CN105620733A - Position alarm device for amphibious aircraft undercarriage folding and unfolding mechanism - Google Patents
Position alarm device for amphibious aircraft undercarriage folding and unfolding mechanism Download PDFInfo
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Abstract
The invention discloses a position alarm device for an amphibious aircraft undercarriage folding and unfolding mechanism. The position alarm device comprises an aircraft alarm computer, a landing mode selection device, an engine operation system, a radio altimeter, a flap control system, an undercarriage folding and unfolding system, a press type red main alarm lamp and a voice frequency device. The electrical input interface end of the aircraft alarm computer is connected with the landing mode selection device, the engine operation system, the radio altimeter, the flap control system and the undercarriage folding and unfolding system. The electrical output interface end of the aircraft alarm computer is connected with the press type red main alarm lamp and the voice frequency device. The aircraft alarm computer comprehensively processes related information acquired by an input interface according to a position alarm logic judgment procedure of the undercarriage folding and unfolding system and sends corresponding commands/information to an electric output interface according to the processing result to drive the press type red main alarm lamp and the voice frequency device, and visual and acoustic double alarm modes are provided for flight crew.
Description
Technical field
The invention belongs to aircraft system circuit design field, particularly relate to a kind of amphibious aircraft wheel-retracting gear position caution device.
Background technology
In the airworthiness regulation the 729th article that Civil Aviation Administration of China promulgates, the aircraft equipped with retractable landing gear is proposed the requirement arranging landing-gear warning device (i.e. aircraft landing form warning) by (CCAR-23-R3 " the 729th article the warning of (f) undercarriage " and CCAR-25-R4 " the 729th article (e) position indicator and caution device "). But this airworthiness regulation requires only for land airplane:
1. in order to remind flight unit before undercarriage does not put down completely and pins, engine throttle is not received below setting, in order to avoid aircraft occurs that stall is landed with the undercarriage do not put well, land airplane is not when arbitrary engine throttle receives the approach fix exceeding regulation, undercarriage puts down completely and locks, it is necessary to 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, in order to remind whether flight crew check undercarriage puts down completely and lock.
2. in order to avoid occur due to flight unit landing period be control aspect need to complete more operation sequence at short notice, the mistake being in high-pressure state and occur putting down wing flap and forget drop, land airplane is not when wing flap is put into the approach fix exceeding regulation, undercarriage puts down completely and locks, it is necessary to arrange the audible warning device of continuous sounding; For guaranteeing landing safety, this audible warning device does not allow to arrange and manually stops the measure of ringing.
But amphibious aircraft is with retractable landing gear, has landing state two kinds different: terrain landing, drop in water surface, the duty of its undercarriage is completely different with the difference of landing form:
1. when amphibious aircraft selects to land by land, and when arbitrary engine throttle receives the approach fix exceeding regulation or wing flap is put into the approach fix exceeding regulation, its undercarriage preferably must be held in the state put down completely and lock, and otherwise will cause hardly imaginable disaster;
2. when amphibious aircraft selects in drop in water surface, and when arbitrary engine throttle receives the approach fix exceeding regulation or wing flap is put into the approach fix exceeding regulation, its undercarriage preferably must be held in receives state that is upper and that lock completely, otherwise will cause hardly imaginable disaster.
If therefore only design the landing form warning of amphibious aircraft by the requirement 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 undercarriage is not the landing state of safety (namely receive upper completely and lock), owing to lacking the warning that flight unit water form, hardly imaginable disaster can be there is when water by aircraft, as wheel-retracting gear destroy by rush of water, housing construction serious damage etc.
Summary of the invention
The present invention proposes a kind of amphibious aircraft wheel-retracting gear position caution device, can solve the problem that required by relevant airworthiness regulation wheel-retracting gear position warning (only landing configuration warning) mode in exist water form warning disappearance problem, it is able to ensure that the complete of amphibious aircraft wheel-retracting gear position warning function (i.e. the warning of landing form): include landing configuration warning and the warning of water form, to improve the safety of amphibious aircraft system.
The embodiment of the present invention provides the position warning system of a kind of amphibious aircraft wheel-retracting gear, including: flight alarm computer, landing modes select device, engine control system, radio altimeter, wing flap control system, landing-gear system, can pressing type redness major alarm lamp, audio devices;
Described flight alarm computer is the core component of the embodiment of the present invention, device is selected with described landing modes by corresponding electrically input interface, described engine control system, described radio altimeter, described wing flap controls system, described landing-gear system cross-links, gather relevant state parameter or service data, and warn the logical judgment flow process Various types of data to gathering to carry out integrated treatment according to the landing form of computer-internal, and according to result by corresponding electrically output interface with described can pressing type redness major alarm lamp, described audio devices cross-links, send corresponding light command signal, voice data information, there is provided for flight unit and warn mode (red light flicker accordingly, continuous sound prompt).
Described landing modes selects device to be a third gear switch: land, the water surface, neutrality, selects signal to described flight alarm three landing modes of computer export: terrain landing mode signal, drop in water surface mode signal, neutral manner signal. 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 electromotor, 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 positional information (throttle lever slow train position positional information etc.), and send described flight alarm computer to and carry out the integrated treatment such as logical judgment of wheel-retracting gear position warning, wherein throttle lever slow train position positional information represents that throttle is recovered to normal landing approach fix.
Described radio altimeter is by its transceiver, reception radio wave, measure radio wave from aircraft to ground, return the time that aircraft experiences again from ground, the actual height on plane distance ground is obtained after resolving, height value after resolving sends described flight alarm computer with digital data format to through data/address bus, for carrying out the integrated treatments such as the logical judgment of wheel-retracting gear position warning.
Described wing flap controls system provides command signal-for controlling the folding and unfolding of trailing edge flap by flap control handle for trailing edge flap, controls assembly by wing flap and controls trailing edge flap and complete folding and unfolding according to command request and provide data message-for feeding back the information such as the state of wing flap control system for described flight alarm computer. Control crank place arranges multiple manipulation gear, the corresponding corresponding location of instruction sensor in each gear place, the mechanical order of flight unit is converted to the signal of telecommunication and is transferred to wing flap control assembly, be used for controlling the folding and unfolding of trailing edge flap; Trailing edge flap folding and unfolding position is provided with flap position transducer, positional information (wing flap landing position positional information etc.) current for trailing edge flap is fed back to wing flap and controls parts, control parts by wing flap and send described flight alarm computer to, for carrying out the integrated treatments such as the logical judgment of wheel-retracting gear position warning, wherein wing flap landing position positional information represents that wing flap is lowered into normal landing approach fix.
Described landing-gear system provides command signal-for controlling the folding and unfolding of undercarriage by undercarriage joystick for undercarriage, controls component controls undercarriage by undercarriage and completes folding and unfolding according to command request and provide data message-for feeding back the information such as the state of landing-gear system for described flight alarm computer. Joystick place arranges multiple gear, and the mechanical order of flight unit, to there being corresponding location of instruction sensor, is converted to the signal of telecommunication and is transferred to undercarriage control parts, be used for controlling the folding and unfolding of undercarriage by each gear place; Undercarriage control position arranges multiple position sensor, current for landing-gear system status information information such as (undercarriage puts down completely and locks, undercarriage is received completely and) lockings is fed back to undercarriage and controls parts, control parts by undercarriage and send described flight alarm computer to, for carrying out the integrated treatments such as the logical judgment of wheel-retracting gear position warning.
Described can pressing type redness major alarm lamp be the offer red light warning of flight unit according to the light command signal that described flight alarm computer is sent; This emergency warning lamp has pressing reset function simultaneously, namely can realize the suppression function of the warning of corresponding light and audible warning sound by pressing this emergency warning lamp.
The voice data information that described audio devices is sent by receiving described flight alarm computer provides continuous print audible warning sound for flight unit.
Further, the position warning system of described a kind of amphibious aircraft wheel-retracting gear may also include remote data concentrator (configurable multiple), described remote data concentrator is disposed adjacent to aircraft sensors source place by nearby principle, and various kinds of sensors data carry out the integrated treatments such as analog digital conversion; The electric input interface of described remote data concentrator and described landing modes select device, described engine control system, described radio altimeter, described wing flap to control system, the crosslinking of described landing-gear system, gather relevant state parameter or service data, the parameter collected or data by the electric output interface of described remote data concentrator, are sent to described flight alarm computer after the integrated treatments such as relevant analog digital conversion.
The position warning system of a kind of amphibious aircraft wheel-retracting gear that the embodiment of the present invention provides, have the advantages that connecting landing modes at the electric input interface place of the alarm computer that flies selects device, engine control system, radio altimeter, wing flap to control system, landing-gear system, and connection can pressing type redness major alarm lamp, audio devices at its electric output interface place.
1. select the positional information of device by gathering landing modes, can determine whether out the landing modes that aircraft is current;
2. the data message of the positional information and radio altimeter by gathering throttle lever slow train position in engine control system, can determine whether out whether throttle is recovered to normal landing approach fix;
3. by gathering the positional information of wing flap landing position in wing flap control system, can determine whether out whether wing flap is lowered into normal landing approach fix;
4. by gathering the folding and unfolding status information of undercarriage in landing-gear system, can determine whether out that undercarriage puts down completely/receives and locks;
5. can pressing type redness major alarm lamp by driving, it is possible to provide the red light warning instruction of undercarriage control position;
6. by driving audio devices, it is possible to provide the audible warning sound instruction of undercarriage control position;
7. by pressing can pressing type redness major alarm lamp, the position caused by throttle lever slow train position, low radio altimeter can be suppressed to warn;
The present invention is directed to the feature of amphibious aircraft wheel-retracting gear, provide more complete position warning solution route, can effectively warn the flight unit amphibious aircraft abnormal landing form that wheel-retracting gear occurs when drop in water surface, two kinds of different landing modes of terrain landing, to take corresponding workaround timely, improve the safety of aircraft, there is bigger 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 provided by the invention; Fig. 2 is the structural representation of another embodiment of the position warning system of a kind of amphibious aircraft wheel-retracting gear provided by the invention;
In figure, 101-109 is the aircraft system/equipment relevant to wheel-retracting gear position warning system, and A-H is the criterion that the warning of wheel-retracting gear position is required. Wherein 101 is flight alarm computer, 102 select device for landing modes, 103 is power operation parts-throttle lever, 104 is radio altimeter, 105 control assembly for wing flap, and 106 is landing-gear system, and 107 is major alarm lamp, 108 is 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 positional 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 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 a part of embodiment of the present invention, rather than whole embodiments. Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of protection of the invention.
The present invention provides a kind of amphibious aircraft wheel-retracting gear position caution device, it is possible to the problem solving amphibious aircraft wheel-retracting gear position warning instruction under different landing modes, is effectively improved the safety of system.
Referring to Fig. 1, it it is the structural representation of an embodiment of a kind of amphibious aircraft wheel-retracting gear position provided by the invention warning system.
The embodiment of the present invention provides the position warning system of a kind of amphibious aircraft wheel-retracting gear, including: flight alarm computer 101, landing modes select device 102, engine control system-throttle lever 103, radio altimeter 104, wing flap control system-wing flap control assembly 105, landing-gear system 106, can pressing type redness major alarm lamp 107, audio devices 108. Specific as follows:
The electric input interface end of flight alarm computer 101 connects landing modes and selects device 102, engine control system-throttle lever 103, radio altimeter 104, wing flap control system-wing flap to control assembly 105, landing-gear system 106, and electric output interface end connects can pressing type redness major alarm lamp 107, audio devices 108.
Flight alarm computer 101 selects the position in device 102 to select signal according to landing modes, it is determined that the landing modes that aircraft is current: terrain landing mode signal is effective when switch is placed in " land " position, then it represents that aircraft will adopt terrain landing mode; When switch is placed in " water surface " position, drop in water surface mode signal is effective, then it represents that aircraft will adopt drop in water surface mode; When switch is placed in " neutrality " position, neutral manner signal is effective, then it represents that aircraft not yet carries out the selection operation of landing modes.
The flight alarm computer 101 altitude information according to the slow train position position signalling in engine control system-throttle lever 103 and radio altimeter 104, determine the landing form that aircraft is current: position signalling is effective when one or more throttle lever slow train positions, and radio altitude is lower than 800 feet, then representing that one or more throttle has been retracted into the landing approach position of regulation, namely aircraft is currently in regular descent program.
Flight alarm computer 101 controls, according to wing flap, the wing flap landing position position signalling that system-wing flap controls in assembly 105, determine the landing form that aircraft is current: position signalling is effective when wing flap landing position, then representing that wing flap has been lowered into the landing approach position of regulation, namely aircraft is currently in regular descent program.
Flight alarm computer 101 is according to the undercarriage control position signalling in landing-gear system 106, determine the folding and unfolding state that undercarriage is current: when undercarriage stowage position signalling effectively then represents that undercarriage is received completely and locks, otherwise then represent that undercarriage is not received upper completely and locks; When gear down position signalling effectively then represents that undercarriage puts down completely and locks, otherwise then represent that undercarriage does not put down completely and locks.
Flight alarm computer 101 selects the position of device 102 to select signal according to landing modes, the slow train position position signalling of engine control system-throttle lever 103, the altitude information of radio altimeter 104, wing flap controls system-wing flap and controls the wing flap landing position position signalling of assembly 105 and the undercarriage control position signalling of landing-gear system 106, determine the position warning form of current wheel-retracting gear, and then output light warning instruction, audio-alert data-driven can pressing type redness major alarm lamp 107, audio devices 108, lamplight pointing is provided for flight unit, audible warning sound:
1. landing modes warning: if not yet selecting 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 computer 101 collect one or several throttle lever 103 slow train position position signalling effectively and the data of radio altimeter 104 lower than 800 feet, and landing modes selection device 102 is not when " water surface " or " land " position (namely neutral manner signal is effective), this flight alarm computer 101 sends light warning order-driven can provide red light flicker warning, transmission audio-alert data-driven audio devices 108 to provide continuous audible warning sound by pressing type redness major alarm lamp 107.
This warning can be passed through to press red major alarm lamp 107 and be inhibited: red major alarm lamp extinguishes, and audible warning sound terminates simultaneously. When again reducing arbitrary throttle to position, (or exceeding) slow train position, it will restart this warning.
�� the wing flap landing position position signalling collected in wing flap control system-wing flap control assembly 105 when flight alarm computer 101 is effective, and landing modes selection device 102 is not when " water surface " or " land " position (namely neutral manner signal is effective), this flight alarm computer 101 sends light warning order-driven can provide red light flicker warning, transmission audio-alert data-driven audio devices 108 to provide continuous audible warning sound by pressing type redness major alarm lamp 107.
Specifying requirement by CCAR25, this warning is not provided with any artificial braking measure, and the red major alarm lamp 107 of pressing cannot suppress this warning.
2. terrain landing warning: if undercarriage 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 operation sequence to flight unit, it is to avoid jeopardize the catastrophic failure of aircraft safety.
�� when flight alarm computer 101 collect landing modes select device 102 terrain landing mode signal effective, and the slow train position position signalling 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 when gear down position signalling is invalid, this flight alarm computer 101 send light warning order-driven can pressing type redness major alarm lamp 107 provide red light flicker warning, send audio-alert data-driven audio devices 108 continuous audible warning sound is provided.
This warning can be passed through to press red major alarm lamp 107 and be inhibited: red major alarm lamp extinguishes, and audible warning sound terminates simultaneously. When again reducing arbitrary throttle to position, (or exceeding) slow train position, it will restart this warning.
�� when flight alarm computer 101 collect landing modes select device 102 terrain landing mode signal effective, and wing flap to control the wing flap landing position position signalling that system-wing flap controls in assembly 105 effective, and in landing-gear system 106 when gear down position signalling is invalid, this flight alarm computer 101 send light warning order-driven can pressing type redness major alarm lamp 107 provide red light flicker warning, send audio-alert data-driven audio devices 108 continuous audible warning sound is provided.
Specifying requirement by CCAR25, this warning is not provided with any artificial braking measure, and the red major alarm lamp 107 of pressing cannot suppress this warning.
3. drop in water surface warning: if undercarriage is not packed up completely and locks when aircraft prepares drop in water surface, (lamplight pointing, audible warning sound) is given a warning to point out flying machine group selection rational operation sequence, it is to avoid jeopardize the catastrophic failure of aircraft safety to flight unit.
�� when flight alarm computer 101 collect landing modes select device 102 water landing mode signal effective, and the slow train position position signalling of one or several throttle lever 103 effectively and the data of radio altimeter 104 lower than 800 feet, and undercarriage stowage position signalling in landing-gear system 106 invalid time, this flight alarm computer 101 sends light warning order-driven and can provide red light flicker warning, send audio-alert data-driven audio devices 108 and provide continuous audible warning sound by pressing type redness major alarm lamp 107.
This warning can be passed through to press red major alarm lamp 107 and be inhibited: red major alarm lamp extinguishes, and audible warning sound terminates simultaneously. When again reducing arbitrary throttle to position, (or exceeding) slow train position, it will restart this warning.
�� when flight alarm computer 101 collect landing modes select device 102 water landing mode signal effective, and wing flap to control the wing flap landing position position signalling that system-wing flap controls in assembly 105 effective, and undercarriage stowage position signalling in landing-gear system 106 invalid time, this flight alarm computer 101 sends light warning order-driven and can provide red light flicker warning, send audio-alert data-driven audio devices 108 and provide continuous audible warning sound by pressing type redness major alarm lamp 107.
Specifying requirement by CCAR25, this warning is not provided with any artificial braking measure, and the red major alarm lamp 107 of pressing cannot suppress this warning.
The position caution device of the amphibious aircraft wheel-retracting gear that the embodiment of the present invention provides, have the advantages that connecting landing modes at the electric input interface place of the alarm computer that flies selects device, engine control system, radio altimeter, wing flap to control system, landing-gear system, and connection can pressing type redness major alarm lamp, audio devices at its electric output interface place.
1. select the positional information of device by gathering landing modes, can determine whether out the landing modes that aircraft is current;
2. the data message of the positional information and radio altimeter by gathering throttle lever slow train position in engine control system, can determine whether out whether throttle is recovered to normal landing approach fix;
3. by gathering the positional information of wing flap landing position in wing flap control system, can determine whether out whether wing flap is lowered into normal landing approach fix;
4. by gathering the folding and unfolding status information of undercarriage in landing-gear system, can determine whether out that undercarriage puts down completely/receives and locks;
5. can pressing type redness major alarm lamp by driving, it is possible to provide the red light warning instruction of undercarriage control position;
6. by driving audio devices, it is possible to provide the audible warning sound instruction of undercarriage control position;
7. by pressing can pressing type redness major alarm lamp, the position caused by throttle lever slow train position, low radio altimeter can be suppressed to warn;
Referring to Fig. 2, it it is the structural representation of another embodiment of the position warning system of a kind of amphibious aircraft wheel-retracting gear provided by the invention. The position caution device of this amphibious aircraft wheel-retracting gear may also include remote data concentrator 109 (configurable multiple), described remote data concentrator 109 is disposed adjacent to aircraft sensors source place by nearby principle, and various kinds of sensors data carry out the integrated treatments such as analog digital conversion; The electric input interface of described remote data concentrator and described landing modes select device 102, described engine control system 103, described radio altimeter 104, described wing flap to control system 105, described landing-gear system 106 cross-links, gather relevant state parameter or service data, the parameter collected or data by the electric output interface of described remote data concentrator, are sent to described flight alarm computer 101 after the integrated treatments such as relevant analog digital conversion. Introducing by this embodiment medium-long range data concentrator 109, can further realize the collection of different grades of organic electronic system signal, integrated treatment and concentration of transmissions, thus improving sharing of Mechatronic Systems/facility information, reduce the quantity of full machine wire, reduce the complexity of aircraft wiring, thus strengthening safety and the maintainability of whole aircraft system.
The present invention is directed to the feature of amphibious aircraft wheel-retracting gear, provide more complete position warning solution route, can effectively warn the flight unit amphibious aircraft abnormal landing form that wheel-retracting gear occurs when drop in water surface, two kinds of different landing modes of terrain landing, to take corresponding workaround timely, improve the safety of aircraft, there is bigger practical value.
The above is the preferred embodiment of the present invention; it should be pointed out 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 (5)
1. an amphibious aircraft wheel-retracting gear position caution device, it is characterized in that, its outside interconnected system includes: flight alarm computer, landing modes select device, engine control system, radio altimeter, wing flap control system, landing-gear system, can pressing type redness major alarm lamp, audio devices.
The electric input interface end of described flight alarm computer connects landing modes and selects device, engine control system, radio altimeter, wing flap to control system, landing-gear system;
The electric output interface end of described flight alarm computer connects can pressing type redness major alarm lamp, audio devices;
The described landing modes that described flight alarm computer warns logical judgment flow process that input interface place is collected according to the position of wheel-retracting gear selects the landing modes status information in device, throttle lever positional 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 integrated treatment, and send the warning instruction of corresponding light according to result, audio-alert information is to output interface, drive described can pressing type redness major alarm lamp, described audio devices, there is provided visual for flight unit, dual alert mode acoustically.
2. wheel-retracting gear position as claimed in claim 1 caution device, it is characterised in that described position caution device may also include remote data concentrator; Described remote data concentrator is disposed adjacent to aircraft sensors source place by nearby principle, and various kinds of sensors data carry out the integrated treatments such as analog digital conversion; The electric input interface of described remote data concentrator and described landing modes select device, described engine control system, described radio altimeter, described wing flap to control system, the crosslinking of described landing-gear system, gather relevant state parameter or service data, the parameter collected or data by the electric output interface of described remote data concentrator, are sent to described flight alarm computer after the integrated treatments such as relevant analog digital conversion.
3. wheel-retracting gear position as claimed in claim 1 caution device, it is characterized in that, described flight alarm COMPUTER DETECTION arrives: described landing modes selects neutral manner signal in device effective, and described engine control system exists the effective described radio altimeter data simultaneously of one or several throttle lever slow train position position signallings lower than 800 feet, or wing flap landing position position signalling is effective in described wing flap control system, then send corresponding instruction/data by electric output interface, trigger described can pressing type redness major alarm lamp and described audio devices to provide light to warn and audible warning sound. warning caused by the described slow parking space state of engine control system throttle lever and described radio altimeter data can be passed through can be inhibited by pressing type redness major alarm lamp described in pressing, it is suppressed that after warning restarted when again reducing arbitrary throttle to position, slow train position subsequently. the warning controlled caused by the state of system wing flap landing position by described wing flap does not allow to arrange any artificial braking measure.
4. wheel-retracting gear position as claimed in claim 1 caution device, it is characterized in that, described flight alarm COMPUTER DETECTION arrives: described landing modes selects terrain landing mode signal in device effective, in described landing-gear system, gear down position signalling is effective, and described engine control system exists the effective described radio altimeter data simultaneously of one or several throttle lever slow train position position signallings lower than 800 feet, or wing flap landing position position signalling is effective in described wing flap control system, then send corresponding instruction/data by electric output interface, trigger described can pressing type redness major alarm lamp and described audio devices to provide light to warn and audible warning sound. warning caused by the described slow parking space state of engine control system throttle lever and described radio altimeter data can be passed through can be inhibited by pressing type redness major alarm lamp described in pressing, it is suppressed that after warning restarted when again reducing arbitrary throttle to position, slow train position subsequently. the warning controlled caused by the state of system wing flap landing position by described wing flap does not allow to arrange any artificial braking measure.
5. wheel-retracting gear position as claimed in claim 1 caution device, it is characterized in that, described flight alarm COMPUTER DETECTION arrives: described landing modes selects water landing mode signal in device effective, in described landing-gear system, undercarriage stowage position signalling is effective, and described engine control system exists the effective described radio altimeter data simultaneously of one or several throttle lever slow train position position signallings lower than 800 feet, or wing flap landing position position signalling is effective in described wing flap control system, then send corresponding instruction/data by electric output interface, trigger described can pressing type redness major alarm lamp and described audio devices to provide light to warn and audible warning sound. warning caused by the described slow parking space state of engine control system throttle lever and described radio altimeter data can be passed through can be inhibited by pressing type redness major alarm lamp described in pressing, it is suppressed that after warning restarted when again reducing arbitrary throttle to position, slow train position subsequently. the warning controlled caused by the state of system wing flap landing position by described wing flap does not allow to arrange any artificial braking measure.
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| CN109733626A (en) * | 2018-11-12 | 2019-05-10 | 中航通飞研究院有限公司 | A kind of alarm of amphibious aircraft hatch door and instruction system |
| CN110824470A (en) * | 2019-10-12 | 2020-02-21 | 中航通飞研究院有限公司 | Radio altitude data processing method of amphibious aircraft |
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| CN111324117B (en) * | 2020-01-20 | 2021-01-08 | 郑州宇通重工有限公司 | Login auxiliary control method and system for special vehicle and computer storage medium |
| CN112623271A (en) * | 2020-12-25 | 2021-04-09 | 中电科芜湖钻石飞机制造有限公司 | General airplane comprehensive control console test equipment |
| CN112623271B (en) * | 2020-12-25 | 2023-08-18 | 中电科芜湖钻石飞机制造有限公司 | Test equipment for comprehensive control console of general aircraft |
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Effective date of registration: 20201204 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. |