071U (en) | A kind of amphibious aircraft wheel-retracting gear position warning device | |
| CN110949659A (en) | Trailing edge flap control method | |
| EP4082899A1 (en) | Aircraft system | |
| CN107839894A (en) | The single catch single operation of aircarrier aircraft enters an automatic detection device and operation method | |
| CN211543878U (en) | Undercarriage of aircraft dual redundancy receive and releases controlling device | |
| CN105620770A (en) | Propeller feathering control method | |
| CN113599738B (en) | Aviation fire extinguishing task control system and control method | |
| US3224713A (en) | Landing gear system | |
| CN104670517A (en) | Helicopter landing fixing and takeoff ejection system | |
| CN109521750B (en) | Shutdown brake control system | |
| CN109144079B (en) | Amphibious aircraft landing configuration control system based on integrated avionics | |
| CN112527253A (en) | Alarm and emergency disposal program design method | |
| CN203117677U (en) | Redundant emergency ventilation control system for airplane | |
| CN115626291B (en) | Indication and alarm system for water injection cabin door of fixed wing fire-extinguishing aircraft | |
| CN211874182U (en) | Central control door lock system of luggage compartment of civil aircraft | |
| CN118062228B (en) | Anti-skid brake system, control method, residual pressure fault warning method and disposal method | |
| CN114476100B (en) | Warning system for preventing pilot from being ejected by mistake based on constraint system | |
| CN113895638A (en) | Method for preventing misoperation when aeroengine fails | |
| CN203213708U (en) | Anti-theft lock with true and false lock cylinders |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
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. |