CN105644800B - One kind is taken off warning system - Google Patents
One kind is taken off warning system Download PDFInfo
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- CN105644800B CN105644800B CN201410725362.7A CN201410725362A CN105644800B CN 105644800 B CN105644800 B CN 105644800B CN 201410725362 A CN201410725362 A CN 201410725362A CN 105644800 B CN105644800 B CN 105644800B
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Abstract
It takes off warning system the invention discloses one kind, comprising: flight alarm computer, red major alarm lamp, audio devices and engine control system, flight control system, Landing Gear System, avionics system etc.；The electrical input terminal of flight alarm computer connects each subsystem in the warning system that takes off in addition to red major alarm lamp, audio devices；The electric output terminal of flight alarm computer connects red major alarm lamp, audio devices；Flight alarm computer alerts logic judgment process to the progress integrated treatment of input terminal relevant information collected according to taking off, and command adapted thereto information is sent according to processing result and drives major alarm lamp, audio devices to electric output terminal, sound and the dual alarm of light are provided for flight unit.Using the embodiment of the present invention, can solve take off required by airworthiness regulation warning in missing the water surface take off form warning the problem of, it is ensured that amphibious aircraft takeoff configuration warning it is complete, improve amphibious aircraft system safety.
Description
Technical field
It takes off warning system the invention belongs to aircraft system circuit design field more particularly to one kind.
Background technique
In the 703rd article of airworthiness regulation " warning system of taking off " that Civil Aviation Administration of China promulgates (CCAR-23-R3 " the
703 articles " and CCAR-25-R4 " the 703rd article ") corresponding design is proposed to commuting class, the warning system of taking off of airplane in transportation category
It is required that:
1. the warning form about warning of taking off.It is required that the warning form of system includes that wing flap or leading edge lift unit do not exist
Within the scope of the takeoff setting that aiMonhiness authority is ratified and wing spoiler, flap or longitudinal balancing device be not in permission
Safe take-off position.
2. the continuity about warning of taking off.It is required that the warning time of system must be extended to: the morphologic change of aircraft is fair
Perhaps the form of safe take-off；Driver takes the movement for stopping starting heats；Aircraft reached lift front-wheel speed, liftoff
Fly；Driver artificially cuts off warning, and is not that warning is required to continue up to until aircraft stops completely.
3. the reliability about warning of taking off.It is required that system must be able to the entire weight model in aircraft type examination and approval
Enclose, using guaranteeing to work normally in height and temperature range, do not allow to occur aircraft and meet alarm form, but system without
The phenomenon that alarm.
However with retractable landing gear amphibious aircraft have two different forms of taking off: it is land take off, water
Face is taken off, and different forms of taking off is corresponding with different safe take-off positions:
1. not allowing the form of safe take-off includes wing flap or leading edge liter when amphibious aircraft selection is taken off by land
Power device is not within the scope of the takeoff setting that aiMonhiness authority is ratified and wing spoiler, flap or longitudinal balancing device
It is not in the safe take-off position of permission and the devices such as rudder trimmer and aileron trimmer not in the peace of permission
Full takeoff setting, airplane wheel brake do not discharge, and automatic pilot should all be within the scope of warning in forms such as on-positions.
2. it not only includes 1. described for not allowing the form of safe take-off when amphibious aircraft selection is when the water surface takes off
The form (except airplane wheel brake does not discharge) for not allowing safe take-off further includes that undercarriage is not received upper completely and lockked outside.
In amphibious aircraft water surface take-off process, if undercarriage occur it is abnormal take off form when (failure is in
The position of mistake), it will serious threat is constituted to the flight safety of aircraft, because on undercarriage is not received completely when the water surface takes off
And lock, it will cause acceleration distance increase of taking off, once the case where aborting, aircraft is likely to go out the water surface, makes
At major accident.If only only considering the flap by the warning system of taking off of the requirement design amphibious aircraft of existing airworthiness regulation
The wing, leading edge lift unit, spoiler, flap and longitudinal balancing device etc., will certainly to larger impact produced by flight safety
The case where part when the water surface takes off does not allow safe take-off form warning missing appearance is generated, this will will cause the aircraft water surface and take off
When aerodynamic configuration change, and then cause hardly imaginable disaster.
Summary of the invention
The present invention proposes that one kind is taken off warning system, and warning system of taking off is able to solve required by related airworthiness regulation
The water surface present in (only land take off form warning) mode takes off the missing for not allowing safe take-off position to alert in form, really
It protects and amphibious takes off the complete of warning system function: taking off form warning and the water surface takes off form warning including land,
To improve the safety of amphibious aircraft system.
The embodiment of the present invention provides a kind of amphibious aircraft and takes off warning system, comprising: and flight alarm computer, sky/
Ground system, engine control system, trailing edge flap system, leading edge device (droope snoot and slat), flap system, brake system
System, elevator and elevator trimming system, rudder and rudder trimming system, aileron and aileron trimming system, automatic Pilot/
Flight director sys tem, landing-gear system, air data system, radio altimeter, pressable formula red major alarm lamp, sound
Frequency device.
The flight alarm computer is the core component of the embodiment of the present invention, passes through corresponding electrical input interface and institute
State sky/ground system, the engine control system, the trailing edge flap system, the leading edge device, the flap system,
The brake system, the elevator and elevator trimming system, the rudder and rudder trimming system, the aileron and
Aileron trimming system, the automatic Pilot/flight director sys tem, the landing-gear system, the air data system, institute
Radio altimeter, the pressable formula red major alarm lamp (warning inhibits function) crosslinking are stated, relevant state parameter is acquired
Or operation data, and it is comprehensive to Various types of data collected progress according to the form warning logic judgment process of taking off of computer-internal
Conjunction processing, and can be pressed according to the corresponding light warning instruction of processing result transmission, audio-alert information to output interface driving
Pressure type red major alarm lamp (light warning function), the audio devices provide pair visual, acoustically for flight unit
Weight alert mode.
The sky/ground system provides aerial or ground status signal to aircraft.There is compression to sense on each undercarriage
Device is used to monitor the compression of landing gear shock strut: when landing gear shock strut compression, target proximity sensor, when aircraft exists
Landing gear shock strut is compressed when ground, and compression sensor is triggered and sends signal, place to the signal processing apparatus closed on
Sky/ground discrete signal is passed into the flight again after reason and alerts computer, for the logic judgment for the form warning that take off
Equal integrated treatments.
The radio altimeter measures radio wave from aircraft to ground by the transmitting of its transceiver, reception radio wave
Face returns to the aircraft time experienced from ground again, the actual height on plane distance ground is obtained after resolving, after resolving
Height value sends the flight to through data/address bus with digital data format and alerts computer, for carrying out form warning of taking off
The integrated treatments such as logic judgment.
The engine control system sends thrust position signal to engine control device by throttle lever control crank,
It is resolved back pressure position signal and is converted to throttle commands signal, provided gasoline throttle angle information for engine, start for controlling
The size of machine oil door.There is corresponding position sensor to be used to monitor the movement of throttle lever at throttle lever control crank: when being pushed forward oil
When door rod control crank, target proximity sensor is pushed forward throttle lever control crank, throttle lever position when aircraft is in starting heats
Sensor is triggered and sends signal to the signal processing apparatus closed on, and thrust position signal is passed to described fly again after processing
Row alarm computer, for integrated treatments such as the logic judgments for the form warning that take off.
The trailing edge flap system is by flap control handle normal mode of operation or wing flap electric switch standby operation mode
Trailing edge flap provides the folding and unfolding that command signal-is used to control trailing edge flap, and wing flap control assembly controls trailing edge flap according to instruction
It is required that completing folding and unfolding, and the state etc. that data information-is used to feed back wing flap control system is provided for the flight alarm computer
Information.Multiple manipulation gears are set at control crank, corresponding location of instruction sensor are corresponded at each gear, by flight unit
Mechanical order be converted to electric signal transmission and give wing flap control assembly, for controlling the folding and unfolding of trailing edge flap；Trailing edge flap folding and unfolding
Position sensor is set at position, the current location information of trailing edge flap is fed back into wing flap control unit, passes through wing flap control
Component processed passes to flight alarm computer, for integrated treatments such as the logic judgments for the form warning that take off.
Leading edge device/the system passes through trailing edge flap system (when normal operating) or spare wing flap electric switch (standby operation
When) command signal-of droope snoot and slat is obtained for controlling the movement of leading edge device, wing flap control assembly controls leading edge dress
It sets and requires to complete folding and unfolding according to instruction, position sensor is set at leading edge device folding and unfolding position, by the current position of leading edge device
Confidence breath feeds back to wing flap control unit, then passes to flight alarm computer, patrols for what the form that take off alerted
Collect the integrated treatments such as judgement.
The flap system is manually manipulated by flap handle or automatic retarding board group part manipulates ground flow-disturbing automatically
Plate.Only when aircraft is on ground, when opening flap handle, ground spoiler is just opened.Position is provided at flap handle
The movement of electric switch monitoring flap handle: when flap handle moves into lower bayonet slot position, target approximated position electric switch, when aircraft exists
When speed brake is released, the flap caution position electric switch that takes off is triggered and sends signal to the signal processing apparatus that closes on；
The movement of position sensor monitoring ground spoiler: the ground when aircraft is on ground is set at the spoiler internal lock valve of ground
Spoiler internal lock valve only controls the work of ground spoiler, and when ground spoiler is withdrawn, position sensor is triggered and to facing
Close signal processing apparatus sends signal, and flap takes off caution signal, ground spoiler retracted state signal again after processing
Flight alarm computer is passed to, for integrated treatments such as the logic judgments for the form warning that take off.
The brake system is by parking brake handle and the starting of brake pedal or unclamps parking brake, parking brake handle
There is the movement of parking brake position electric switch monitoring handle at place: when pull-up parking brake handle, target approximated position electric switch is stopped
Normal danger electric switch is triggered and sends signal to the signal processing apparatus closed on, then parking brake status information is passed to institute
Flight alarm computer is stated, for integrated treatments such as the logic judgments for the form warning that take off.
The elevator and elevator trimming system pass through elevator trimming control electric switch and instruct trimmer in institute demander
Trim is carried out upwards, the trim position of position sensor monitoring trimmer, the signal processing device through closing at trimmer
It sets and passes to flight alarm computer, for integrated treatments such as the logic judgments for the form warning that take off.
The rudder and rudder trimming system pass through rudder trimming control knob and instruct trimmer in institute demander
Trim is carried out upwards, the trim position of position sensor monitoring trimmer, the signal processing device through closing at trimmer
It sets and passes to flight alarm computer, for integrated treatments such as the logic judgments for the form warning that take off.
The aileron trimming system aileron trim electric switch instruction trimmer carries out trim, trimmer in the desired direction
Locate the trim position of position sensor monitoring trimmer, the signal processing apparatus through closing on passes to the flight alarm meter
Calculation machine, for integrated treatments such as the logic judgments for the form warning that take off.
Automatic Pilot/the flight director sys tem connects the connection that electric switch realizes automatic Pilot by automatic Pilot, connects
Signal processing apparatus of the status signal of electric switch through closing on passes to the flight alarm computer, alert for the form that take off
The integrated treatments such as the logic judgment of announcement.
The landing-gear system provides command signal-by undercarriage control handle for undercarriage and is used to control to rise and fall
The folding and unfolding of frame requires to complete folding and unfolding and alert for the flight to calculate by undercarriage control unit control undercarriage according to instruction
Machine provides data information-and is used to feed back the information such as the state of landing-gear system.The multiple gears of setting at handle are controlled, each
It is corresponding with corresponding location of instruction sensor at 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；A variety of position sensors are set at undercarriage control position, by undercarriage control
The current status information of system (information such as undercarriage puts down completely and locks, undercarriage is received completely and locked) feeds back to and rises and falls
Frame control unit sends the flight to by undercarriage control unit and alerts computer, for carrying out wheel-retracting gear
The integrated treatments such as the logic judgment of position warning.
The air data system is provided according to static pressure transducer, total pressure sensor, angle of attack sensor, total temperature probe
Static pressure, total pressure, 4 angle of attack, total temperature initial parameters, resolve and export a large amount of atmosphere data parameter, the air speed value after resolving
The flight is sent to through data/address bus with digital data format and alerts computer, and for take off, the logic that form alerts is sentenced
It is disconnected to wait integrated treatments.
The pressable formula red major alarm lamp is according to the light command signal come transmitted by the flight alarm computer
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 inhibition 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, the amphibious aircraft takes off, and to may also include remote data concentrator (configurable more for warning system
It is a), the remote data concentrator is disposed adjacent at aircraft sensors source by nearby principle, to various kinds of sensors data into
The integrated treatments such as row analog-to-digital conversion；The electrical input interface of the remote data concentrator and the sky/ground system described are started
Machine steerable system, the trailing edge flap system, the leading edge device, the flap system, the brake system, the lifting
It is rudder and elevator trimming system, the rudder and rudder trimming system, the aileron and aileron trimming system, described automatic
Driving/flight director sys tem, the landing-gear system, the air data system, radio altimeter crosslinking, are adopted
Collect relevant state parameter or operation data, collected parameter or data are led to after the integrated treatments such as relevant analog-to-digital conversion
The electrical output interface for crossing the remote data concentrator is sent to the flight alarm computer.
Amphibious aircraft provided in an embodiment of the present invention takes off warning system, has the advantages that and accuses in flight
It is (preceding that sky/ground system, engine control system, trailing edge flap system, leading edge device are connected at the electrical input interface of alert computer
Edge wing flap and slat), flap system, brake system, elevator and elevator trimming system, rudder and rudder trim system
It is system, aileron and aileron trimming system, automatic Pilot/flight director sys tem, landing-gear system, air data system, wireless
Electrical height table, pressable formula red major alarm lamp.
1) by acquisition sky/ground system it is hollow/data information of ground status signal and radio altimeter, can determine whether
The current water, land and air state of aircraft out；
2) by throttle lever thrust position information in acquisition engine control system, it can determine whether out whether throttle lever has been in
Fly in thrust range；
3) by the location status information of wing flap in acquisition trailing edge flap control system, it can determine whether out trailing edge flap whether not
In position of taking off, perhaps it is in skew or asymmetric state or has non-mandatory movement；
4) by acquire the location status information of droope snoot and slat in leading edge device, can determine whether out droope snoot with
Whether slat is not released, or has non-mandatory movement；
5) by the location status information of ground spoiler in acquisition flap system, whether can determine whether out ground spoiler
It is unrecovered；
6) it is taken off warning message by flap in acquisition flap system, can determine whether out whether flap handle puts down；
7) by the status information of parking brake in acquisition brake system, it can determine whether out whether parking brake does not unclamp；
8) by the position signal of trimmer in acquisition elevator and elevator trimming system, it can determine whether out that elevator is matched
Whether leveling device exceeds allowed band；
9) by the position signal of trimmer in acquisition rudder and rudder trimming system, it can determine whether out that rudder is matched
Whether leveling device exceeds allowed band；
10) status signal that electric switch is connected by automatic Pilot in acquisition automatic Pilot/flight director sys tem, can determine whether out
Whether automatic Pilot is switched on；
11) by the position signal of trimmer in acquisition aileron and aileron trimming system, it can determine whether out aileron with paperback
It whether sets beyond allowed band；
12) by the status signal of undercarriage in acquisition landing-gear system, it can determine whether out whether undercarriage is received completely
It goes up and locks；
13) by air speed value in acquisition air data system, it can determine whether out whether air speed is greater than V1；
14) whether by the inhibition signal of acquisition pressable formula red major alarm lamp, can determine whether out to take off to alert is suppressed；
15) pass through driving pressable formula red major alarm lamp, it is possible to provide the red light warning of undercarriage control position refers to
Show；
16) pass through driving audio devices, it is possible to provide the audible warning sound of undercarriage control position indicates；
The present invention for amphibious aircraft take off form the characteristics of, provide more complete takeoff configuration warning and solve
Approach can effectively warn flight unit amphibious aircraft to take off in the water surface, land two kinds of differences of taking off are taken off institute under mode
The abnormal takeoff configuration occurred improves the safety of aircraft timely to take corresponding workaround, has biggish
Practical value.
Detailed description of the invention
Fig. 1 be amphibious aircraft provided by the invention take off warning system one embodiment structural schematic diagram；Fig. 2
Be amphibious aircraft provided by the invention take off warning system another embodiment structural schematic diagram
In figure, 101-118 is aircraft system/equipment relevant to warning system of taking off, and A-R is to take off to alert required to sentence
According to.Wherein, 101 it is flight alarm computer, 102 be pressable formula red major alarm lamp, 103 be loudspeaker, 104 is big destiny
According to system, 105 be sky/ground system, 106 be radio altimeter, 107 be throttle lever control crank, 108 be flap manipulation hand
Handle, 109 be parking brake handle, 110 be landing-gear system, 111 be trailing edge flap, 112 be leading edge device, 113 be from
Dynamic driving/flight director sys tem, 114 be aileron and aileron trimming system, 115 be elevator and elevator trimming system, 116 be
Rudder and rudder trimming system, 117 be ground spoiler, 118 be remote data concentrator, A is light warning, B is alert
Accuse inhibition, C is audible warning sound, D is air speed information, E is aircraft wheel information carrying breath, F is radio altitude information, G is throttle lever position
Confidence breath, H flap control crank location information, I parking brake handle position information, J are undercarriage control status information, K
Trailing edge flap location information, L droope snoot location information, M are autopilot engagement status information, N is aileron trim condition
Information, O are elevator trim condition information, P is rudder trim condition information, Q is ground spoiler location information, R is comprehensive
Close warning message.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
The present invention provides one kind and takes off warning system, is able to solve amphibious aircraft by land or when water surface takes off is different
The problem of improper form alerts, effectively improves the safety of system.
It is the structural schematic diagram of one embodiment of warning system provided by the invention of taking off referring to Fig. 1.
The embodiment of the present invention provides one kind and takes off warning system, comprising: flight alarm computer 101, pressable formula are red
Major alarm lamp 102, loudspeaker 103, air data system 104, sky/ground system 105, radio altimeter 106, throttle lever operation
Handle 107, flap control crank 108, parking brake handle 109, landing-gear system 110, trailing edge flap 111, leading edge
Device 112, automatic Pilot/flight director sys tem 113, aileron and aileron trimming system 114, elevator and elevator trimming system
115, rudder and rudder trimming system 116, ground spoiler 117.It is specific as follows:
The electrical input interface end of flight alarm computer 101 connects pressable formula red major alarm lamp 102, atmosphere data
System 104, sky/ground system 105, throttle lever control crank 107, flap control crank 108, stop at radio altimeter 106
Brake lever 109, landing-gear system 110, trailing edge flap 111, leading edge device 112, automatic Pilot/flight director sys tem
113, aileron and aileron trimming system 114, elevator and elevator trimming system 115, rudder and rudder trimming system
116, ground spoiler 117, electrical output interface end connect pressable formula red major alarm lamp 102, loudspeaker 103.
Flight alarm computer 101 inhibits information according to the warning of pressable formula red major alarm lamp 102, determines the police that takes off
Whether accuse and be suppressed: after warning of taking off is triggered, flight unit can cancel warning tones and warning by pressing major alarm lamp
Lamp；When safe take-off position occurs not allowing again in form of taking off, retriggered is taken off warning (including warning tones and warning
Lamp).
Flight alarm computer 101 determines whether aircraft airspeed is greater than V1 according to the air speed data of air data system 104
(take off decision speed): because any speed can be aborted within the acceleration-stop distance established up to V1 takes off, institute
To allow that warning system of taking off is automatically closed when aircraft lift front-wheel departs.
Flight alarm computer 101 is according to sky/ground system 105 sky/ground status information and radio altimeter 106 height
Degree evidence determines the current water/land/sky form of aircraft: when " ground " effectively then indicates that aircraft is currently in sky/ground status information
It is land；When " sky " is effectively in sky/ground status information and less than 6 meters of radio altitude value (fixed according to aircraft altitude) then indicates aircraft
It is currently at the water surface；Then indicate that aircraft is currently located when " sky " is effectively in sky/ground status information and radio altitude value is not less than 6 meters
In aerial.
Flight alarm computer 101 determines throttle lever according to the throttle lever thrust position information of throttle lever control crank 107
Whether within the scope of takeoff thrust: when one or more throttle lever thrust positions " position of taking off " effectively then indicate that throttle lever is in
Within the scope of takeoff thrust, aircraft is currently at the starting heats stage.
Flight alarm computer 101 takes off warning message according to the flap of flap control crank 108, determines flap
Whether do not put down: when flap handle removes lower bayonet slot position, flap, which takes off, alerts electric switch work " warning position " and effectively then indicates
Flap handle is not put down.
Flight alarm computer 101 determines that parking brake is according to the parking brake status information of parking brake handle 109
No not unclamp: when pull-up parking brake handle, parking brake handle position electric switch work " parking brake " effectively then indicates to stop
Brake lever does not unclamp.
Flight alarm computer 101 rises and falls according to the undercarriage control location information in landing-gear system 110, determination
Whether frame is received upper completely and is locked: on the contrary when undercarriage stowage position signal effectively then indicates that undercarriage is received completely and locked
Then indicate that undercarriage is not received upper completely and locked.
Flight alarm computer 101 determines trailing edge flap according to the flap configuration status information in trailing edge flap system 111
Whether in the non-security position taken off: when the non-security takeoff setting information of trailing edge flap effectively then indicates that trailing edge flap is not allowing
The position of safe take-off, i.e. trailing edge flap, which are not in, takes off position or is in skew or asymmetric state, or has non-mandatory
Movement.
Flight alarm computer 101 is according to the droope snoot and flap position status information in leading edge device 112, before determining
Whether edge wing flap and slat are in the non-security position taken off: when the non-security takeoff setting information of leading edge device effectively then indicates leading edge
Device is not released in the position for not allowing safe take-off, i.e. droope snoot and slat, or has non-mandatory movement.
Flight alarm computer 101 connects the state of electric switch according to automatic Pilot in automatic Pilot/flight director sys tem 113
Information, determines whether automatic Pilot is switched on: effectively then indicating that automatic Pilot is switched on when connecting electric switch " on ".
Flight alarm computer 101 determines secondary according to the location information of trimmer in aileron and aileron trimming system 114
Whether wing balancing device exceeds allowed band: when trimmer position electric switch " neutral position " effectively then indicates at aileron trimmer
It is the safe take-off position for being in permission in neutral position, otherwise indicates that aileron trimmer exceeds allowed band.
Flight alarm computer 101 is determined according to the location information of 115 trimmer of elevator and elevator trimming system
Whether elevator balancing device exceeds allowed band: when trimmer position electric switch " neutral position " effectively then indicates elevator trim
It is the safe take-off position for being in permission that mechanism, which is in neutral position, otherwise indicates that agriculture aircraft elevator exceeds allowed band.
Flight alarm computer 101 is determined according to the location information of 116 trimmer of rudder and rudder trimming system
Whether rudder balancing device exceeds allowed band: when trimmer position electric switch " neutral position " effectively then indicates rudder trim
It is the safe take-off position for being in permission that mechanism, which is in neutral position, otherwise indicates that agriculture aircraft elevator exceeds allowed band.
Not whether flight alarm computer 101 determine ground spoiler according to the location status information of ground spoiler 117
It withdraws: indicating that ground spoiler is withdrawn when ground spoiler position electric switch " withdrawal " is effective, otherwise indicate ground spoiler not
It withdraws.
Flight alarm computer 101 inhibits information, atmosphere data system according to the warning of pressable formula red major alarm lamp 102
The air speed data of system 104, the sky/vacant lot status information of ground system 105, the altitude information of radio altimeter 106, throttle lever behaviour
The throttle lever thrust position information of vertical handle 107, the flap of flap control crank 108 take off warning message, parking brake
The parking brake status information of handle 109, the undercarriage control location information of landing-gear system 110, trailing edge flap 111
Location status information, the location status information of leading edge device 112, the on-state of automatic Pilot/flight director sys tem 113 letter
Breath, aileron and the location information of aileron trimming system 114, the location information of elevator and elevator trimming system 115, rudder
And the location status information of the location information of rudder trimming system 116, ground spoiler 117, it determines currently to take off and alerts shape
State, and then light warning instruction, audio-alert data-driven pressable formula red major alarm lamp 102, audio devices 103 are exported,
Lamplight pointing, audible warning sound are provided for flight unit.
1. land take off
When flight alarm computer 101 collects following information, then by electrical output interface send corresponding instruction/
Data trigger pressable formula red major alarm lamp 102 and loudspeaker 103 to provide light warning and audible warning sound.
● sky/ground system 105 sky/ground status information " ground " effectively, and
● the throttle lever thrust position information " position of taking off " of throttle lever control crank 107 effectively, and
● the air speed value of air data system 104 is less than V1, and
● the warning of pressable formula red major alarm lamp 102 inhibits information invalid.And
● there are any following forms: the non-security takeoff setting information of the wing flap of trailing edge flap system 111 is effective or leading edge
The non-security takeoff setting information of the leading edge device of device 112 is effective or the ground spoiler location information of ground spoiler 117
" withdrawal " in vain or the caution position information of taking off of flap control crank 108 " warning position " effectively or parking brake handle
109 parking brake location information " parking brake " is effectively or the trim position information of elevator and elevator trimming system 115
" neutral position " effectively or the trim position information " neutral position " of rudder and rudder trimming system 116 effectively or aileron and pair
The trim position information " neutral position " of wing trimming system 114 is effectively or the connection information of automatic Pilot/flight director sys tem 113
" on " is effective.
2. the water surface takes off
When flight alarm computer 101 collects following information, then by electrical output interface send corresponding instruction/
Data trigger pressable formula red major alarm lamp 102 and loudspeaker 103 to provide light warning and audible warning sound.
● sky/ground system 105 sky/ground status information " sky " effectively, and
● the height value of radio altimeter 106 less than 6 meters, and
● the throttle lever thrust position information " position of taking off " of throttle lever control crank 107 effectively, and
● the air speed value of air data system 104 is less than V1, and
● the warning of pressable formula red major alarm lamp 102 inhibits information invalid.And
● there are any following forms: the non-security takeoff setting information of the wing flap of trailing edge flap system 111 is effective or leading edge
The non-security takeoff setting information of the leading edge device of device 112 is effective or the ground spoiler location information of ground spoiler 117
" withdrawal " in vain or the caution position information of taking off of flap control crank 108 " warning position " effectively or elevator and elevator
The trim position information " neutral position " of trimming system 115 effectively or rudder and the trim position of rudder trimming system 116 letter
Cease " neutral position " effectively or the trim position information " neutral position " of aileron and aileron trimming system 114 effectively or automatic Pilot/
The connection information " on " of flight director sys tem 113 is effective or the undercarriage stowage position signal of landing-gear system 110 without
Effect.
Amphibious aircraft provided in an embodiment of the present invention takes off warning system, has the advantages that and accuses in flight
Connecting sky/ground system, engine control system, trailing edge flap system, leading edge device/at the electrical input interface of alert computer is
System (droope snoot and slat), flap system, brake system, elevator and elevator trimming system, rudder and rudder
It is trimming system, aileron trimming system, automatic Pilot/flight director sys tem, landing-gear system, air data system, wireless
Electrical height table, pressable formula red major alarm lamp, and pressable formula red major alarm lamp, sound are connected at its electrical output interface
Frequency device.
1) by acquisition sky/ground system it is hollow/data information of ground status signal and radio altimeter, can determine whether
The current water, land and air state of aircraft out；
2) by throttle lever thrust position information in acquisition engine control system, it can determine whether out whether throttle lever has been in
Fly in thrust range；
3) by the location status information of wing flap in acquisition trailing edge flap control system, it can determine whether out trailing edge flap whether not
In position of taking off, perhaps it is in skew or asymmetric state or has non-mandatory movement；
4) by acquire the location status information of droope snoot and slat in leading edge device, can determine whether out droope snoot with
Whether slat is not released, or has non-mandatory movement；
5) by the location status information of ground spoiler in acquisition flap system, whether can determine whether out ground spoiler
It is unrecovered；
6) it is taken off warning message by flap in acquisition flap system, can determine whether out whether flap handle puts down；
7) by the status information of parking brake in acquisition brake system, it can determine whether out whether parking brake does not unclamp；
8) by the position signal of trimmer in acquisition elevator and elevator trimming system, it can determine whether out that elevator is matched
Whether leveling device exceeds allowed band；
9) by the position signal of trimmer in acquisition rudder and rudder trimming system, it can determine whether out that rudder is matched
Whether leveling device exceeds allowed band；
10) status signal that electric switch is connected by automatic Pilot in acquisition automatic Pilot/flight director sys tem, can determine whether out
Whether automatic Pilot is switched on；
11) by the position signal of trimmer in acquisition aileron and aileron trimming system, it can determine whether out aileron with paperback
It whether sets beyond allowed band；
12) by the status signal of undercarriage in acquisition landing-gear system, it can determine whether out whether undercarriage is received completely
It goes up and locks；
13) by air speed value in acquisition air data system, it can determine whether out whether air speed is greater than V1；
14) whether by the inhibition signal of acquisition pressable formula red major alarm lamp, can determine whether out to take off to alert is suppressed；
15) pass through driving pressable formula red major alarm lamp, it is possible to provide the red light warning of undercarriage control position refers to
Show；
16) pass through driving audio devices, it is possible to provide the audible warning sound of undercarriage control position indicates.
It referring to fig. 2, is that the take off structure of another embodiment of warning system of amphibious aircraft provided by the invention is shown
It is intended to.It may also include remote data concentrator 118 (can configure multiple), the remote data concentration in the warning system of taking off
Device 118 is disposed adjacent at aircraft sensors source by nearby principle, and it is comprehensive to carry out analog-to-digital conversion etc. to various kinds of sensors data
Processing；The electrical input interface of the remote data concentrator and the air data system 104, the sky/ground system 105,
The radio altimeter 106, the throttle lever control crank 107, the flap control crank 108, the parking brake
Handle 109, the trailing edge flap system 111, the leading edge device 112, described is driven the landing-gear system 110 automatically
Sail/flight director sys tem 113, the aileron and aileron trimming system 114, the elevator and elevator trimming system 115, institute
Rudder and rudder trimming system 116, the ground spoiler 117 crosslinking are stated, relevant state parameter or operation number are acquired
According to collected parameter or data pass through the electricity of the remote data concentrator after the integrated treatments such as relevant analog-to-digital conversion
Gas output interface is sent to the flight alarm computer 101.By the introducing of the embodiment medium-long range data concentrator 118,
Acquisition, integrated treatment and the concentration of transmissions that can further realize different grades of electromechanical subsystem signals, to improve electromechanics
Sharing for system/device information, reduces the quantity of full machine conducting wire, the complexity of aircraft wiring is reduced, to enhance entire aircraft
The safety of system and maintainability.
The present invention is directed to the characteristics of amphibious aircraft takeoff configuration, provides more complete configuration warning and solves way
Diameter can effectively warn flight unit amphibious aircraft to take off in the water surface, be gone out under land two kinds of different takeoff conditions of taking off
Existing abnormal form of taking off improves the safety of aircraft timely to take corresponding workaround, has biggish reality
With value.
The above is a preferred embodiment of the present invention, it is noted that for those skilled in the art
For, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also considered as
Protection scope of the present invention.
Claims (4)
- The warning system 1. one kind is taken off characterized by comprising flight alarm computer, sky/ground system, power management system System, trailing edge flap system, leading edge device/system, flap system, brake system, elevator and elevator trimming system, direction Rudder and rudder trimming system, aileron trimming system, automatic Pilot/flight director sys tem, landing-gear system, atmosphere data System, radio altimeter, pressable formula red major alarm lamp, audio devices；The electrical input interface end of the flight alarm computer connects sky/ground system, engine control system, trailing edge flap system System, leading edge device/system, flap system, brake system, elevator and elevator trimming system, rudder and rudder are matched Flat system, aileron and aileron trimming system, automatic Pilot/flight director sys tem, landing-gear system, air data system, Radio altimeter, pressable formula red major alarm lamp；The electrical output interface end of the flight alarm computer connects pressable formula red major alarm lamp, audio devices；Flight alarm computer according to take off alert logic judgment process it is collected to input interface place, from The relevant information of lower system/device carries out integrated treatment: the sky/ground system, the engine control system, the rear flap Wing system, the leading edge device, the flap system, the brake system, the elevator and elevator trimming system, institute State rudder and rudder trimming system, the aileron and aileron trimming system, the automatic Pilot/flight director sys tem, institute Landing-gear system, the air data system, the radio altimeter, the pressable formula red major alarm lamp are stated, And corresponding light warning instruction, audio-alert information to the output interface driving pressable formula red are sent according to processing result Major alarm lamp, the audio devices provide dual alert mode visual, acoustically for flight unit.
- 2. warning system of taking off as described in claim 1, which is characterized in that the warning system of taking off may also include long-range number According to concentrator；The remote data concentrator is disposed adjacent at aircraft sensors source by nearby principle, to various kinds of sensors Data carry out analog-to-digital conversion integrated treatment；It is the electrical input interface of the remote data concentrator and the sky/ground system, described It is engine control system, the trailing edge flap system, the leading edge device, the flap system, the brake system, described It is elevator and elevator trimming system, the rudder and rudder trimming system, the aileron and aileron trimming system, described Automatic Pilot/flight director sys tem, the landing-gear system, the air data system, the radio altimeter are handed over Connection, acquires relevant state parameter or operation data, and collected parameter or data pass through relevant analog-to-digital conversion integrated treatment The electrical output interface for passing through the remote data concentrator afterwards is sent to the flight alarm computer.
- 3. warning system of taking off as described in claim 1, which is characterized in that the flight alarm COMPUTER DETECTION arrives: when winged Machine is in ground, and one or more throttle levers are in take-off range, and air speed is less than the decision speed V1 that takes off, and alerts and inhibit When button is not pressed, any one condition, which does not meet, below can trigger warning system work of taking off；A) trailing edge flap is not on position of taking off, and is perhaps in skew or asymmetric state or has non-mandatory movement；B) droope snoot and slat are not released, or have non-mandatory movement；C) ground spoiler is unrecovered；D) flap handle is not put down；E) parking brake does not unclamp；F) elevator balancing device exceeds allowed band；G) rudder balancing device exceeds allowed band；H) aileron balancing device exceeds allowed band；I) autopilot engagement.
- 4. warning system of taking off as described in claim 1, which is characterized in that the flight alarm COMPUTER DETECTION arrives: when winged Machine is in the water surface, and one or more throttle levers are in take-off range, and air speed is less than the decision speed V1 that takes off, and alerts and inhibit When button is not pressed, any one condition, which does not meet, below can trigger warning system work of taking off；A) trailing edge flap is not on position of taking off, and is perhaps in skew or asymmetric state or has non-mandatory movement；B) droope snoot and slat are not released, or have non-mandatory movement；C) ground spoiler is unrecovered；D) flap handle is not put down；E) elevator balancing device exceeds allowed band；F) rudder balancing device exceeds allowed band；G) aileron balancing device exceeds allowed band；H) autopilot engagement；I) any undercarriage is not received and is locked.
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| CN201410725362.7A CN105644800B (en) | 2014-12-03 | 2014-12-03 | One kind is taken off warning system |
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| CN201410725362.7A CN105644800B (en) | 2014-12-03 | 2014-12-03 | One kind is taken off warning system |
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| CN105644800B true CN105644800B (en) | 2019-08-13 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106628207B (en) * | 2016-11-25 | 2022-05-24 | 上海航空电器有限公司 | Alarm suppression method for ground proximity alarm system |
| US10281913B2 (en) * | 2017-08-14 | 2019-05-07 | The Boeing Company | Methods and systems for intelligent predictive aircraft takeoff rejection decision making |
| CN109144079B (en) * | 2018-08-22 | 2021-04-23 | 中国民航大学 | Amphibious aircraft landing configuration control system based on integrated avionics |
| CN109720589B (en) * | 2018-11-12 | 2023-05-23 | 中航通飞华南飞机工业有限公司 | Indication and alarm system of rudder control system of large amphibious aircraft |
| 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 |
| RU2729905C1 (en) * | 2019-08-26 | 2020-08-13 | Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации | Control method of an unmanned aerial vehicle |
| 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 |
| CN111532438B (en) * | 2020-05-09 | 2023-03-31 | 中国航空无线电电子研究所 | Double-side rod overlapping protection control and alarm system |
| CN112455662B (en) * | 2020-09-18 | 2024-02-02 | 中电科芜湖通用航空产业技术研究院有限公司 | Aircraft landing gear warning initiation and elimination circuit and method |
| CN112380623A (en) * | 2020-11-17 | 2021-02-19 | 中航通飞华南飞机工业有限公司 | Method for evaluating airworthiness conformity of flight quality of amphibious aircraft |
| CN113978757B (en) * | 2021-10-25 | 2023-11-21 | 哈尔滨哈飞航空工业有限责任公司 | Device and method for judging operation stage of airplane |
| CN113975697A (en) * | 2021-10-25 | 2022-01-28 | 中航通飞华南飞机工业有限公司 | Fire-fighting aircraft water-drawing takeoff alarming method |
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Effective date of registration: 20201202 Address after: 519000 Building 201, No. 999 Jinhai Middle Road, Jinwan District, Zhuhai City, Guangdong Province Patentee after: SOUTH CHINA AIRCRAFT INDUSTRY CO., LTD. OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. Address before: 218 floor 2, building 2, 3 Xiasha street, Wan Chai, Xiangzhou District, Zhuhai, Guangdong, 519040 Patentee before: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. |