CN105644800A - Take-off warning system - Google Patents
Take-off warning system Download PDFInfo
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- CN105644800A CN105644800A CN201410725362.7A CN201410725362A CN105644800A CN 105644800 A CN105644800 A CN 105644800A CN 201410725362 A CN201410725362 A CN 201410725362A CN 105644800 A CN105644800 A CN 105644800A
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Abstract
The invention discloses a take-off warning system which comprises a flight warning computer, a red main warning lamp, an audio device, an engine operation system, a flight operation system, an undercarriage system, an avionics system and the like. The electrical input end of the flight warning computer is connected with all subsystems except for the red main warning lamp and the audio device in the take-off warning system. The electrical output end of the flight warning computer is connected with the red main warning lamp and the audio device. The flight warning computer comprehensively processes related information acquired through the input end according to a take-off warning logical judgment procedure and sends corresponding command information to the electrical output end to drive the main warning lamp and the audio device according to a processing result, and a sound warning and a lamplight warning are provided for a flight crew. By the adoption of the embodiment of the take-off warning system, the problem that a water surface take-off state warning is not available in takeoff warnings required by an airworthiness regulation can be solved, it is guaranteed that the take-off configuration warnings of an amphibious aircraft are completed, and the safety of an amphibious aircraft system is improved.
Description
Technical field
The invention belongs to aircraft system circuit design field, particularly relate to one and take off warning system.
Background technology
In the seaworthiness regulations the 703rd article " warning system of taking off " that Civil Aviation Administration of China promulgates, the warning system of taking off of class of travelling frequently, transport class aircraft is proposed corresponding design requirements by (CCAR-23-R3 " the 703rd article " and CCAR-25-R4 " the 703rd article "):
1. about the warning form of warning of taking off. The warning form of requirement system comprises wing flap or leading edge lifting unit does not take off within the scope of position what aiMonhiness authority ratified, and the safe take-off position that wing interceptor, flap or longitudinal balancing device are not allowing.
2. about the continuity of warning of taking off. The warning time of requirement system must be extended to: the morphologic change of aircraft is the form allowing safe take-off; Officer takes and stops the sliding action run of taking off; Aircraft reaches the speed lifting front-wheel, liftoff takes off; Officer artificially cuts off warning, and is not that requirement warning to be continued up to till aircraft stops completely.
3. about the reliability of warning of taking off. Requirement system must at the whole weight range of aircraft type examination and approval, use in height and temperature range and ensure normal operation, do not allow to occur that aircraft meets warning form, but system does not carry out the phenomenon reported to the police.
But with the amphibious aircraft of retractable landing gear, there are two kinds of different forms of taking off: land take off, the water surface take off, different forms of taking off is to there being different safe take-off positions:
1. when amphibious aircraft is selected to take off by land, the form of safe take-off is not allowed to comprise wing flap or leading edge lifting unit does not take off within the scope of position what aiMonhiness authority ratified, and the safe take-off position that wing interceptor, flap or longitudinal balancing device are not allowing, and the device such as yaw rudder trim mechanism and aileron trim mechanism is in the safe take-off position not allowed, airplane wheel brake does not discharge, and robot pilot all should within warning scope in forms such as on positions.
2., when amphibious aircraft is selected to take off at the water surface, do not allow the form of safe take-off not only to comprise the 1. described form (airplane wheel brake do not discharge except) not allowing safe take-off and outward, also comprise landing gear and do not receive completely and go up and pin.
In amphibious aircraft water surface take-off process, if landing gear occur abnormal take off form time (fault or be in mistake position), the flight of aircraft will be formed safely serious threat, because landing gear is not received completely and is gone up and pin when the water surface takes off, the acceleration distance that takes off can be caused to increase, once there is the situation interrupting taking off, the water surface gone out possibly by aircraft, causes serious accident. If only design the warning system of taking off of amphibious aircraft by the requirement of existing seaworthiness regulations, namely only consider that flight safety is produced bigger impact by wing flap, leading edge lifting unit, interceptor, flap and longitudinal balancing device etc., will certainly produce part when the water surface takes off does not allow the situation of safe take-off form warning disappearance to occur, the change of aerodynamic configuration when this will cause the aircraft water surface to take off, and then cause hardly imaginable disaster.
Summary of the invention
The present invention proposes one and takes off warning system, the disappearance that the water surface existed takes off and do not allow safe take-off position to warn in form can be solved in the warning system of taking off required by relevant seaworthiness regulations (only land take off form warning) mode, guarantee that amphibious aircraft is taken off the complete of warning system function: comprise and land take off form warning and the water surface takes off form warning, to improve the security of amphibious aircraft system.
The embodiment of the present invention provides a kind of and amphibious takes off warning system, comprising: flight alarm computer, sky/ground system, engine maneuvering system, trailing edge wing flap system, leading edge device (leading edge wing flap and slat), flap system, brake system, elevating rudder and elevating rudder trim system, yaw rudder and yaw rudder trim system, aileron and aileron trim system, automatic Pilot/flight guidance system, landing gear extension and retraction system, atmosphere data system, radio altimeter, can push type redness main warning light, audio devices.
Described flight alarm computer is the core component of the embodiment of the present invention, by corresponding electrically input interface and described sky/ground system, described engine maneuvering system, described trailing edge wing flap system, described leading edge device, described flap system, described brake system, described elevating rudder and elevating rudder trim system, described yaw rudder and yaw rudder trim system, described aileron and aileron trim system, described automatic Pilot/flight guidance system, described landing gear extension and retraction system, described atmosphere data system, described radio altimeter, described can the red main warning light (warning inhibit feature) of push type be cross-linked, gather relevant state parameter or service data, and according to the form warning Logic judgment flow process of taking off of computer-internal, the Various types of data gathered is carried out comprehensive treating process, and send the warning instruction of corresponding light according to result, audio-alert information can the red main warning light (light alarm function) of push type to exporting described in interface driver, described audio devices, for flight unit provides visually, dual alert mode in the sense of hearing.
Described sky/ground system provides status signal that is aerial or ground to aircraft. Each landing gear there is compression sensor be used for monitoring the compression of landing gear shock strut: when landing gear shock strut compresses, target is close to sensor, when aircraft landing gear shock strut when ground is compressed, compression sensor is triggered and sends signal to the signal processor unit closed on, sky/ground discrete signal is passed to described flight alarm computer again, the comprehensive treating processs such as the Logic judgment of the form warning that is used for carrying out taking off after process.
Described radio altimeter is by its transceiver, reception radiowave, measure the time that radiowave returns aircraft from aircraft to ground again and experiences from ground, the actual height on plane distance ground is obtained after resolving, the comprehensive treating processs such as the height value after resolving sends described flight alarm computer with digital data format to through data bus, the Logic judgment of the form warning that is used for carrying out taking off.
Described engine maneuvering system sends thrust position signal by throttle lever maneuvering lever to engine control parts, and after resolving, thrust position signal is converted to throttle commands signal, for engine provides gasoline throttle angle information, is used for controlling the size of engine throttle. Throttle lever maneuvering lever place has corresponding position transducer to be used for monitoring the motion of throttle lever: when currently pushing away throttle lever maneuvering lever, target is close to sensor, throttle lever maneuvering lever is pushed away before aircraft is when taking off sliding race, throttle lever position sensor is triggered and sends signal to the signal processor unit closed on, described flight alarm computer is given by thrust position signal transmission again, the comprehensive treating processs such as the Logic judgment of the form warning that is used for carrying out taking off after process.
Described trailing edge wing flap system by wing flap maneuvering lever normal mode of operation or wing flap electric switch operating method for subsequent use for trailing edge wing flap provides the folding and unfolding of instruction signal-be used for controlling trailing edge wing flap, wing flap control unit control trailing edge wing flap completes folding and unfolding according to command request, and provides the information such as state that data information-be used for feeds back wing flap Controlling System for described flight alarm computer. Maneuvering lever place arranges multiple manipulation shelves position, and the corresponding corresponding location of instruction sensor in each grade of position place, is converted to electric signal transmission to wing flap control unit by the mechanical order of flight unit, is used for controlling the folding and unfolding of trailing edge wing flap; Trailing edge wing flap folding and unfolding position is provided with position transducer, positional information current for trailing edge wing flap is fed back to wing flap function unit, described flight alarm computer is passed to, the comprehensive treating processs such as the Logic judgment of the form warning that is used for carrying out taking off by wing flap function unit.
Described leading edge device/system obtains the motion of the instruction signal of leading edge wing flap and slat-be used for controlling leading edge device by trailing edge wing flap system (during normal running) or wing flap electric switch for subsequent use (during operation for subsequent use), wing flap control unit control leading edge device completes folding and unfolding according to command request, leading edge device folding and unfolding position is provided with position transducer, positional information current for leading edge device is fed back to wing flap function unit, pass to described flight alarm computer again, the comprehensive treating processs such as the Logic judgment of the form warning that is used for carrying out taking off.
Described flap system handles ground interceptor automatically by flap handle manual maneuvering or automatic flap assembly. Only when aircraft is on ground, when opening flap handle, ground interceptor is just opened. Flap handle place is provided with the motion of position electric switch monitoring flap handle: when flap handle moves into lower bayonet slot position, target approximated position electric switch, when aircraft is released at ground flap, the flap caution position electric switch that takes off is triggered and sends signal to the signal processor unit that closes on; Interceptor internal lock valve place, ground is provided with the motion of position transducer monitoring ground interceptor: when aircraft interceptor internal lock valve in ground when ground only controls ground interceptor work, when ground interceptor is regained, position transducer is triggered and sends signal to the signal processor unit closed on, flap is taken off warning signal, ground interceptor retracted state signal transmission again to described flight alarm computer after process, the comprehensive treating processs such as the Logic judgment of the form warning that is used for carrying out taking off.
Described brake system is started by parking brake handle and brake pedal or is unclamped parking brake, there is the action of parking brake position electric switch monitoring handle at parking brake handle place: when pull-up parking brake handle, target approximated position electric switch, parking brake position electric switch is triggered and sends signal to the signal processor unit closed on, parking brake status information is passed to described flight alarm computer again, the comprehensive treating processs such as the Logic judgment of the form warning that is used for carrying out taking off.
Described elevating rudder and elevating rudder trim system carry out trim in the desired direction by elevating rudder trimming control electric switch instruction trim mechanism, the trim position of position sensor monitoring trim mechanism of place of trim mechanism, the comprehensive treating processs such as the signal processor unit through closing on passes to described flight alarm computer, the Logic judgment of the form warning that is used for carrying out taking off.
Described yaw rudder and yaw rudder trim system direction of passage rudder trimming control knob instruction trim mechanism carry out trim in the desired direction, the trim position of position sensor monitoring trim mechanism of place of trim mechanism, the comprehensive treating processs such as the signal processor unit through closing on passes to described flight alarm computer, the Logic judgment of the form warning that is used for carrying out taking off.
Described aileron trim system aileron trim electric switch instruction trim mechanism carries out trim in the desired direction, the trim position of position sensor monitoring trim mechanism of place of trim mechanism, the comprehensive treating processs such as the signal processor unit through closing on passes to described flight alarm computer, the Logic judgment of the form warning that is used for carrying out taking off.
Described automatic Pilot/flight guidance system connects, by automatic Pilot, the connection that electric switch realizes automatic Pilot, the comprehensive treating processs such as the signal processor unit of status signal through closing on connecting electric switch passes to described flight alarm computer, the Logic judgment of the form warning that is used for carrying out taking off.
Described landing gear extension and retraction system for landing gear provides instruction signal-be used for control the folding and unfolding of landing gear by landing gear pilot lever, is controlled landing gear by landing gear function unit and completes folding and unfolding according to command request and provide the information such as state of data information-be used for feeding back landing gear extension and retraction system for described flight alarm computer. Pilot lever place arranges multiple grades of positions, and the mechanical order of flight unit, to there being corresponding location of instruction sensor, is converted to electric signal transmission to landing gear function unit by each grade of position place, is used for controlling the folding and unfolding of landing gear; Landing gear folding and unfolding position arranges multiple position transducer, by current for landing gear extension and retraction system status information (landing gear put down completely and lock, landing gear receives and the information such as locking completely) feed back to landing gear function unit, send described flight alarm computer to by landing gear function unit, it is used for carrying out the comprehensive treating process such as Logic judgment of landing gear jack position warning.
Static pressure that described atmosphere data system provides according to static pressure transducer, total head sensor, angle-of-attack detector, total temperature probe, total head, the angle of attack, total temperature 4 initial parameters, resolve and export a large amount of atmosphere data parameters, the comprehensive treating processs such as the air speed value after resolving sends described flight alarm computer with digital data format to through data bus, the Logic judgment of the form warning that is used for carrying out taking off.
Described can the red main warning light of push type be the red light warning of flight unit offer according to the light instruction signal that described flight alarm computer sends; This warning light has pressing reset function simultaneously, namely can realize the warning of corresponding light and the inhibit feature of sound equipment warning by pressing this warning light.
The audio frequency data information that described audio devices sends by receiving described flight alarm computer is flight unit offer continuous print sound equipment warning.
Further, described amphibious warning system of taking off also can comprise long range data concentrator (configurable multiple), described long range data concentrator is arranged near aircraft sensor source place by nearby principle, and various kinds of sensors data carry out the comprehensive treating processs such as analog to digital conversion;The electric input interface of described long range data concentrator and described sky/ground system, described engine maneuvering system, described trailing edge wing flap system, described leading edge device, described flap system, described brake system, described elevating rudder and elevating rudder trim system, described yaw rudder and yaw rudder trim system, described aileron and aileron trim system, described automatic Pilot/flight guidance system, described landing gear extension and retraction system, described atmosphere data system, described radio altimeter is cross-linked, gather relevant state parameter or service data, the parameter collected or data after the comprehensive treating processs such as relevant analog to digital conversion by the electric output interface of described long range data concentrator, it is sent to described flight alarm computer.
What the embodiment of the present invention provided amphibious takes off warning system, has following useful effect: connect at the electric input interface place of flight alarm computer sky/ground system, engine maneuvering system, trailing edge wing flap system, leading edge device (leading edge wing flap and slat), flap system, brake system, elevating rudder and elevating rudder trim system, yaw rudder and yaw rudder trim system, aileron and aileron trim system, automatic Pilot/flight guidance system, landing gear extension and retraction system, atmosphere data system, radio altimeter, can the push type main warning light of redness.
1) by gathering sky/ground system hollow/ground status signal, and the data information of radio altimeter, the water, land and air state that aircraft is current can be judged;
2) by gathering throttle lever thrust position information in engine maneuvering system, can judge whether throttle lever is in and take off within the scope of thrust;
3) by gathering the position status information of wing flap in trailing edge wing flap Controlling System, can judge whether trailing edge wing flap is not in position of taking off, or be in crooked or asymmetric state, or have non-mandatory motion;
4) by having gathered the position status information of leading edge wing flap and slat in leading edge device, can judge whether leading edge wing flap and slat are not released, or have non-mandatory motion;
5) by gathering the position status information of ground interceptor in flap system, can judge that whether ground interceptor is unrecovered;
6) take off warning message by gathering flap in flap system, can judge whether flap handle puts down;
7) by gathering the status information of parking brake in brake system, can judge whether parking brake does not unclamp;
8) by gathering the position signal of trim mechanism in elevating rudder and elevating rudder trim system, can judge whether elevating rudder balancing device exceeds allowed band;
9) by gathering the position signal of trim mechanism in yaw rudder and yaw rudder trim system, can judge whether yaw rudder balancing device exceeds allowed band;
10) connect the status signal of electric switch by gathering automatic Pilot in automatic Pilot/flight guidance system, can judge whether automatic Pilot is switched on;
11) by gathering the position signal of trim mechanism in aileron and aileron trim system, can judge whether aileron balancing device exceeds allowed band;
12) by gathering the status signal of landing gear in landing gear extension and retraction system, can judge whether landing gear is received completely and go up and lock;
13) by gathering air speed value in atmosphere data system, can judge whether air speed is greater than V1;
14) by gather can the suppression signal of the red main warning light of push type, whether warning of can judging to take off is suppressed;
15) by driving can the red main warning light of push type, the red light warning instruction of landing gear its stored position can be provided;
16) by driving audio devices, the sound equipment warning instruction of landing gear its stored position can be provided;
The present invention is directed to the amphibious feature taking off form, provide more complete takeoff configuration warning solution route, can effectively warn the abnormal takeoff configuration that the flight amphibious aircraft of unit takes off, land two kinds of differences of taking off are taken off and occurred under mode at the water surface, to take timely corresponding to evade measure, improve the security of aircraft, there is bigger practical value.
Accompanying drawing explanation
Fig. 1 is the structural representation of the amphibious embodiment taking off warning system provided by the invention; Fig. 2 is the structural representation of amphibious another embodiment taking off warning system provided by the invention
In figure, 101-118 is the aircraft system/device relevant to warning system of taking off, and A-R is the criterion taken off needed for warning. wherein, 101 is flight alarm computer, 102 is can the red main warning light of push type, 103 is loud speaker, 104 is atmosphere data system, 105 is sky/ground system, 106 is radio altimeter, 107 is throttle lever maneuvering lever, 108 is flap maneuvering lever, 109 is parking brake handle, 110 is landing gear extension and retraction system, 111 is trailing edge wing flap, 112 is leading edge device, 113 is automatic Pilot/flight guidance system, 114 is aileron and aileron trim system, 115 is elevating rudder and elevating rudder trim system, 116 is yaw rudder and yaw rudder trim system, 117 is ground interceptor, 118 is long range data concentrator, and A is light warning, B is warning suppression, C is sound equipment warning, D is air speed information, E is aircraft wheel information carrying breath, F is wireless elevation information, G is throttle lever positional information, H flap maneuvering lever positional information, I parking brake handle position information, J is landing gear folding and unfolding status information, K trailing edge wing flap positional information, L leading edge wing flap positional information, M is that status information connected by robot pilot, N is aileron trim condition information, O is elevating rudder trim condition information, P is yaw rudder trim condition information, Q is ground interceptor positional information, R 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 clearly and completely described, it is clear that described embodiment is only the present invention's part embodiment, instead of whole embodiments. Based on the embodiment in the present invention, those of ordinary skill in the art, not making other embodiments all obtained under creative work prerequisite, belong to the scope of protection of the invention.
The present invention provides one to take off warning system, it is possible to solves amphibious aircraft by land or the problem of different improper form warning when the water surface takes off, effectively improves the security of system.
See Fig. 1, it it is the structural representation of an embodiment of warning system of taking off provided by the invention.
The embodiment of the present invention provides one to take off warning system, comprise: flight alarm computer 101, can the red main warning light 102 of push type, loud speaker 103, atmosphere data system 104, sky/ground system 105, radio altimeter 106, throttle lever maneuvering lever 107, flap maneuvering lever 108, parking brake handle 109, landing gear extension and retraction system 110, trailing edge wing flap 111, leading edge device 112, automatic Pilot/flight guidance system 113, aileron and aileron trim system 114, elevating rudder and elevating rudder trim system 115, yaw rudder and yaw rudder trim system 116, ground interceptor 117.Specific as follows:
The electric input interface end of flight alarm computer 101 connects can the red main warning light 102 of push type, atmosphere data system 104, sky/ground system 105, radio altimeter 106, throttle lever maneuvering lever 107, flap maneuvering lever 108, parking brake handle 109, landing gear extension and retraction system 110, trailing edge wing flap 111, leading edge device 112, automatic Pilot/flight guidance system 113, aileron and aileron trim system 114, elevating rudder and elevating rudder trim system 115, yaw rudder and yaw rudder trim system 116, ground interceptor 117, electrically exporting that interface end connects can the red main warning light 102 of push type, loud speaker 103.
Flight alarm computer 101 is according to the warning of the red main warning light 102 of push type suppressing information, it is determined that whether warning of taking off is suppressed: after warning of taking off is triggered, and flight unit, by pressing main warning light, cancels warning sound and warning light; When form of taking off occurs not allowing safe take-off position again, will again trigger warning of taking off (comprising warning sound and warning light).
Flight alarm computer 101 is according to the air speed data of atmosphere data system 104, determine whether aircraft airspeed is greater than V1 (resolution of taking off speed): because any speed until V1 take off can be terminated in the acceleration set up-stoppings apart within, so when aircraft lift front-wheel depart time, allow automatically to close warning system of taking off.
Flight alarm computer 101 is according to the high degrees of data of the sky/ground status information of sky/ground system 105 and radio altimeter 106, it is determined that water/land/sky form that aircraft is current: when in sky/ground status information " " effectively then expression aircraft be currently in land; When " sky " in sky/ground status information effectively and wireless height value be less than 6 meters (fixed according to aircraft altitude) and then represent that aircraft is currently in the water surface; When " sky " in sky/ground status information effectively and wireless height value be not less than 6 meters and then represent that aircraft is currently in the air.
Flight alarm computer 101 is according to the throttle lever thrust position information of throttle lever maneuvering lever 107, determining whether throttle lever is in takes off within the scope of thrust: taking off within the scope of thrust when one or more throttle lever thrust position " position of taking off " effectively then represents that throttle lever is in, aircraft is currently in the sliding race stage of taking off.
Flight alarm computer 101 takes off warning message according to the flap of flap maneuvering lever 108, it is determined that whether flap does not put down: when flap handle moves out of lower bayonet slot position, flap warning electric switch work " warning position " of taking off effectively then represents that flap handle does not put down.
Flight alarm computer 101 is according to the parking brake status information of parking brake handle 109, it is determined that whether parking brake does not unclamp: when pull-up parking brake handle, parking brake handle position electric switch work " parking brake " effectively then represents that parking brake handle does not unclamp.
Flight alarm computer 101 is according to the landing gear its stored position information in landing gear extension and retraction system 110, determine that whether landing gear is received completely go up and lock: go up when landing gear retracted position signal effectively then represents that landing gear is received completely and lock, on the contrary then expression landing gear completely receipts go up and lock.
Flight alarm computer 101 is according to the wing flap position status information in trailing edge wing flap system 111, determine that whether trailing edge wing flap is in the non-security position taken off: positional information of taking off effectively then represents that trailing edge wing flap is in the position not allowing safe take-off when trailing edge wing flap is non-security, namely trailing edge wing flap is not in and takes off position or be in crooked or asymmetric state, or has non-mandatory motion.
Flight alarm computer 101 is according to the leading edge wing flap in leading edge device 112 and slat position status information, determine that whether leading edge wing flap and slat are in the non-security position taken off: positional information of taking off effectively then represents that leading edge device is in the position not allowing safe take-off when leading edge device is non-security, namely leading edge wing flap and slat are not released, or have non-mandatory motion.
The status information of electric switch connected by flight alarm computer 101 according to automatic Pilot in automatic Pilot/flight guidance system 113, it is determined that whether automatic Pilot is switched on: when connection electric switch " connection " effectively then represents that automatic Pilot is switched on.
Flight alarm computer 101 is according to the positional information of trim mechanism in aileron and aileron trim system 114, determine whether aileron balancing device exceeds allowed band: when trim mechanism position electric switch " neutral position " effectively then represents that aileron trim mechanism is in the safe take-off position that namely neutral position is in permission, otherwise represent that aileron trim mechanism exceeds allowed band.
Flight alarm computer 101 is according to the positional information of elevating rudder and elevating rudder trim system 115 trim mechanism, determine whether elevating rudder balancing device exceeds allowed band: when trim mechanism position electric switch " neutral position " effectively then represents that agriculture aircraft elevator is in the safe take-off position that namely neutral position is in permission, otherwise represent that agriculture aircraft elevator exceeds allowed band.
Flight alarm computer 101 is according to the positional information of yaw rudder and yaw rudder trim system 116 trim mechanism, determine whether yaw rudder balancing device exceeds allowed band: when trim mechanism position electric switch " neutral position " effectively then represents that yaw rudder trim mechanism is in the safe take-off position that namely neutral position is in permission, otherwise represent that agriculture aircraft elevator exceeds allowed band.
Flight alarm computer 101 is according to the position status information of ground interceptor 117, it is determined that whether ground interceptor is unrecovered: represent that ground interceptor is regained when interceptor position, ground electric switch " withdrawal " is effective, otherwise represents that ground interceptor is unrecovered.
Flight alarm computer 101 is according to the warning of the red main warning light 102 of push type suppressing information, the air speed data of atmosphere data system 104, the vacant lot status information of sky/ground system 105, the high degrees of data of radio altimeter 106, the throttle lever thrust position information of throttle lever maneuvering lever 107, the flap of flap maneuvering lever 108 takes off warning message, the parking brake status information of parking brake handle 109, the landing gear its stored position information of landing gear extension and retraction system 110, the position status information of trailing edge wing flap 111, the position status information of leading edge device 112, the connection status information of automatic Pilot/flight guidance system 113, the positional information of aileron and aileron trim system 114, the positional information of elevating rudder and elevating rudder trim system 115, the positional information of yaw rudder and yaw rudder trim system 116, the position status information of ground interceptor 117, it is determined that warning form of currently taking off, and then export light warning instruction, audio-alert data-driven can the red main warning light 102 of push type, audio devices 103, for flight unit provides lamplight pointing, sound equipment is warned.
1. land take off
When the alarm computer 101 that flies collects following information, then send corresponding instruction/data by electrically exporting interface, triggering can the red main warning light 102 of push type and loud speaker 103 to provide light warning and sound equipment warning.
The sky of �� sky/ground system 105/ground status information " " effectively, and
The throttle lever thrust position information " position of taking off " of �� throttle lever maneuvering lever 107 is effective, and
The air speed value of �� atmosphere data system 104 is less than V1, and
�� the warning of the red main warning light 102 of push type can suppress information invalid.And
There is any following form in ��: the non-security positional information of taking off of the wing flap of trailing edge wing flap system 111 is effective, or the non-security positional information of taking off of the leading edge device of leading edge device 112 is effective, or ground interceptor positional information " withdrawal " of ground interceptor 117 is invalid, or the caution position information of taking off " warning position " of flap maneuvering lever 108 is effective, or the parking brake positional information " parking brake " of parking brake handle 109 is effective, or the trim position information " neutral position " of elevating rudder and elevating rudder trim system 115 is effective, or the trim position information " neutral position " of yaw rudder and yaw rudder trim system 116 is effective, or the trim position information " neutral position " of aileron and aileron trim system 114 is effective, or the connection information " connection " of automatic Pilot/flight guidance system 113 is effective.
2. the water surface takes off
When the alarm computer 101 that flies collects following information, then send corresponding instruction/data by electrically exporting interface, triggering can the red main warning light 102 of push type and loud speaker 103 to provide light warning and sound equipment warning.
The sky of �� sky/ground system 105/ground status information " sky " is effective, and
The height value of �� radio altimeter 106 is less than 6 meters, and
The throttle lever thrust position information " position of taking off " of �� throttle lever maneuvering lever 107 is effective, and
The air speed value of �� atmosphere data system 104 is less than V1, and
�� the warning of the red main warning light 102 of push type can suppress information invalid. And
There is any following form in ��: the non-security positional information of taking off of the wing flap of trailing edge wing flap system 111 is effective, or the non-security positional information of taking off of the leading edge device of leading edge device 112 is effective, or ground interceptor positional information " withdrawal " of ground interceptor 117 is invalid, or the caution position information of taking off " warning position " of flap maneuvering lever 108 is effective, or the trim position information " neutral position " of elevating rudder and elevating rudder trim system 115 is effective, or the trim position information " neutral position " of yaw rudder and yaw rudder trim system 116 is effective, or the trim position information " neutral position " of aileron and aileron trim system 114 is effective, or the connection information " connection " of automatic Pilot/flight guidance system 113 is effective, or the landing gear retracted position invalidating signal of landing gear extension and retraction system 110.
The amphibious of embodiment of the present invention offer takes off warning system, there is following useful effect: connect sky/ground system at the electric input interface place of flight alarm computer, engine maneuvering system, trailing edge wing flap system, leading edge device/system (leading edge wing flap and slat), flap system, brake system, elevating rudder and elevating rudder trim system, yaw rudder and yaw rudder trim system, aileron trim system, automatic Pilot/flight guidance system, landing gear extension and retraction system, atmosphere data system, radio altimeter, can the red main warning light of push type, and electrically export that interface connects at it can the red main warning light of push type, audio devices.
1) by gathering sky/ground system hollow/ground status signal, and the data information of radio altimeter, the water, land and air state that aircraft is current can be judged;
2) by gathering throttle lever thrust position information in engine maneuvering system, can judge whether throttle lever is in and take off within the scope of thrust;
3) by gathering the position status information of wing flap in trailing edge wing flap Controlling System, can judge whether trailing edge wing flap is not in position of taking off, or be in crooked or asymmetric state, or have non-mandatory motion;
4) by having gathered the position status information of leading edge wing flap and slat in leading edge device, can judge whether leading edge wing flap and slat are not released, or have non-mandatory motion;
5) by gathering the position status information of ground interceptor in flap system, can judge that whether ground interceptor is unrecovered;
6) take off warning message by gathering flap in flap system, can judge whether flap handle puts down;
7) by gathering the status information of parking brake in brake system, can judge whether parking brake does not unclamp;
8) by gathering the position signal of trim mechanism in elevating rudder and elevating rudder trim system, can judge whether elevating rudder balancing device exceeds allowed band;
9) by gathering the position signal of trim mechanism in yaw rudder and yaw rudder trim system, can judge whether yaw rudder balancing device exceeds allowed band;
10) connect the status signal of electric switch by gathering automatic Pilot in automatic Pilot/flight guidance system, can judge whether automatic Pilot is switched on;
11) by gathering the position signal of trim mechanism in aileron and aileron trim system, can judge whether aileron balancing device exceeds allowed band;
12) by gathering the status signal of landing gear in landing gear extension and retraction system, can judge whether landing gear is received completely and go up and lock;
13) by gathering air speed value in atmosphere data system, can judge whether air speed is greater than V1;
14) by gather can the suppression signal of the red main warning light of push type, whether warning of can judging to take off is suppressed;
15) by driving can the red main warning light of push type, the red light warning instruction of landing gear its stored position can be provided;
16) by driving audio devices, the sound equipment warning instruction of landing gear its stored position can be provided.
See Fig. 2, it it is the structural representation of amphibious another embodiment taking off warning system provided by the invention. long range data concentrator 118 (configurable multiple) also can be comprised in this takes off warning system, described long range data concentrator 118 is arranged near aircraft sensor source place by nearby principle, and various kinds of sensors data carry out the comprehensive treating processs such as analog to digital conversion, the electric input interface of described long range data concentrator and described atmosphere data system 104, described sky/ground system 105, described radio altimeter 106, described throttle lever maneuvering lever 107, described flap maneuvering lever 108, described parking brake handle 109, described landing gear extension and retraction system 110, described trailing edge wing flap system 111, described leading edge device 112, described automatic Pilot/flight guidance system 113, described aileron and aileron trim system 114, described elevating rudder and elevating rudder trim system 115, described yaw rudder and yaw rudder trim system 116, described ground interceptor 117 is cross-linked, gather relevant state parameter or service data, the parameter collected or data after the comprehensive treating processs such as relevant analog to digital conversion by the electric output interface of described long range data concentrator, it is sent to described flight alarm computer 101. by the introducing of this embodiment medium-long range data centralization device 118, the collection of the organic electronic system signal realizing different grades that can be further, comprehensive treating process and concentration of transmissions, thus improve sharing of Mechatronic Systems/equipment information, reduce the quantity of full machine wire, reduce the complexity of aircraft wiring, thus strengthen the security of whole aircraft system and the property safeguarded.
The present invention is directed to the feature of amphibious aircraft takeoff configuration, provide more complete configuration warning solution route, can effectively warn the abnormal form of taking off that flight unit amphibious aircraft is taken off, land two kinds of differences of taking off are taken off and occurred under state at the water surface, to take timely corresponding to evade measure, improve the security of aircraft, there is bigger practical value.
The above is the preferred embodiment of the present invention; it is noted that for those skilled in the art, under the premise without departing from the principles of the invention; can also making some improvements and modifications, these improvements and modifications are also considered as protection scope of the present invention.
Claims (4)
1. a warning system of taking off, it is characterized in that, comprising: flight alarm computer, sky/ground system, engine maneuvering system, trailing edge wing flap system, leading edge device/system (leading edge wing flap and slat), flap system, brake system, elevating rudder and elevating rudder trim system, yaw rudder and yaw rudder trim system, aileron trim system, automatic Pilot/flight guidance system, landing gear extension and retraction system, atmosphere data system, radio altimeter, can push type redness main warning light, audio devices.
The electric input interface end of described flight alarm computer connect sky/ground system, engine maneuvering system, trailing edge wing flap system, leading edge device/system (leading edge wing flap and slat), flap system, brake system, elevating rudder and elevating rudder trim system, yaw rudder and yaw rudder trim system, aileron and aileron trim system, automatic Pilot/flight guidance system, landing gear extension and retraction system, atmosphere data system, radio altimeter, can the push type main warning light of redness;
The electric output interface end of described flight alarm computer connects can push type red main warning light, audio devices;
Described flight alarm computer is according to taking off what input interface place was collected by warning Logic judgment flow process, the relevant information coming from following system/device carries out comprehensive treating process: described sky/ground system, described engine maneuvering system, described trailing edge wing flap system, described leading edge device, described flap system, described brake system, described elevating rudder and elevating rudder trim system, described yaw rudder and yaw rudder trim system, described aileron and aileron trim system, described automatic Pilot/flight guidance system, described landing gear extension and retraction system, described atmosphere data system, described radio altimeter, described can the red main warning light (warning inhibit feature) of push type, and send the warning instruction of corresponding light according to result, audio-alert information can the red main warning light (light alarm function) of push type to exporting described in interface driver, described audio devices, for flight unit provides visually, dual alert mode in the sense of hearing.
2. take off as claimed in claim 1 warning system, it is characterised in that, described in warning system of taking off also can comprise long range data concentrator, described long range data concentrator is arranged near aircraft sensor source place by nearby principle, and various kinds of sensors data carry out the comprehensive treating processs such as analog to digital conversion, the electric input interface of described long range data concentrator and described sky/ground system, described engine maneuvering system, described trailing edge wing flap system, described leading edge device, described flap system, described brake system, described elevating rudder and elevating rudder trim system, described yaw rudder and yaw rudder trim system, described aileron and aileron trim system, described automatic Pilot/flight guidance system, described landing gear extension and retraction system, described atmosphere data system, described radio altimeter is cross-linked, gather relevant state parameter or service data, the parameter collected or data after the comprehensive treating processs such as relevant analog to digital conversion by the electric output interface of described long range data concentrator, it is sent to described flight alarm computer.
3. take off as claimed in claim 1 warning system, it is characterized in that, described flight alarm COMPUTER DETECTION to: when aircraft is in ground, and one or more throttle lever is in the scope of taking off, and air speed is less than V1 (resolution of taking off speed), and when warning suppression button not press, any one condition not met all can trigger warning system work of taking off below.
A) trailing edge wing flap is not in position of taking off, or is in crooked or asymmetric state, or has non-mandatory motion;
B) leading edge wing flap and slat are not released, or have non-mandatory motion;
C) ground interceptor is unrecovered;
D) flap handle does not put down;
E) parking brake does not unclamp;
F) elevating rudder balancing device (longitudinal trim) exceeds allowed band;
G) yaw rudder balancing device (lateral trim) exceeds allowed band;
H) aileron balancing device (roll trim) exceeds allowed band;
I) robot pilot is connected.
4. take off as claimed in claim 1 warning system, it is characterized in that, described flight alarm COMPUTER DETECTION to: when aircraft is in the water surface, and one or more throttle lever is in the scope of taking off, and air speed is less than V1 (resolution of taking off speed), and when warning suppression button not press, any one condition not met all can trigger warning system work of taking off below.
A) trailing edge wing flap is not in position of taking off, or is in crooked or asymmetric state, or has non-mandatory motion;
B) leading edge wing flap and slat are not released, or have non-mandatory motion;
C) ground interceptor is unrecovered;
D) flap handle does not put down;
E) elevating rudder balancing device (longitudinal trim) exceeds allowed band;
F) yaw rudder balancing device (lateral trim) exceeds allowed band;
G) aileron balancing device (roll trim) exceeds allowed band;
H) robot pilot is connected;
I) arbitrary landing gear is not received and is locked.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628207A (en) * | 2016-11-25 | 2017-05-10 | 上海航空电器有限公司 | Ground proximity warning system alarm inhibition method |
| CN109144079A (en) * | 2018-08-22 | 2019-01-04 | 中国民航大学 | A kind of amphibious aircraft landing configuration control system based on integrated avionics |
| CN109383823A (en) * | 2017-08-14 | 2019-02-26 | 波音公司 | The method and system for determining to be formed is interrupted for intelligent predicting aircraft takeoff |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1567553A (en) * | 1976-06-14 | 1980-05-14 | Litton Industries Inc | Digital ground proximity warning systems |
| CA1295716C (en) * | 1988-04-06 | 1992-02-11 | Charles D. Bateman | Ground proximity warning system for use with aircraft having degraded performance |
| CN1136353A (en) * | 1994-09-28 | 1996-11-20 | 国家航空工业公司 | System for generating an anomaly signal during take-off of an aircraft |
| CN102812502A (en) * | 2010-03-24 | 2012-12-05 | 波音公司 | Runway condition monitoring |
-
2014
- 2014-12-03 CN CN201410725362.7A patent/CN105644800B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1567553A (en) * | 1976-06-14 | 1980-05-14 | Litton Industries Inc | Digital ground proximity warning systems |
| CA1295716C (en) * | 1988-04-06 | 1992-02-11 | Charles D. Bateman | Ground proximity warning system for use with aircraft having degraded performance |
| CN1136353A (en) * | 1994-09-28 | 1996-11-20 | 国家航空工业公司 | System for generating an anomaly signal during take-off of an aircraft |
| CN102812502A (en) * | 2010-03-24 | 2012-12-05 | 波音公司 | Runway condition monitoring |
Non-Patent Citations (1)
| Title |
|---|
| 张建虎: "B737_NG飞机起飞警告故障分析", 《自动化应用》 * |
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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. |