CN204297071U - A kind of amphibious aircraft wheel-retracting gear position warning device - Google Patents
A kind of amphibious aircraft wheel-retracting gear position warning device Download PDFInfo
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- CN204297071U CN204297071U CN201420634231.3U CN201420634231U CN204297071U CN 204297071 U CN204297071 U CN 204297071U CN 201420634231 U CN201420634231 U CN 201420634231U CN 204297071 U CN204297071 U CN 204297071U
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Abstract
The utility model discloses a kind of amphibious aircraft wheel-retracting gear position warning device, comprising: flight alarm computing machine, landing modes selecting arrangement, engine control system, radio altimeter, wing flap control system, landing-gear system, can the red major alarm lamp of push type, audio devices.The electric input interface end of flight alarm computing machine connects landing modes selecting arrangement, engine control system, radio altimeter, wing flap control system, landing-gear system; The electric output interface end of flight alarm computing machine connects can the red major alarm lamp of push type, audio devices; Flight alarm computing machine carries out comprehensive treatment according to the position warning Logic judgment flow process of wheel-retracting gear to the relevant information that input interface place gathers, and send command adapted thereto/information to electric output interface according to result, driving can the red major alarm lamp of push type, audio devices, for flight unit provides visual and dual alert mode acoustically.Adopt the utility model embodiment, can solve lack in the wheel-retracting gear position warning mode required by airworthiness regulation water form warning problem, guarantee the complete of amphibian landing form warning, improve the safety of amphibian system.
Description
Technical field
The utility model belongs to aircraft system circuit design field, particularly relates to a kind of amphibious aircraft wheel-retracting gear position warning device.
Background technology
In the airworthiness regulation the 729th article that Civil Aviation Administration of China promulgates, (CCAR-23-R3 " the 729th article (f) alighting gear warning " and CCAR-25-R4 " the 729th article (e) notch indicator and warning device ") proposes the requirement arranging landing-gear warning device (i.e. aircraft landing form warning) to the aircraft that retractable landing gear is housed.But this airworthiness regulation requires only for land airplane:
1. in order to remind flight unit before alighting gear does not put down completely and pins, engine throttle is not received below specified value, in order to avoid there is stall and land with the alighting gear do not put well in aircraft, land airplane, when arbitrary engine throttle receives the approach fix that exceedes regulation and alighting gear does not put down completely and locks, must arrange the audible warning device of continuous sounding; In order to not disturb the communication of landing period flight unit and ground control, this audible warning device should be provided with and manually stop the measure of ringing, and can when reducing the approach fix that arbitrary throttle specified to (or exceeding) again, can automatically recover its audible warning sound, to remind flight crew check alighting gear whether put down completely and lock.
2. in order to avoid occur due to flight unit landing period be control aspect need to complete more operating sequence at short notice, be in high-pressure state and the mistake occurring putting down wing flap and forget drop, land airplane, when wing flap is put into the approach fix that exceedes regulation and alighting gear does not put down completely and locks, must arrange the audible warning device of continuous sounding; For guaranteeing landing safety, this audible warning device does not allow to arrange manually to stop the measure of ringing.
But amphibious aircraft is with retractable landing gear, have two kinds of different landing states: terrain landing, drop in water surface, the mode of operation of its alighting gear is completely different with the difference of landing form:
1. when amphibious aircraft is selected to land by land, and arbitrary engine throttle receives the approach fix that exceedes regulation or wing flap when being put into the approach fix exceeding regulation, its alighting gear must remain on and put down completely and the state locked, otherwise will cause hardly imaginable disaster;
2. when amphibious aircraft is selected in drop in water surface, and arbitrary engine throttle receives the approach fix that exceedes regulation or wing flap when being put into the approach fix exceeding regulation, its alighting gear must remain on to receive completely and go up and the state locked, otherwise will cause hardly imaginable disaster.
If therefore only by the landing form warning of the requirement design amphibious aircraft of existing airworthiness regulation, this aircraft will certainly be caused the disappearance of water form warning function, this will cause: in water process at aircraft, if alighting gear is not the landing state of safety (namely receive completely and go up and lock), owing to lacking the warning of flight unit to water form, hardly imaginable disaster can be there is when water by aircraft, as wheel-retracting gear destroy by rush of water, housing construction badly broken etc.
Summary of the invention
The utility model proposes a kind of amphibious aircraft wheel-retracting gear position warning device, can solve required by relevant airworthiness regulation wheel-retracting gear position warning (only landing configuration warning) mode in exist water form warning disappearance problem, the complete of amphibious aircraft wheel-retracting gear position warning function (form of namely landing warning) can be guaranteed: comprise landing configuration warning and the warning of water form, to improve the safety of amphibious aircraft system.
The utility model embodiment provides a kind of position warning system of amphibious aircraft wheel-retracting gear, comprising: flight alarm computing machine, landing modes selecting arrangement, engine control system, radio altimeter, wing flap control system, landing-gear system, can the red major alarm lamp of push type, audio devices;
Described flight alarm computing machine is the core component of the utility model embodiment, by corresponding electrically input interface and described landing modes selecting arrangement, described engine control system, described radio altimeter, described wing flap control system, described landing-gear system is cross-linked, gather relevant state parameter or operating data, and according to the landing form warning Logic judgment flow process of computer-internal, comprehensive treatment is carried out to gathered Various types of data, and according to result by corresponding electrically output interface with described can push type redness major alarm lamp, described audio devices is cross-linked, send corresponding light command signal, voice data information, for flight unit provides corresponding warning mode, (red light glimmers, continuous sound prompt).
Described landing modes selecting arrangement is a third gear switch: land, the water surface, neutrality, selects signal: terrain landing mode signal, drop in water surface mode signal, neutral manner signal to described flight alarm computer export three landing modes.When switch is placed in " land " position, terrain landing mode signal is effective, represents that aircraft will adopt terrain landing mode; When switch is placed in " water surface " position, drop in water surface mode signal is effective, represents that aircraft will adopt drop in water surface mode; When switch is placed in " neutrality " position, neutral manner signal is effective, represents that aircraft not yet carries out the selection operation of landing modes.
Described engine control system provides throttle commands signal by throttle lever for driving engine, is used for controlling the size of engine throttle.Throttle lever place arranges multiple manipulation gear, each gear place is to having corresponding position switch in order to provide corresponding throttle lever location information (throttle lever slow train position location information etc.), and send described flight alarm computing machine to and carry out the comprehensive treatments such as the Logic judgment of wheel-retracting gear position warning, wherein throttle lever slow train position location information represents that throttle is recovered to normal landing approach fix.
Described radio altimeter is by its transceiver, reception radiowave, measurement radiowave returns the time that aircraft experiences again from aircraft to ground from ground, the actual height on plane distance ground is obtained after resolving, height value after resolving sends described flight alarm computing machine with digital data format to through data bus, is used for the comprehensive treatments such as the Logic judgment carrying out the warning of wheel-retracting gear position.
Described wing flap control system for trailing edge flap provides command signal-be used for control the folding and unfolding of trailing edge flap by flap control handle, is controlled trailing edge flap by wing flap control assembly and completes folding and unfolding according to command request and provide data message-be used for feeding back the information such as the state of wing flap control system for described flight alarm computing machine.Bar handle place arranges multiple manipulation gear, and the corresponding corresponding location of instruction sensor in each gear place, is converted to electric signal transmission to wing flap control assembly by the mechanical order of flight unit, is used for controlling the folding and unfolding of trailing edge flap; Trailing edge flap folding and unfolding position is provided with flap position transducer, location information (wing flap landing position location information etc.) current for trailing edge flap is fed back to wing flap function unit, described flight alarm computing machine is sent to by wing flap function unit, be used for carrying out the comprehensive treatments such as the Logic judgment of wheel-retracting gear position warning, wherein wing flap landing position location information represents that wing flap is lowered into normal landing approach fix.
Described landing-gear system for alighting gear provides command signal-be used for control the folding and unfolding of alighting gear by alighting gear control handle, is controlled alighting gear by alighting gear function unit and completes folding and unfolding according to command request and provide data message-be used for feeding back the information such as the state of landing-gear system for described flight alarm computing machine.Control handle place arranges multiple gear, and the mechanical order of flight unit, to there being corresponding location of instruction sensor, is converted to electric signal transmission to alighting gear function unit by each gear place, is used for controlling the folding and unfolding of alighting gear; Undercarriage control position arranges multiple position transduser, by current for landing-gear system status information (alighting gear put down completely and lock, alighting gear receives and the information such as locking completely) feed back to alighting gear function unit, send described flight alarm computing machine to by alighting gear function unit, be used for the comprehensive treatments such as the Logic judgment carrying out the warning of wheel-retracting gear position.
Describedly can the push type red major alarm lamp light command signal of sending according to described flight alarm computing machine red light be provided to warn for flight unit; This warning light has pressing reset function simultaneously, namely can be realized the inhibit feature of the warning of corresponding light and audible warning sound by this warning light of pressing.
Described audio devices provides continuous print audible warning sound by receiving the described flight alarm computing machine voice data information of sending for flight unit.
Further, the position warning system of described a kind of amphibious aircraft wheel-retracting gear also can comprise remote data concentrator (configurable multiple), described remote data concentrator is arranged near aircraft sensors source place by nearby principle, various kinds of sensors data is carried out to the comprehensive treatments such as analogue to digital conversion; The electric input interface of described remote data concentrator and described landing modes selecting arrangement, described engine control system, described radio altimeter, described wing flap control system, described landing-gear system are cross-linked, gather relevant state parameter or operating data, the parameter collected or data by the electric output interface of described remote data concentrator, are sent to described flight alarm computing machine after the comprehensive treatments such as relevant analogue to digital conversion.
The position warning system of a kind of amphibious aircraft wheel-retracting gear that the utility model embodiment provides, there is following beneficial effect: connect landing modes selecting arrangement, engine control system, radio altimeter, wing flap control system, landing-gear system at the electric input interface place of flight alarm computing machine, and can the red major alarm lamp of push type, audio devices in its electric output interface place connection.
1. by gathering the location information of landing modes selecting arrangement, the landing modes that aircraft is current can be judged;
2. by gathering the location information of throttle lever slow train position and the data message of radio altimeter in engine control system, can judge whether throttle is recovered to normal landing approach fix;
3. by gathering the location information of wing flap landing position in wing flap control system, can judge whether wing flap is lowered into normal landing approach fix;
4. by gathering the folding and unfolding status information of alighting gear in landing-gear system, can judge alighting gear put down completely/receipts on and lock;
5. can the red major alarm lamp of push type by driving, the red light warning instruction of undercarriage control position can be provided;
6. by driving audio devices, the audible warning sound of undercarriage control position can be provided to indicate;
7. can the red major alarm lamp of push type by pressing, the position caused by throttle lever slow train position, low radio altimeter can be suppressed to warn;
The utility model is for the feature of amphibious aircraft wheel-retracting gear, provide more complete position warning solution route, the flight unit amphibious aircraft mal that wheel-retracting gear occurs when drop in water surface, terrain landing two kinds of different landing modes landing form can be warned by actv., to take corresponding workaround timely, improve the safety of aircraft, there is larger practical value.
Accompanying drawing explanation
Fig. 1 is the structural representation of an embodiment of the position warning system of a kind of amphibious aircraft wheel-retracting gear that the utility model provides; Fig. 2 is the structural representation of another embodiment of the position warning system of a kind of amphibious aircraft wheel-retracting gear that the utility model provides;
In figure, 101-109 is the aircraft system/equipment relevant to wheel-retracting gear position warning system, the criterion of A-H needed for the warning of wheel-retracting gear position.Wherein 101 is flight alarm computing machine, 102 is landing modes selecting arrangement, 103 is power operation parts-throttle lever, 104 is radio altimeter, 105 is wing flap control assembly, and 106 is landing-gear system, and 107 is major alarm lamp, 108 is loud speaker, 109 is remote data concentrator, and A is undercarriage control status system, and B is flap configuration information, C radio altitude information, D throttle lever location information, E is landing modes status information, and F is light information, G is aural information, and H is comprehensive warning message.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the utility model embodiment, be clearly and completely described the technical scheme in the utility model embodiment, obviously, described embodiment is only the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.
The utility model provides a kind of amphibious aircraft wheel-retracting gear position warning device, can solve the problem of the wheel-retracting gear position warning instruction of amphibious aircraft under different landing modes, effectively improve the safety of system.
See Fig. 1, it is the structural representation of an embodiment of a kind of amphibious aircraft wheel-retracting gear position warning system that the utility model provides.
The utility model embodiment provides a kind of position warning system of amphibious aircraft wheel-retracting gear, comprising: flight alarm computing machine 101, landing modes selecting arrangement 102, engine control system-throttle lever 103, radio altimeter 104, wing flap control system-wing flap control assembly 105, landing-gear system 106, can the red major alarm lamp 107 of push type, audio devices 108.Specific as follows:
The electric input interface end of flight alarm computing machine 101 connects landing modes selecting arrangement 102, engine control system-throttle lever 103, radio altimeter 104, wing flap control system-wing flap control assembly 105, landing-gear system 106, and electric output interface end connects can the red major alarm lamp 107 of push type, audio devices 108.
Flight alarm computing machine 101 selects signal according to the position in landing modes selecting arrangement 102, determines the landing modes that aircraft is current: terrain landing mode signal is effective when switch is placed in " land " position, then represent that aircraft will adopt terrain landing mode; When switch is placed in " water surface " position, drop in water surface mode signal is effective, then represent that aircraft will adopt drop in water surface mode; When switch is placed in " neutrality " position, neutral manner signal is effective, then represent that aircraft not yet carries out the selection operation of landing modes.
Flight alarm computing machine 101 is according to the altitude information of the slow train position position signal in engine control system-throttle lever 103 and radio altimeter 104, determine the landing form that aircraft is current: position signal is effective when one or more throttle lever slow train positions, and radio altitude is lower than 800 feet, then represent that one or more throttle has been recovered to the landing approach position of regulation, namely aircraft is current is in regular descent program.
Flight alarm computing machine 101 is according to the wing flap landing position position signal in wing flap control system-wing flap control assembly 105, determine the landing form that aircraft is current: position signal is effective when wing flap landing position, then represent that wing flap has been lowered into the landing approach position of regulation, namely aircraft is current is in regular descent program.
Flight alarm computing machine 101 is according to the undercarriage control position signal in landing-gear system 106, determine the folding and unfolding state that alighting gear is current: go up when undercarriage stowage position signal effectively then represents that alighting gear is received completely and lock, on the contrary then represent alighting gear completely receive go up and lock; When gear down position signal effectively then represents that alighting gear puts down completely and locks, otherwise then represent that alighting gear does not put down completely and locks.
Flight alarm computing machine 101 selects signal according to the position of landing modes selecting arrangement 102, the slow train position position signal of engine control system-throttle lever 103, the altitude information of radio altimeter 104, the wing flap landing position position signal of wing flap control system-wing flap control assembly 105 and the undercarriage control position signal of landing-gear system 106, determine the position warning form of current wheel-retracting gear, and then export light warning instruction, audio-alert data-driven can the red major alarm lamp 107 of push type, audio devices 108, for flight unit provides lamplight pointing, audible warning sound:
1. landing modes warning: if not yet select landing modes (non-selected terrain landing or drop in water surface) when aircraft prepares landing, then give a warning (lamplight pointing, audible warning sound) to point out flying machine group selection rational landing modes to flight unit.
● when flight alarm computing machine 101 collect one or several throttle lever 103 slow train position position signal effectively and the data of radio altimeter 104 lower than 800 feet, and landing modes selecting arrangement 102 is not when " water surface " or " land " position (namely neutral manner signal is effective), this flight alarm computing machine 101 send light warning order-driven can the red major alarm lamp 107 of push type provide red light glimmer warning, send audio-alert data-driven audio devices 108 continuous audible warning sound be provided.
This warning is inhibited by pressing red major alarm lamp 107: red major alarm lamp extinguishes, and audible warning sound stops simultaneously.When again reducing arbitrary throttle to position, (or exceeding) slow train position, this warning will be restarted.
● the wing flap landing position position signal collected in wing flap control system-wing flap control assembly 105 when flight alarm computing machine 101 is effective, and landing modes selecting arrangement 102 is not when " water surface " or " land " position (namely neutral manner signal is effective), this flight alarm computing machine 101 send light warning order-driven can the red major alarm lamp 107 of push type provide red light glimmer warning, send audio-alert data-driven audio devices 108 continuous audible warning sound be provided.
Specify requirement by CCAR25, this warning does not arrange any artificial braking measure, presses red major alarm lamp 107 and cannot suppress this warning.
2. terrain landing warning: if alighting gear does not put down completely and locks when aircraft prepares terrain landing, then give a warning (lamplight pointing, audible warning sound) to point out flying machine group selection rational operating sequence to flight unit, avoid the catastrophic failure jeopardizing aircraft safety.
● the terrain landing mode signal collecting landing modes selecting arrangement 102 when flight alarm computing machine 101 is effective, and the slow train position position signal of one or several throttle lever 103 effectively and the data of radio altimeter 104 lower than 800 feet, and in landing-gear system 106 gear down position signal is invalid time, this flight alarm computing machine 101 send light warning order-driven can the red major alarm lamp 107 of push type provide red light glimmer warning, send audio-alert data-driven audio devices 108 continuous audible warning sound be provided.
This warning is inhibited by pressing red major alarm lamp 107: red major alarm lamp extinguishes, and audible warning sound stops simultaneously.When again reducing arbitrary throttle to position, (or exceeding) slow train position, this warning will be restarted.
● the terrain landing mode signal collecting landing modes selecting arrangement 102 when flight alarm computing machine 101 is effective, and the wing flap in wing flap control system-wing flap control assembly 105 lands, position position signal is effective, and in landing-gear system 106 gear down position signal is invalid time, this flight alarm computing machine 101 send light warning order-driven can the red major alarm lamp 107 of push type provide red light glimmer warning, send audio-alert data-driven audio devices 108 continuous audible warning sound be provided.
Specify requirement by CCAR25, this warning does not arrange any artificial braking measure, presses red major alarm lamp 107 and cannot suppress this warning.
3. drop in water surface warning: if alighting gear is not packed up completely and locks when aircraft prepares drop in water surface, give a warning (lamplight pointing, audible warning sound) to point out flying machine group selection rational operating sequence to flight unit, avoid the catastrophic failure jeopardizing aircraft safety.
● the water landing mode signal collecting landing modes selecting arrangement 102 when flight alarm computing machine 101 is effective, and the slow train position position signal of one or several throttle lever 103 effectively and the data of radio altimeter 104 lower than 800 feet, and undercarriage stowage position signal in landing-gear system 106 invalid time, this flight alarm computing machine 101 send light warning order-driven can the red major alarm lamp 107 of push type provide red light glimmer warning, send audio-alert data-driven audio devices 108 continuous audible warning sound be provided.
This warning is inhibited by pressing red major alarm lamp 107: red major alarm lamp extinguishes, and audible warning sound stops simultaneously.When again reducing arbitrary throttle to position, (or exceeding) slow train position, this warning will be restarted.
● the water landing mode signal collecting landing modes selecting arrangement 102 when flight alarm computing machine 101 is effective, and the wing flap in wing flap control system-wing flap control assembly 105 lands, position position signal is effective, and undercarriage stowage position signal in landing-gear system 106 invalid time, this flight alarm computing machine 101 send light warning order-driven can the red major alarm lamp 107 of push type provide red light glimmer warning, send audio-alert data-driven audio devices 108 continuous audible warning sound be provided.
Specify requirement by CCAR25, this warning does not arrange any artificial braking measure, presses red major alarm lamp 107 and cannot suppress this warning.
The position warning device of the amphibious aircraft wheel-retracting gear that the utility model embodiment provides, there is following beneficial effect: connect landing modes selecting arrangement, engine control system, radio altimeter, wing flap control system, landing-gear system at the electric input interface place of flight alarm computing machine, and can the red major alarm lamp of push type, audio devices in its electric output interface place connection.
1. by gathering the location information of landing modes selecting arrangement, the landing modes that aircraft is current can be judged;
2. by gathering the location information of throttle lever slow train position and the data message of radio altimeter in engine control system, can judge whether throttle is recovered to normal landing approach fix;
3. by gathering the location information of wing flap landing position in wing flap control system, can judge whether wing flap is lowered into normal landing approach fix;
4. by gathering the folding and unfolding status information of alighting gear in landing-gear system, can judge alighting gear put down completely/receipts on and lock;
5. can the red major alarm lamp of push type by driving, the red light warning instruction of undercarriage control position can be provided;
6. by driving audio devices, the audible warning sound of undercarriage control position can be provided to indicate;
7. can the red major alarm lamp of push type by pressing, the position caused by throttle lever slow train position, low radio altimeter can be suppressed to warn;
See Fig. 2, it is the structural representation of another embodiment of the position warning system of a kind of amphibious aircraft wheel-retracting gear that the utility model provides.Remote data concentrator 109 (configurable multiple) also can be comprised in the position warning device of this amphibious aircraft wheel-retracting gear, described remote data concentrator 109 is arranged near aircraft sensors source place by nearby principle, various kinds of sensors data is carried out to the comprehensive treatments such as analogue to digital conversion; The electric input interface of described remote data concentrator and described landing modes selecting arrangement 102, described engine control system 103, described radio altimeter 104, described wing flap control system 105, described landing-gear system 106 are cross-linked, gather relevant state parameter or operating data, the parameter collected or data by the electric output interface of described remote data concentrator, are sent to described flight alarm computing machine 101 after the comprehensive treatments such as relevant analogue to digital conversion.By the introducing of this embodiment medium-long range data concentrator 109, further can realize the collection of the organic electronic system signal of different brackets, comprehensive treatment and concentration of transmissions, thus improve sharing of Mechatronic Systems/facility information, reduce the quantity of full machine wire, reduce the complexity of aircraft wiring, thus strengthen safety and the maintainability of whole aircraft system.
The utility model is for the feature of amphibian wheel-retracting gear, provide more complete position warning solution route, the flight unit amphibian mal that wheel-retracting gear occurs when drop in water surface, terrain landing two kinds of different landing modes landing form can be warned by actv., to take corresponding workaround timely, improve the safety of aircraft, there is larger practical value.
The above is preferred implementation of the present utility model; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the utility model principle; can also make some improvements and modifications, these improvements and modifications are also considered as protection domain of the present utility model.
Claims (5)
1. an amphibious aircraft wheel-retracting gear position warning device, it is characterized in that, its outside interconnected system comprises: flight alarm computing machine, landing modes selecting arrangement, engine control system, radio altimeter, wing flap control system, landing-gear system, can the red major alarm lamp of push type, audio devices;
The electric input interface end of described flight alarm computing machine connects landing modes selecting arrangement, engine control system, radio altimeter, wing flap control system, landing-gear system;
The electric output interface end of described flight alarm computing machine connects can the red major alarm lamp of push type, audio devices;
Landing modes status information in the described landing modes selecting arrangement that described flight alarm computing machine collects input interface place according to the position warning Logic judgment flow process of wheel-retracting gear, throttle lever location information in described engine control system, elevation information in described radio altimeter, flap configuration information in described wing flap control system, undercarriage control status information in described landing-gear system carries out comprehensive treatment, and send corresponding light warning instruction according to result, audio-alert information is to output interface, drive described can the red major alarm lamp of push type, described audio devices, for flight unit provides visual, dual alert mode acoustically.
2. wheel-retracting gear position as claimed in claim 1 warning device, it is characterized in that, described position warning device also can comprise remote data concentrator; Described remote data concentrator is arranged near aircraft sensors source place by nearby principle, various kinds of sensors data is carried out to the comprehensive treatments such as analogue to digital conversion; The electric input interface of described remote data concentrator and described landing modes selecting arrangement, described engine control system, described radio altimeter, described wing flap control system, described landing-gear system are cross-linked, gather relevant state parameter or operating data, the parameter collected or data by the electric output interface of described remote data concentrator, are sent to described flight alarm computing machine after the comprehensive treatments such as relevant analogue to digital conversion.
3. wheel-retracting gear position as claimed in claim 1 warning device, it is characterized in that, described flight alarm COMPUTER DETECTION arrives: in described landing modes selecting arrangement, neutral manner signal is effective, and exist in described engine control system one or several throttle lever slow train positions position signal actvies simultaneously described radio altimeter data lower than 800 feet, or wing flap landing position position signal is effective in described wing flap control system, then send corresponding instruction/data by electric output interface, trigger described can the red major alarm lamp of push type and described audio devices warning and audible warning sound to provide light, warning caused by the slow parking space state of described engine control system throttle lever and described radio altimeter data is by pressing described can being inhibited by the red major alarm lamp of push type, and the warning after suppression is restarted to during position, slow train position again reducing arbitrary throttle subsequently, the warning of being landed caused by the state of position by described wing flap control system wing flap does not allow to arrange any artificial braking measure.
4. wheel-retracting gear position as claimed in claim 1 warning device, it is characterized in that, described flight alarm COMPUTER DETECTION arrives: in described landing modes selecting arrangement, terrain landing mode signal is effective, in described landing-gear system, gear down position signal is effective, and exist in described engine control system one or several throttle lever slow train positions position signal actvies simultaneously described radio altimeter data lower than 800 feet, or wing flap landing position position signal is effective in described wing flap control system, then send corresponding instruction/data by electric output interface, trigger described can the red major alarm lamp of push type and described audio devices warning and audible warning sound to provide light, warning caused by the slow parking space state of described engine control system throttle lever and described radio altimeter data is by pressing described can being inhibited by the red major alarm lamp of push type, and the warning after suppression is restarted to during position, slow train position again reducing arbitrary throttle subsequently, the warning of being landed caused by the state of position by described wing flap control system wing flap does not allow to arrange any artificial braking measure.
5. wheel-retracting gear position as claimed in claim 1 warning device, it is characterized in that, described flight alarm COMPUTER DETECTION arrives: in described landing modes selecting arrangement, water landing mode signal is effective, in described landing-gear system, undercarriage stowage position signal is effective, and exist in described engine control system one or several throttle lever slow train positions position signal actvies simultaneously described radio altimeter data lower than 800 feet, or wing flap landing position position signal is effective in described wing flap control system, then send corresponding instruction/data by electric output interface, trigger described can the red major alarm lamp of push type and described audio devices warning and audible warning sound to provide light, warning caused by the slow parking space state of described engine control system throttle lever and described radio altimeter data is by pressing described can being inhibited by the red major alarm lamp of push type, and the warning after suppression is restarted to during position, slow train position again reducing arbitrary throttle subsequently, the warning of being landed caused by the state of position by described wing flap control system wing flap does not allow to arrange any artificial braking measure.
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| CN201420634231.3U CN204297071U (en) | 2014-10-28 | 2014-10-28 | A kind of amphibious aircraft wheel-retracting gear position warning device |
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| CN201420634231.3U CN204297071U (en) | 2014-10-28 | 2014-10-28 | A kind of amphibious aircraft wheel-retracting gear position warning device |
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| CN105151282A (en) * | 2015-09-14 | 2015-12-16 | 江西洪都航空工业集团有限责任公司 | Control method for reliable ground locking of landing gear of airplane |
| CN105620733A (en) * | 2014-10-28 | 2016-06-01 | 中航通飞研究院有限公司 | Position alarm device for amphibious aircraft undercarriage folding and unfolding mechanism |
| CN106184783A (en) * | 2016-08-17 | 2016-12-07 | 哈尔滨飞机工业集团有限责任公司 | A kind of audible alarm control system |
| CN109871628A (en) * | 2019-02-27 | 2019-06-11 | 北京航空航天大学 | It is a kind of for assessing the simulation computing system and method for amphibious aircraft seaworthiness accordance |
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2014
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| CN105620733B (en) * | 2014-10-28 | 2017-11-17 | 中航通飞研究院有限公司 | A kind of amphibious aircraft wheel-retracting gear position warning device |
| CN105015801A (en) * | 2015-06-02 | 2015-11-04 | 中航飞机股份有限公司西安飞机分公司 | Undercarriage raising/lowering time detection device |
| CN105151282A (en) * | 2015-09-14 | 2015-12-16 | 江西洪都航空工业集团有限责任公司 | Control method for reliable ground locking of landing gear of airplane |
| CN106184783A (en) * | 2016-08-17 | 2016-12-07 | 哈尔滨飞机工业集团有限责任公司 | A kind of audible alarm control system |
| CN109871628A (en) * | 2019-02-27 | 2019-06-11 | 北京航空航天大学 | It is a kind of for assessing the simulation computing system and method for amphibious aircraft seaworthiness accordance |
| CN109871628B (en) * | 2019-02-27 | 2021-03-09 | 北京航空航天大学 | Simulation computing system and method for evaluating seaworthiness compliance of amphibious aircraft |
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