CN105620733B - A kind of amphibious aircraft wheel-retracting gear position warning device - Google Patents
A kind of amphibious aircraft wheel-retracting gear position warning device Download PDFInfo
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- CN105620733B CN105620733B CN201410588929.0A CN201410588929A CN105620733B CN 105620733 B CN105620733 B CN 105620733B CN 201410588929 A CN201410588929 A CN 201410588929A CN 105620733 B CN105620733 B CN 105620733B
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Abstract
The invention discloses a kind of amphibious aircraft wheel-retracting gear position warning device, including：Flight alarm computer, landing modes selection device, engine control system, radio altimeter, wing flap control system, landing-gear system, pressable formula red major alarm lamp, audio devices.Electric input interface end connection landing modes selection device, engine control system, radio altimeter, wing flap control system, the landing-gear system of flight alarm computer；Electric output interface end connection pressable formula red major alarm lamp, the audio devices of flight alarm computer；Flight alarm computer alerts logic judgment flow according to the position of wheel-retracting gear and carries out integrated treatment to the relevant information gathered at input interface, and command adapted thereto/information is sent to electric output interface according to result, pressable formula red major alarm lamp, audio devices are driven, visual and acoustically dual alert mode is provided for flight unit.
Description
Technical field
The invention belongs to aircraft system circuit design field, more particularly to a kind of amphibious aircraft wheel-retracting gear
Position warning device.
Background technology
(CCAR-23-R3 " the 729th article of (f) undercarriage police in the 729th article of the airworthiness regulation that Civil Aviation Administration of China promulgates
Accuse " and CCAR-25-R4 " the 729th article of (e) position indicator and warning device ") aircraft equipped with retractable landing gear is proposed
The requirement of setting landing-gear warning device (i.e. aircraft landing form alerts).But the requirement of this airworthiness regulation is only to be directed to continental rise
For aircraft：
1. in order to remind flight unit before undercarriage does not put down and pinned completely, engine throttle not received to rule
Below definite value, in order to avoid aircraft stall occurs and landed with the undercarriage do not put well, land airplane is received in any engine throttle
To more than defined approach fix and when undercarriage does not put down and locked completely, it is necessary to set the audible warning sound of continuous sounding to fill
Put；In order to not disturb the communication of landing period flight unit and ground control, the audible warning device, which should be provided with, manually to stop
The measure of sound, and can automatically recover its audible warning sound when reducing approach fix as defined in any throttle to (or more than) again,
To remind whether flight crew check undercarriage puts down and lock completely.
2. in order to avoid occurring because flight unit needs to complete in a short time in landing period for control aspect
More operation sequence, there is the mistake put down wing flap and forget drop in high-pressure state, land airplane
Wing flap be put into more than defined approach fix and undercarriage do not put down and lock completely when, it is necessary to the sound equipment of continuous sounding is set
Warning device；To ensure safety of landing, the audible warning device, which does not allow to set, manually stops the measure of ringing.
But amphibious aircraft carries retractable landing gear, there are two kinds of different landing states：Terrain landing, the water surface
Landing, the working condition of its undercarriage is with the different and completely different of landing form：
1. when amphibious aircraft selection is landed by land, and any engine throttle is received more than defined position of marching into the arena
Put or wing flap is put into when exceeding defined approach fix, its undercarriage preferably must be held in the state put down and locked completely, otherwise
Hardly imaginable disaster will be caused；
2. when amphibious aircraft selection is in drop in water surface, and any engine throttle is received more than defined position of marching into the arena
Put or wing flap is put into when exceeding defined approach fix, its undercarriage preferably must be held in receives state that is upper and locking completely, otherwise
Hardly imaginable disaster will be caused.
If the landing form that amphibious aircraft is therefore only designed by the requirement of existing airworthiness regulation alerts, will certainly cause
The missing of the aircraft dampening form warning function, this will cause：During aircraft dampening, if undercarriage is not in the drop of safety
Fall state (receive upper and lock completely), due to lacking the warning to flight unit dampening form, can occur in aircraft dampening
Hardly imaginable disaster, such as wheel-retracting gear are destroyed by rush of water, housing construction serious damage.
The content of the invention
The present invention proposes a kind of amphibious aircraft wheel-retracting gear position warning device, can solve the problem that related seaworthiness
Dampening form warning present in wheel-retracting gear position warning (only landing configuration warning) mode required by regulations lacks
The problem of mistake, it can be ensured that amphibious aircraft wheel-retracting gear position warning function (land form warning) it is complete
It is whole：Including landing configuration warning and the warning of dampening form, to improve the security of amphibious aircraft system.
The embodiment of the present invention provides a kind of position warning system of amphibious aircraft wheel-retracting gear, including：Fly
Row alarm computer, landing modes selection device, engine control system, radio altimeter, wing flap control system, undercarriage
Extension and retraction system, pressable formula red major alarm lamp, audio devices；
The flight alarm computer is the core component of the embodiment of the present invention, passes through corresponding electrically input interface and institute
State the landing modes selection device, engine control system, the radio altimeter, the wing flap control system, described
Landing-gear system is crosslinked, and gathers the state parameter or service data of correlation, and warn according to the landing form of computer-internal
Accuse logic judgment flow and integrated treatment is carried out to the Various types of data gathered, and corresponding electrically output is passed through according to result
Interface is crosslinked with the pressable formula red major alarm lamp, the audio devices, sends corresponding light command signal, audio number
It is believed that breath, corresponding warning mode (red light flicker, continuous sound prompt) is provided for flight unit.
The landing modes selection device is a third gear switch：The land, water surface, neutrality, calculated to the flight alarm
Machine exports three landing modes selection signals：Terrain landing mode signal, drop in water surface mode signal, neutral manner signal.When
Terrain landing mode signal is effective when switch is placed in " land " position, represents that aircraft will use terrain landing mode；When switch is put
Drop in water surface mode signal is effective when " water surface " position, represents that aircraft will use drop in water surface mode；When switch is placed in " in
It is vertical " position when neutral manner signal it is effective, represent that aircraft not yet carries out the selection operation of landing modes.
The engine control system provides throttle commands signal by throttle lever for engine, for controlling engine oil
The size of door.Multiple manipulation gears are set at throttle lever, and it is corresponding to provide to be corresponding with corresponding position switch at each gear
Throttle lever positional information (throttle lever slow train position positional information etc.), and send to it is described flight alarm computer carry out undercarriage
The integrated treatments such as the logic judgment of jack position warning, wherein throttle lever slow train position positional information represent that throttle is recovered to just
Normal landing approach position.
The radio altimeter is launched by its transceiver, receives radio wave, and measurement radio wave is from aircraft to ground
The face time that return aircraft is undergone from ground again, the actual height on plane distance ground is obtained after resolving, after resolving
Height value sends the flight alarm computer to digital data format through data/address bus, for carrying out wheel-retracting gear
The integrated treatments such as the logic judgment of position warning.
The wing flap control system by flap control handle for trailing edge flap provide command signal-be used for control the trailing edge flap
The folding and unfolding of the wing, control trailing edge flap to require to complete folding and unfolding according to instruction by wing flap control assembly and calculated for the flight alarm
Machine offer data message-be used for feeding back the information such as the state of wing flap control system.Multiple manipulation gears are set at control crank, often
Corresponding location of instruction sensor is corresponded at individual gear, the mechanical order of flight unit is converted into electric signal transmission gives wing flap control
Component processed, for controlling the folding and unfolding of trailing edge flap；Trailing edge flap folding and unfolding position is provided with flap position transducer, by the trailing edge flap
The current positional information of the wing (wing flap landing position positional information etc.) feeds back to wing flap control unit, is transmitted by wing flap control unit
Computer is alerted to the flight, for carrying out the integrated treatments such as the logic judgment of wheel-retracting gear position warning, wherein
Wing flap landing position positional information represents that wing flap is lowered into normal landing approach fix.
The landing-gear system provides command signal-be used for controlling and rising and falling by undercarriage joystick for undercarriage
The folding and unfolding of frame, control undercarriage to require to complete folding and unfolding according to instruction by undercarriage control unit and calculated for the flight alarm
Machine offer data message-be used for feeding back the information such as the state of landing-gear system.Multiple gears are set at joystick, each
Corresponding location of instruction sensor is corresponding with gear, the mechanical order of flight unit is converted into electric signal transmission to undercarriage
Control unit, for controlling the folding and unfolding of undercarriage；Undercarriage control position sets a variety of position sensors, by undercarriage control
The current status information of system (information such as undercarriage is put down and locked completely, undercarriage is received above and locked completely) feeds back to and risen and fallen
Frame control unit, the flight alarm computer is sent to by undercarriage control unit, for carrying out wheel-retracting gear
The integrated treatments such as the logic judgment of position warning.
The pressable formula red major alarm lamp alerts the light command signal come transmitted by computer according to the flight
Red light warning is provided for flight unit；The emergency warning lamp has pressing reset function simultaneously, i.e., can by pressing the emergency warning lamp
Realize the suppression function of corresponding light warning and audible warning sound.
The audio devices by receive it is described flight alarm computer transmitted by come audio data information be flying machine
Group provides continuous audible warning sound.
Further, a kind of position warning system of amphibious aircraft wheel-retracting gear may also include remotely
Data concentrator (configurable multiple), the remote data concentrator is disposed adjacent to aircraft sensors source by nearby principle
Place, the integrated treatments such as analog-to-digital conversion are carried out to various kinds of sensors data；The electric input interface of the remote data concentrator with
The landing modes selection device, the engine control system, the radio altimeter, the wing flap control system, institute
Landing-gear system crosslinking is stated, gathers the state parameter or service data of correlation, the parameter collected or data are by related
The integrated treatment such as analog-to-digital conversion after by the electric output interface of the remote data concentrator, be sent to the flight alarm
Computer.
A kind of position warning system of amphibious aircraft wheel-retracting gear provided in an embodiment of the present invention, have with
Lower beneficial effect：Landing modes selection device, power management system are connected at the electric input interface of flight alarm computer
System, radio altimeter, wing flap control system, landing-gear system, and pressable formula is connected at its electric output interface
Red major alarm lamp, audio devices.
1. by gathering the positional information of landing modes selection device, the current landing modes of aircraft are can determine whether out；
2. by gathering the number of the positional information of throttle lever slow train position and radio altimeter in engine control system
It is believed that breath, can determine whether out whether throttle is recovered to normal landing approach fix；
3. by gathering the positional information of wing flap landing position in wing flap control system, it can determine whether out whether wing flap is lowered into just
Normal landing approach position；
4. by gathering the folding and unfolding status information of undercarriage in landing-gear system, it can determine whether out that undercarriage is put completely
Under/receipts on and lock；
5. by driving pressable formula red major alarm lamp, it is possible to provide the red light warning of undercarriage control position refers to
Show；
6. by driving audio devices, it is possible to provide the audible warning sound instruction of undercarriage control position；
7. by pressing pressable formula red major alarm lamp, can suppress by throttle lever slow train position, low radio altimeter institute
Caused position warning；
The characteristics of present invention is directed to amphibious aircraft wheel-retracting gear, there is provided more complete position warning solution
Certainly approach, flight unit amphibious aircraft can be effectively warned in two kinds of drop in water surface, terrain landing different landing modes
The abnormal landing form that wheel-retracting gear occurs, timely to take corresponding workaround, improves aircraft
Security, there is larger practical value.
Brief description of the drawings
Fig. 1 is an a kind of reality of the position warning system of amphibious aircraft wheel-retracting gear provided by the invention
Apply the structural representation of example；Fig. 2 is a kind of position warning system of amphibious aircraft wheel-retracting gear provided by the invention
The structural representation of another embodiment of system；
In figure, 101-109 is the aircraft system/equipment related to wheel-retracting gear position warning system, and A-H is
Fall the criterion needed for the warning of frame jack position.Wherein 101 be flight alarm computer, and 102 be landing modes selection device,
103 be power operation part-throttle lever, and 104 be radio altimeter, and 105 be wing flap control assembly, and 106 be that undercarriage is received
Place system, 107 be main emergency warning lamp, and 108 be loudspeaker, and 109 be remote data concentrator, and A is undercarriage control status system, B
It is landing modes status information for flap configuration information, C radio altitude information, D throttle lever positional informations, E, F believes for light
Breath, G are aural information, and H is comprehensive warning message.
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, rather than whole embodiments.It is based on
Embodiment in the present invention, those of ordinary skill in the art are obtained every other under the premise of creative work is not made
Embodiment, belong to the scope of protection of the invention.
The present invention provides a kind of amphibious aircraft wheel-retracting gear position warning device, can solve the problem that amphibious
The problem of wheel-retracting gear position warning of the aircraft under different landing modes indicates, effectively improve the safety of system
Property.
It is the one of a kind of amphibious aircraft wheel-retracting gear position warning system provided by the invention referring to Fig. 1
The structural representation of individual embodiment.
The embodiment of the present invention provides a kind of position warning system of amphibious aircraft wheel-retracting gear, including：Fly
Row alarm computer 101, landing modes selection device 102, engine control system-throttle lever 103, radio altimeter 104,
Wing flap control system-wing flap control assembly 105, landing-gear system 106, pressable formula red major alarm lamp 107, audio dress
Put 108.It is specific as follows：
The electric input interface end connection landing modes selection device 102 of flight alarm computer 101, power management system
System-throttle lever 103, radio altimeter 104, wing flap control system-wing flap control assembly 105, landing-gear system 106,
Electric output interface end connection pressable formula red major alarm lamp 107, audio devices 108.
Position selection signal of the flight alarm computer 101 in landing modes selection device 102, determines that aircraft is current
Landing modes：When switch is placed in " land " position, terrain landing mode signal is effective, then it represents that aircraft will use land drop
Fall mode；When switch is placed in " water surface " position, drop in water surface mode signal is effective, then it represents that aircraft will use drop in water surface side
Formula；When switch is placed in " neutrality " position, neutral manner signal is effective, then it represents that aircraft not yet carries out the selection behaviour of landing modes
Make.
Slow train position position signalling and nothing of the flight alarm computer 101 in engine control system-throttle lever 103
The altitude information of line electrical height table 104, determine the current landing form of aircraft：When one or more throttle lever slow train position positions are believed
Number effectively, and radio altitude be less than 800 feet, then it represents that one or more throttles have been retracted into defined landing approach position
Put, i.e., aircraft is currently in regular descent program.
Wing flap landing position position letter of the flight alarm computer 101 in wing flap control system-wing flap control assembly 105
Number, determine the current landing form of aircraft：When wing flap landing position position signalling it is effective, then it represents that wing flap be lowered into as defined in
Land approach fix, i.e. aircraft are currently in regular descent program.
Undercarriage control position signalling of the flight alarm computer 101 in landing-gear system 106, it is determined that rising and falling
The current folding and unfolding state of frame：When undercarriage stowage position signalling effectively then represents undercarriage, receipts are upper completely and lock, on the contrary then table
Show that undercarriage is not received upper and locked completely；When gear down position signalling effectively then represents that undercarriage puts down and locked completely,
On the contrary then expression undercarriage does not put down and locked completely.
Position selection signal of the flight alarm computer 101 according to landing modes selection device 102, power management system
The slow train position position signalling of system-throttle lever 103, the altitude information of radio altimeter 104, wing flap control system-wing flap control
The wing flap landing position position signalling of component 105 and the undercarriage control position signalling of landing-gear system 106, it is determined that currently
The position warning form of wheel-retracting gear, and then output light warning instructs, audio-alert data-driven pressable formula is red
Color major alarm lamp 107, audio devices 108, lamplight pointing, audible warning sound are provided for flight unit：
1. landing modes alert：If not yet select landing modes (non-selected terrain landing when aircraft prepares to land
Or drop in water surface), then (lamplight pointing, audible warning sound) is given a warning to flight unit to prompt flight unit optimum selection reasonably to drop
Fall mode.
● when flight alarm computer 101 collect one or several slow train position position signallings of throttle lever 103 effectively and nothing
The data of line electrical height table 104 be less than 800 feet, and landing modes selection device 102 not in " water surface " or " land " position (i.e.
Neutral manner signal is effective) when, flight alarm computer 101 sends light warning order-driven pressable formula red major alarm
Lamp 107 provides red light flicker warning, transmission audio-alert data-driven audio devices 108 provide continuous audible warning sound.
The warning can be inhibited by pressing red major alarm lamp 107：Red major alarm lamp extinguishes, while audible warning sound
Terminate.When reducing any throttle again to (or more than) slow train position position, it will restart the warning.
● the wing flap landing position in wing flap control system-wing flap control assembly 105 is collected when flight alarm computer 101
Position signalling is effective, and landing modes selection device 102 is not in " water surface " or " land " position (i.e. neutral manner signal is effective)
When, flight alarm computer 101 sends light warning order-driven pressable formula red major alarm lamp 107 and provides red light
Flicker warning, transmission audio-alert data-driven audio devices 108 provide continuous audible warning sound.
Requirement is provided by CCAR25, the warning is not provided with any artificial braking measure, and pressing red major alarm lamp 107 can not
Suppress the warning.
2. terrain landing alerts：If when aircraft prepare terrain landing when undercarriage do not put down and lock completely, to fly
Row unit gives a warning (lamplight pointing, audible warning sound) to prompt flight unit optimum selection rational operation sequence, avoids endangering
And the catastrophic failure of aircraft safety.
● when flight alarm computer 101 collect landing modes selection device 102 terrain landing mode signal it is effective,
And one or several throttle levers 103 slow train position position signalling effectively and radio altimeter 104 data be less than 800 feet,
And the gear down position signalling in landing-gear system 106 it is invalid when, the flight alarm computer 101 send light police
Order-driven pressable formula red major alarm lamp 107 is accused red light flicker warning is provided, sends audio-alert data-driven sound
Frequency device 108 provides continuous audible warning sound.
The warning can be inhibited by pressing red major alarm lamp 107：Red major alarm lamp extinguishes, while audible warning sound
Terminate.When reducing any throttle again to (or more than) slow train position position, it will restart the warning.
● when flight alarm computer 101 collect landing modes selection device 102 terrain landing mode signal it is effective,
And the wing flap landing position position signalling in wing flap control system-wing flap control assembly 105 is effective, and landing-gear system 106
In gear down position signalling it is invalid when, the flight alarm computer 101 send light warning order-driven pressable formula
Red major alarm lamp 107 provides red light flicker warning, sends the offer continuant of audio-alert data-driven audio devices 108
Ring warning.
Requirement is provided by CCAR25, the warning is not provided with any artificial braking measure, and pressing red major alarm lamp 107 can not
Suppress the warning.
3. drop in water surface alerts：When aircraft prepares drop in water surface, if undercarriage is not packed up and locked completely, to flight
Unit gives a warning (lamplight pointing, audible warning sound) to prompt flight unit optimum selection rational operation sequence, avoids jeopardizing
The catastrophic failure of aircraft safety.
● when flight alarm computer 101 collect landing modes selection device 102 water landing mode signal it is effective,
And one or several throttle levers 103 slow train position position signalling effectively and radio altimeter 104 data be less than 800 feet,
And the undercarriage stowage position signalling in landing-gear system 106 it is invalid when, the flight alarm computer 101 send light police
Order-driven pressable formula red major alarm lamp 107 is accused red light flicker warning is provided, sends audio-alert data-driven sound
Frequency device 108 provides continuous audible warning sound.
The warning can be inhibited by pressing red major alarm lamp 107：Red major alarm lamp extinguishes, while audible warning sound
Terminate.When reducing any throttle again to (or more than) slow train position position, it will restart the warning.
● when flight alarm computer 101 collect landing modes selection device 102 water landing mode signal it is effective,
And the wing flap landing position position signalling in wing flap control system-wing flap control assembly 105 is effective, and landing-gear system 106
In undercarriage stowage position signalling it is invalid when, the flight alarm computer 101 send light warning order-driven pressable formula
Red major alarm lamp 107 provides red light flicker warning, sends the offer continuant of audio-alert data-driven audio devices 108
Ring warning.
Requirement is provided by CCAR25, the warning is not provided with any artificial braking measure, and pressing red major alarm lamp 107 can not
Suppress the warning.
The position warning device of amphibious aircraft wheel-retracting gear provided in an embodiment of the present invention, have with following
Beneficial effect：Landing modes selection device, engine control system, nothing are connected at the electric input interface of flight alarm computer
Line electrical height table, wing flap control system, landing-gear system, and the red master of pressable formula is connected at its electric output interface
Emergency warning lamp, audio devices.
1. by gathering the positional information of landing modes selection device, the current landing modes of aircraft are can determine whether out；
2. by gathering the number of the positional information of throttle lever slow train position and radio altimeter in engine control system
It is believed that breath, can determine whether out whether throttle is recovered to normal landing approach fix；
3. by gathering the positional information of wing flap landing position in wing flap control system, it can determine whether out whether wing flap is lowered into just
Normal landing approach position；
4. by gathering the folding and unfolding status information of undercarriage in landing-gear system, it can determine whether out that undercarriage is put completely
Under/receipts on and lock；
5. by driving pressable formula red major alarm lamp, it is possible to provide the red light warning of undercarriage control position refers to
Show；
6. by driving audio devices, it is possible to provide the audible warning sound instruction of undercarriage control position；
7. by pressing pressable formula red major alarm lamp, can suppress by throttle lever slow train position, low radio altimeter institute
Caused position warning；
It is a kind of position warning system of amphibious aircraft wheel-retracting gear provided by the invention referring to Fig. 2
The structural representation of another embodiment.It can also be wrapped in the position warning device of the amphibious aircraft wheel-retracting gear
Remote data concentrator 109 (configurable multiple) is included, the remote data concentrator 109 is disposed adjacent to aircraft by nearby principle
At sensor source, the integrated treatments such as analog-to-digital conversion are carried out to various kinds of sensors data；The remote data concentrator it is electric
Input interface and the landing modes selection device 102, the engine control system 103, the radio altimeter 104,
The wing flap control system 105, the landing-gear system 106 are crosslinked, and are gathered the state parameter or service data of correlation, are adopted
The parameter or data collected is after the integrated treatments such as the analog-to-digital conversion of correlation by the electric defeated of the remote data concentrator
Outgoing interface, it is sent to the flight alarm computer 101.By the introducing of the embodiment medium-long range data concentrator 109, can enter
Collection, integrated treatment and the concentration of transmissions of realizing different grades of electromechanical subsystem signals of one step, so as to improve Mechatronic Systems/
Sharing for facility information, reduces the quantity of full machine wire, the complexity of aircraft wiring is reduced, so as to strengthen whole aircraft system
Security and maintainability.
The characteristics of present invention is directed to amphibious aircraft wheel-retracting gear, there is provided more complete position warning solution
Certainly approach, flight unit amphibious aircraft can be effectively warned in two kinds of drop in water surface, terrain landing different landing modes
The abnormal landing form that wheel-retracting gear occurs, timely to take corresponding workaround, improves aircraft
Security, there is larger practical value.
Described above is the preferred embodiment of the present invention, it is noted that for those skilled in the art
For, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications are also considered as
Protection scope of the present invention.
Claims (5)
- A kind of 1. amphibious aircraft wheel-retracting gear position warning device, it is characterised in that its outside interconnected system bag Include：Flight alarm computer, landing modes selection device, engine control system, radio altimeter, wing flap control system, Landing-gear system, pressable formula red major alarm lamp, audio devices；The electric input interface end connection landing modes selection device of the flight alarm computer, engine control system, nothing Line electrical height table, wing flap control system, landing-gear system；Electric output interface end connection pressable formula red major alarm lamp, the audio devices of the flight alarm computer；It is describedFlight alarm computer alerts logic judgment flow to being gathered at input interface according to the position of wheel-retracting gear To the landing modes selection device in landing modes status information, the throttle lever position in the engine control system Information, the elevation information in the radio altimeter, the flap configuration information in the wing flap control system, the undercarriage Undercarriage control status information in extension and retraction system carries out integrated treatment, and sends corresponding light warning according to result and refer to Make, audio-alert information to output interface, drive the pressable formula red major alarm lamp, the audio devices, be flying machine Group provides dual alert mode visual, acoustically.
- 2. wheel-retracting gear position as claimed in claim 1 warning device, it is characterised in that the position warning device Also include remote data concentrator；The remote data concentrator is disposed adjacent at aircraft sensors source by nearby principle, The integrated treatments such as analog-to-digital conversion are carried out to various kinds of sensors data；The electric input interface of the remote data concentrator with it is described Landing modes selection device, the engine control system, the radio altimeter, the wing flap control system, described Fall the crosslinking of frame extension and retraction system, gather the state parameter or service data of correlation, the parameter collected or data are by related mould By the electric output interface of the remote data concentrator after the integrated treatments such as number conversion, it is sent to the flight alarm and calculates Machine.
- 3. wheel-retracting gear position as claimed in claim 1 warning device, it is characterised in that the flight alarm calculates Machine examination measures：Neutral manner signal is effective in the landing modes selection device, and has one in the engine control system The radio altimeter data are less than 800 feet, or institute while individual or several throttle lever slow train positions position signalling is effective It is effective to state in wing flap control system wing flap landing position position signalling, then corresponding instruction/data is sent by electric output interface, The pressable formula red major alarm lamp and the audio devices are triggered to provide light warning and audible warning sound；Started by described Warning caused by the slow parking space state of machine steerable system throttle lever and the radio altimeter data can be by can described in pressing Push type red major alarm lamp is inhibited, and the warning after suppression obtains when then reducing any throttle again to slow train position position To restarting；Do not allowed to set any artificial suppression as the warning caused by wing flap control system wing flap landing position state Measure.
- 4. wheel-retracting gear position as claimed in claim 1 warning device, it is characterised in that the flight alarm calculates Machine examination measures：Terrain landing mode signal is effective in the landing modes selection device, is risen and fallen in the landing-gear system Frame extended position signal is effective, and one or several throttle lever slow train position position signallings in the engine control system be present The radio altimeter data are less than wing flap landing position position in 800 feet, or the wing flap control system while effectively Signal is effective, then sends corresponding instruction/data by electric output interface, trigger the pressable formula red major alarm lamp and The audio devices with provide light warning and audible warning sound；By the slow parking space state of the engine control system throttle lever and institute Stating the warning caused by radio altimeter data can be inhibited by pressing the pressable formula red major alarm lamp, be suppressed Warning afterwards is restarted when then reducing any throttle again to slow train position position；By the wing flap control system flap Warning caused by wing landing position state does not allow to set any artificial braking measure.
- 5. wheel-retracting gear position as claimed in claim 1 warning device, it is characterised in that the flight alarm calculates Machine examination measures：Landing modes signal is effective in the landing modes selection device reclaimed water, is risen and fallen in the landing-gear system Frame retracted position signal is effective, and one or several throttle lever slow train position position signallings in the engine control system be present The radio altimeter data are less than wing flap landing position position in 800 feet, or the wing flap control system while effectively Signal is effective, then sends corresponding instruction/data by electric output interface, trigger the pressable formula red major alarm lamp and The audio devices with provide light warning and audible warning sound；By the slow parking space state of the engine control system throttle lever and institute Stating the warning caused by radio altimeter data can be inhibited by pressing the pressable formula red major alarm lamp, be suppressed Warning afterwards is restarted when then reducing any throttle again to slow train position position；By the wing flap control system flap Warning caused by wing landing position state does not allow to set any artificial braking measure.
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| CN201410588929.0A CN105620733B (en) | 2014-10-28 | 2014-10-28 | A kind of amphibious aircraft wheel-retracting gear position warning device |
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| CN201410588929.0A CN105620733B (en) | 2014-10-28 | 2014-10-28 | A kind of amphibious aircraft wheel-retracting gear position warning device |
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| CN105620733A CN105620733A (en) | 2016-06-01 |
| CN105620733B true CN105620733B (en) | 2017-11-17 |
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| CN109144079B (en) * | 2018-08-22 | 2021-04-23 | 中国民航大学 | Amphibious aircraft landing configuration control system based on integrated avionics |
| CN109733626B (en) * | 2018-11-12 | 2023-06-30 | 中航通飞华南飞机工业有限公司 | Amphibious aircraft cabin door alarm and indication system |
| CN109720590B (en) * | 2018-11-12 | 2023-03-28 | 中航通飞华南飞机工业有限公司 | Alarm and indication system for starting process of multi-turboprop engine of amphibious aircraft |
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| CN110824470B (en) * | 2019-10-12 | 2024-04-16 | 中航通飞华南飞机工业有限公司 | Radio altitude data processing method of amphibious aircraft |
| CN111324117B (en) * | 2020-01-20 | 2021-01-08 | 郑州宇通重工有限公司 | Login auxiliary control method and system for special vehicle and computer storage medium |
| CN112623271B (en) * | 2020-12-25 | 2023-08-18 | 中电科芜湖钻石飞机制造有限公司 | Test equipment for comprehensive control console of general aircraft |
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