CN111056019B - Emergency evacuation signal system for airplane - Google Patents
Emergency evacuation signal system for airplane Download PDFInfo
- Publication number
- CN111056019B CN111056019B CN201911366911.5A CN201911366911A CN111056019B CN 111056019 B CN111056019 B CN 111056019B CN 201911366911 A CN201911366911 A CN 201911366911A CN 111056019 B CN111056019 B CN 111056019B
- Authority
- CN
- China
- Prior art keywords
- switch
- cockpit
- control panel
- lamp
- self
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000001681 protective effect Effects 0.000 claims abstract description 27
- 210000000056 organ Anatomy 0.000 claims description 2
- 230000006854 communication Effects 0.000 abstract description 9
- 230000006870 function Effects 0.000 description 9
- 238000000034 method Methods 0.000 description 6
- 229920001200 poly(ethylene-vinyl acetate) Polymers 0.000 description 6
- 230000009131 signaling function Effects 0.000 description 4
- 238000011112 process operation Methods 0.000 description 3
- 230000005236 sound signal Effects 0.000 description 3
- 238000013475 authorization Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000011664 signaling Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Audible And Visible Signals (AREA)
Abstract
The provided emergency evacuation signal system for the airplane comprises a cockpit control panel and a cockpit buzzer which are arranged in a cockpit of the airplane, a front cabin control panel arranged in a front cabin of the airplane and a rear cabin control panel arranged in a rear cabin of the airplane; a self-locking switch with a protective cover and a lamp, a two-gear rotary switch and a non-self-locking switch are arranged on the control panel of the cockpit; the cockpit buzzer comprises a cockpit buzzer which is arranged in the aircraft cockpit through a support; the front passenger cabin control panel is provided with a front protective cover light touch switch, a front signal indicator light and a front buzzer; and a rear belt lamp touch switch, a rear signal indicator lamp and a rear buzzer are arranged on the rear passenger cabin control panel. The system enables the flight unit and the crew service group to quickly complete information communication and issue emergency evacuation commands, greatly simplifies the communication flow between the flight unit and the crew service group when emergency evacuation is carried out, strives for precious time for evacuation of passengers in the passenger cabin under dangerous conditions, and is convenient to operate, simple in system structure and high in reliability.
Description
Technical Field
The invention belongs to the technical field of airplane avionics systems, and particularly relates to an airplane emergency evacuation signal system.
Background
The emergency evacuation signal system is a signal system which can simply and quickly carry out simple information communication between a flight unit and a crew unit and execute emergency evacuation deployment when an airplane needs to be evacuated in an emergency under a dangerous state, and can guide people on the airplane to evacuate from the airplane quickly and safely after the transportation airplane and the civil airplane are forced to land successfully.
Disclosure of Invention
The technical problems solved by the invention are as follows: the invention provides an emergency evacuation signal system for an airplane, which can enable a flight unit and a crew service unit to quickly complete information communication and issue an emergency evacuation command through simple and quick keys, switches, light and sound signals, greatly simplifies the communication process operation mode between the flight unit and the crew service unit when emergency evacuation needs to be executed, strives for precious time for evacuation of passengers in a passenger cabin under dangerous conditions, and has the advantages of convenience in operation, simple system structure, high reliability and the like.
The technical scheme adopted by the invention is as follows: the emergency evacuation signal system for the airplane comprises a cockpit control panel and a cockpit buzzer which are arranged in a cockpit of the airplane, a front passenger cabin control panel arranged in a front passenger cabin of the airplane and a rear passenger cabin control panel arranged in a rear passenger cabin of the airplane;
the cockpit control board is provided with a self-locking switch with a protective cover and a lamp, a two-gear rotary switch, a non-self-locking switch and an internal control circuit board; the cockpit buzzer comprises a cockpit buzzer which is arranged on the aircraft cockpit through a bracket;
the front passenger cabin control panel is provided with a front protective cover light touch switch, a front signal indicator light, a front buzzer and an internal control circuit board;
the rear passenger cabin control panel is provided with a rear belt lamp touch switch, a rear signal indicator lamp, a rear buzzer and an internal control circuit board;
the cockpit control board and the front cabin control board are connected through a cable I, trigger signals are provided between the cockpit control board and the front cabin control board, and the front cabin control board provides signal lamp driving signals for a key with a lamp on the cockpit control board;
the cockpit buzzer and the front cabin control panel are connected through a cable II, and the front cabin control panel provides a sound driving signal for the cockpit buzzer.
The front cabin control panel is connected with the rear cabin control panel through a cable III, and the front cabin control panel provides a trigger signal for the rear cabin control panel.
The technical scheme is further limited, the self-locking switch with the protective cover and the lamp is a four-pole double-throw self-locking switch, a self-locking switch signal indicator lamp and a self-locking switch protective cover are arranged on the self-locking switch with the protective cover and the lamp, the non-self-locking switch is a one-position non-self-locking switch, a non-self-locking switch signal indicator lamp is arranged on the non-self-locking switch, and an external connector is arranged on the side surface of an internal control circuit board of the control panel of the cockpit; and the outgoing lines of the self-locking switch with the protective cover and the lamp, the two-gear rotary switch and the non-self-locking switch are all connected with an internal control circuit board of the control panel of the cockpit.
Further inject above-mentioned technical scheme, preceding safety cover area lamp dabs and is equipped with preceding switch signal indicator I and front switch safety cover on the switch, preceding area lamp dabs and is equipped with preceding switch signal indicator II on the switch, take the safety cover area lamp to dabble switch, preceding area lamp dabs switch, preceding signal indicator and preceding bee calling organ's lead-out wire all is connected with the internal control circuit board of preceding main cabin control panel.
The technical scheme is further limited, a rear switch signal indicator lamp is arranged on the rear light touch switch, and lead-out wires of the rear light touch switch, the rear signal indicator lamp and the rear buzzer are all connected with an internal control circuit board of the rear passenger cabin control board.
Compared with the prior art, the invention has the advantages that:
the system can enable the flight unit and the crew service unit to quickly complete information communication and issue emergency evacuation commands through simple and quick keys, switches, light and sound signals, greatly simplifies the communication process operation mode between the flight unit and the crew service unit when emergency evacuation needs to be executed, and strives for precious time for evacuation of passengers in the passenger cabin under dangerous conditions.
Drawings
FIG. 1 is a schematic diagram of the system of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the present invention, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation. The use of the phrase "comprising" does not exclude the presence of other identical elements in the process, method, article, or apparatus that comprises the same element.
Referring to fig. 1, for the embodiment of the present invention,
example 1: the emergency evacuation signal system for an airplane, as shown in fig. 1, includes a cockpit control panel 10 and a cockpit buzzer 40 disposed in a cockpit of the airplane, a front cabin control panel 20 disposed in a front cabin of the airplane, and a rear cabin control panel 30 disposed in a rear cabin of the airplane.
The cockpit control board 10 is provided with a self-locking switch 11 with a protective cover and a lamp, a two-gear rotary switch 13, a non-self-locking switch 14 and an internal control circuit board; the cockpit buzzer 40 comprises a cockpit buzzer 41 mounted on the cockpit of the airplane through a bracket;
the front passenger cabin control panel 20 is provided with a front protective cover light touch switch 21, a front light touch switch 25, a front signal indicator lamp 23, a front buzzer 24 and an internal control circuit board;
the rear passenger cabin control panel 30 is provided with a rear light-touch switch 33, a rear signal indicator lamp 31, a rear buzzer 32 and an internal control circuit board;
the cockpit control board 10 and the front cabin control board 20 are connected through a cable I51, trigger signals are provided between the cockpit control board 10 and the front cabin control board 20, and the front cabin control board 20 provides signal lamp driving signals for keys with lamps on the cockpit control board 10;
the cockpit buzzer 40 is connected with the front cabin control panel 20 through a cable II 52, and the front cabin control panel 20 provides a sound driving signal for the cockpit buzzer 40.
The front cabin control board 20 and the back cabin control board 30 are connected through a cable III 53, and the front cabin control board 20 provides a trigger signal for the back cabin control board 30.
The main functions of the emergency evacuation signal system in this embodiment are as follows:
the flight unit issues an emergency evacuation signal function: the flight unit directly issues emergency evacuation signals through the cockpit control panel 10.
The emergency evacuation signal issuing function of the crew member: emergency evacuation signaling may be performed by the crew member through the forward cabin control panel 20 in the event of flight crew authorization.
The emergency evacuation signal function is applied and issued by the crew member: when the flight crew is not authorized, the crew department can request the emergency evacuation signal to be issued through the front cabin control panel 20, and at the moment, the pilot lamp on the light switch of the cockpit control panel 10 and the cockpit buzzer 40 can respond to the request signal of the crew department operating the front cabin control panel 20 to prompt the flight crew to authorize or issue the emergency evacuation signal.
Signal lamp instruction function: when the emergency evacuation signal is issued, the on-off indicator lamp on the cockpit control panel 10, the signal indicator lamp on the front cabin control panel 20, and the signal indicator lamp on the rear cabin control panel 30 may flash an alarm indication.
Example 2: an emergency evacuation signal system for an aircraft, as shown in fig. 1, includes a cockpit control panel 10 and a cockpit buzzer 40 disposed in a cockpit of the aircraft, a front cabin control panel 20 disposed in a front cabin of the aircraft, and a rear cabin control panel 30 disposed in a rear cabin of the aircraft.
The cockpit control board 10 is installed at the top of an aircraft cockpit or in a central control area of the cockpit, and a self-locking switch 11 with a protective cover and a lamp, a two-gear rotary switch 13, a non-self-locking switch 14 and an internal control circuit board are arranged on the cockpit control board 10;
the self-locking switch 11 with the protective cover and the lamp is a four-pole double-throw self-locking switch, namely a COMMAND switch is adopted, the self-locking switch 11 with the protective cover and the lamp is provided with a self-locking switch signal indicator lamp 15, a switch body is printed with COMMAND characters, and the switch is provided with a self-locking switch protective cover 12 for preventing false triggering;
the two-gear rotary switch 13 adopts a CAPT rotary switch, the indication position on the switch is printed with CAPT and PURS characters, the lower indication position is printed with CAPT characters, and the switch is a two-position self-locking switch.
The non-self-locking switch 14 is a one-position non-self-locking switch, namely a HORNOFF switch is adopted, the switch body is printed with HORNOFF characters, and a non-self-locking switch signal indicator lamp 16 is arranged on the non-self-locking switch 14.
The side surface of the internal control circuit board of the cockpit control board 10 is provided with an external connector; the outgoing lines of the self-locking switch with the protective cover and the lamp 11, the two-gear rotary switch 13 and the non-self-locking switch 14 are all connected with the internal control circuit board of the cockpit control board 10. The flight unit can conveniently touch the switch on the panel of the cockpit control panel 10 to operate, and can clearly identify the indicator light signal on the self-locking switch with the light.
The cockpit buzzer 40 comprises a cockpit buzzer 41, wherein the cockpit buzzer 41 is mounted at the top of the aircraft cockpit through a support and provides a sound alarm signal for the flight unit.
The front passenger cabin control panel 20 is installed on a front passenger cabin wall plate of an airplane, and a front protective cover with a light touch switch 21, a front light touch switch 25, a front signal indicator light 23, a front buzzer 24 and an internal control circuit board are arranged on the front passenger cabin control panel 20;
the light touch switch 21 with the lamp of the front protective cover adopts a COMMAND switch, the light touch switch 21 with the lamp of the front protective cover is provided with a front switch signal indicator lamp I26, the switch body is printed with COMMAND characters, the switch is a light touch switch, and the front switch protective cover 22 for preventing false triggering is added on the switch;
the front signal indicator lamp 23 adopts an EVAC indicator lamp, the EVAC indicator lamp is printed with EVAC characters, and the color of the indicator lamp is red;
a schematic arc line for representing the buzzer is printed around the sound outlet of the front buzzer 24;
the front light touch switch 25 adopts a HORNOFF switch, a front switch signal indicator light II 27 is arranged on the front light touch switch 25, the switch body is printed with HORNOFF characters, and the switch is a touch switch.
The outgoing lines of the light-touch switch 21 with the protective cover and the front light-touch switch 25, the front signal indicator light 23 and the front buzzer 24 are all connected with the internal control circuit board of the front passenger cabin control board 20. The light touch switch control function with the protective cover, the light touch switch 21 and the front light touch switch 25 is realized by an internal circuit of a control panel, the switch realizes that the state is turned once when logic is pressed once, and the state of the corresponding indicator light on the switch is also turned along with the turning. The front crew member of the aircraft cabin can conveniently touch the switches on the panel of the front cabin control panel 20 for operation, and can clearly identify the indicator light signals and the sound alarm signals on the panel.
The rear cabin control panel 30 is mounted on a rear cabin wall plate of the airplane, and a rear light-touch switch 33, a rear signal indicator lamp 31, a rear buzzer 32 and an internal control circuit board are arranged on the rear cabin control panel 30;
the rear light-carrying tact switch 33 is a HORNOFF switch, a rear switch signal indicator light 34 is arranged on the rear light-carrying tact switch 33, the switch body is printed with HORNOFF characters, and the switch is a tact switch.
The rear signal indicator lamp 31 adopts an EVAC indicator lamp, the EVAC indicator lamp is printed with EVAC characters, and the color of the indicator lamp is red;
a schematic arc line for representing the buzzer is printed around the sound outlet of the rear buzzer 32;
the outgoing lines of the rear light tact switch 33, the rear signal indicator light 31 and the rear buzzer 32 are all connected with the internal control circuit board of the rear passenger cabin control board 30. The touch switch control function of the rear belt light touch switch 33 is realized by an internal circuit of the control panel, the state is turned once when the switch realization logic is pressed once, and the state of the corresponding rear switch signal indicator light 34 on the switch is also turned over along with the state. The rear crew member of the aircraft cabin can conveniently touch the switches on the panel of the rear cabin control panel 30 for operation, and can clearly identify the indicator light signals and the sound alarm signals on the panel.
The specific connection relation among all the components of the emergency evacuation signal system is as follows:
the cockpit control panel 10 and the front cabin control panel 20 are connected through a cable I51, a COMMAND switch, a CAPT rotary switch and a HORNOFF switch on the cockpit control panel 10 provide trigger signals for the cockpit control panel 20, and the front cabin control panel 20 provides driving signals for a COMMAND switch indicator lamp on the cockpit control panel 10;
the cockpit buzzer 40 is connected with the front cabin control panel 20 through a cable II 52, and the front cabin control panel 20 provides a sound driving signal for the cockpit buzzer 410.
The front cabin control board 20 and the rear cabin control board 30 are connected through a cable III 53, and the front cabin control board 20 provides a trigger signal for the rear cabin control board 30.
The main functions of the emergency evacuation signal system are as follows:
the aircraft unit issues an emergency evacuation signal function: the flight crew can directly issue emergency evacuation signals by pressing the COMMAND switch on cockpit control panel 10.
The emergency evacuation signal issuing function of the crew member: in the case of flight crew authorization, i.e., with the cockpit CAPT rotary switch in the "CAPT & PURS" position, the crew may issue emergency evacuation signals by pressing the COMMAND switch on the forward cabin control panel 20.
The emergency evacuation signal function is applied and issued by the crew member: when the flight crew is not authorized, namely when the captain rotary switch of the cockpit is located at the captain position, the crew member can apply for issuing the emergency evacuation signal by pressing the COMMAND switch on the front cabin control board 20, and at the moment, the indicator lamp on the COMMAND switch of the cockpit and the cockpit buzzer can respond to the application signal of the crew member for operating the front cabin control board 20, so as to prompt the flight crew to authorize or issue the emergency evacuation signal.
Signal lamp instruction function: when the emergency evacuation signal is issued, the indicator lights of the COMMAND switch on the cockpit panel 10, the signal indicator lights on the front cabin panel 20 and the signal indicator lights on the rear cabin panel flash an alarm indication.
Buzzer sound alarm function: when the emergency evacuation signal is issued, the cockpit buzzer 41, the front buzzer 24 on the front cabin control panel 20, and the rear buzzer 32 on the rear cabin control panel 30 perform continuous acoustic alarms, and the acoustic alarms may be muted by the HORNOFF switches on the respective zone control panels.
The system can enable the flight unit and the crew service unit to quickly complete information communication and issue emergency evacuation commands through simple and quick keys, switches, light and sound signals, greatly simplifies the communication process operation mode between the flight unit and the crew service unit when emergency evacuation needs to be executed, strives for precious time for evacuation of passengers in the passenger cabin under dangerous conditions, and has the advantages of convenience in operation, simple system structure, high reliability and the like. The emergency evacuation signal realized by the system meets the aviation standard and airworthiness standard, and can be widely applied to civil airliners.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (3)
1. Emergent signal system that withdraws of aircraft, its characterized in that: the device comprises a cockpit control panel (10) and a cockpit buzzer (40) which are arranged in a cockpit of the airplane, a front cabin control panel (20) which is arranged in a front cabin of the airplane, and a rear cabin control panel (30) which is arranged in a rear cabin of the airplane;
the cockpit control panel (10) is provided with a self-locking switch (11) with a protective cover and a lamp, a two-gear rotary switch (13), a non-self-locking switch (14) and an internal control circuit board; the cockpit buzzer device (40) comprises a cockpit buzzer (41) which is arranged on the cockpit of the airplane through a bracket;
the front passenger cabin control panel (20) is provided with a front protective cover light touch switch (21), a front light touch switch (25), a front signal indicator lamp (23), a front buzzer (24) and an internal control circuit board;
the rear passenger cabin control panel (30) is provided with a rear light-carrying light touch switch (33), a rear signal indicator lamp (31), a rear buzzer (32) and an internal control circuit board;
the cockpit control board (10) is connected with the front cabin control board (20) through a cable I (51), trigger signals are provided between the cockpit control board (10) and the front cabin control board (20), and the front cabin control board (20) provides signal lamp driving signals for a key with a lamp on the cockpit control board (10);
the cockpit buzzer (40) is connected with the front cabin control panel (20) through a cable II (52), and the front cabin control panel (20) provides a sound driving signal for the cockpit buzzer (40);
the front cabin control board (20) and the rear cabin control board (30) are connected through a cable III (53), and the front cabin control board (20) provides a trigger signal for the rear cabin control board (30);
the self-locking switch (11) with the protective cover and the lamp is a four-pole double-throw self-locking switch, a self-locking switch signal indicator lamp (15) and a self-locking switch protective cover (12) are arranged on the self-locking switch (11) with the protective cover and the lamp, the non-self-locking switch (14) is a one-position non-self-locking switch, a non-self-locking switch signal indicator lamp (16) is arranged on the non-self-locking switch (14), and an external connector is arranged on the side face of an internal control circuit board of the cockpit control board (10); outgoing lines of the self-locking switch (11) with the protective cover and the lamp, the two-gear rotary switch (13) and the non-self-locking switch (14) are connected with an internal control circuit board of the control panel (10) of the cockpit.
2. An aircraft emergency evacuation signal system as claimed in claim 1, wherein: preceding area safety cover takes the lamp to dabber on switch (21) and is equipped with preceding switch signal indicator I (26) and preceding switch safety cover (22), preceding area lamp dabs and is equipped with preceding switch signal indicator II (27) on switch (25), take the safety cover to take the lamp to dabber switch (21), preceding area lamp dabs switch (25), preceding lead-out wire of preceding signal indicator (23) and preceding bee calling organ (24) all is connected with the internal control circuit board of preceding main cabin control panel (20).
3. An aircraft emergency evacuation signal system as claimed in claim 1, wherein: and a rear switch signal indicator lamp (34) is arranged on the rear light tact switch (33), and outgoing lines of the rear light tact switch (33), the rear signal indicator lamp (31) and the rear buzzer (32) are all connected with an internal control circuit board of the rear passenger cabin control board (30).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911366911.5A CN111056019B (en) | 2019-12-26 | 2019-12-26 | Emergency evacuation signal system for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911366911.5A CN111056019B (en) | 2019-12-26 | 2019-12-26 | Emergency evacuation signal system for airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111056019A CN111056019A (en) | 2020-04-24 |
| CN111056019B true CN111056019B (en) | 2022-08-19 |
Family
ID=70303954
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911366911.5A Active CN111056019B (en) | 2019-12-26 | 2019-12-26 | Emergency evacuation signal system for airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111056019B (en) |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10148499A1 (en) * | 2001-10-01 | 2003-04-17 | Hans-Dieter Grosmann | Electronic flight companion system for improving flight safety and security sends an emergency signal like a taxi emergency signal from the cockpit/flight deck crew. |
| US6980104B2 (en) * | 2002-01-29 | 2005-12-27 | Capitol Electronics, Inc. | Aircraft with security alarm system |
| GB2448864B (en) * | 2007-04-14 | 2009-08-12 | Saf T Glo Ltd | Aircraft security |
| CN202226060U (en) * | 2010-12-31 | 2012-05-23 | 中国飞行试验研究院 | Emergency escape device for airplane |
| US8774795B2 (en) * | 2011-05-20 | 2014-07-08 | Honeywell International Inc. | Reconfigurable satcom avionics radio |
| CN204204142U (en) * | 2014-11-17 | 2015-03-11 | 华侨大学 | Passenger vehicle detection early warning system |
| CN106707974A (en) * | 2015-07-19 | 2017-05-24 | 张学 | Distributed aircraft cabin simulator control system |
| CN105205385B (en) * | 2015-09-09 | 2018-07-03 | 中国银行股份有限公司 | A kind of business operation authorization method and system |
| CN106255043B (en) * | 2016-09-06 | 2019-05-28 | 西北工业大学 | Passenger plane emergency evacuation guides system |
| CN207089128U (en) * | 2017-07-27 | 2018-03-13 | 黄傲飞 | Alarm is withdrawn in the fire fighting truck scene of a fire |
| CN109586784B (en) * | 2018-12-27 | 2021-05-04 | 中电科航空电子有限公司 | Airborne routing implementation method based on multi-security-level data transmission |
-
2019
- 2019-12-26 CN CN201911366911.5A patent/CN111056019B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN111056019A (en) | 2020-04-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9789970B2 (en) | System and method for prevention of inadvertent escape slide deployment for an aircraft | |
| US9799186B2 (en) | Thermal event detection and notification system | |
| EP2803573B1 (en) | Passenger interface units and assemblies | |
| US10002538B2 (en) | Aircraft clearance enforcement | |
| US6845302B2 (en) | Airliner irreversible-control anti-hijack system | |
| US20100302074A1 (en) | Method and a device for detecting a thrust dissymmetry of an aircraft during landing | |
| WO1981001796A1 (en) | Method and system for aircraft fire protection | |
| EP2049205B1 (en) | An assembly comprising a storage box for a respiratory mask to be worn by crewmembers of an aircraft | |
| CA1083686A (en) | Parking guidance system for aircraft | |
| US10822088B2 (en) | Unified passenger service unit (PSU) control | |
| US6980104B2 (en) | Aircraft with security alarm system | |
| CN111056019B (en) | Emergency evacuation signal system for airplane | |
| US9981738B2 (en) | Parking brake control system for an aircraft | |
| CN106184783A (en) | A kind of audible alarm control system | |
| CN105730455A (en) | Automobile anti-collision control system and control method thereof | |
| US3237894A (en) | Apparatus for the prevention of the explosion of fuel tanks | |
| KR101887803B1 (en) | The collision prevention system using emergency lights of car | |
| CN109071029B (en) | Convertible display device for displaying emergency slide activation status in an aircraft | |
| GB2183582A (en) | Aircraft security method and apparatus | |
| RU2359868C2 (en) | Airplane with system of general-airplane equipment control | |
| CN211874182U (en) | Central control door lock system of luggage compartment of civil aircraft | |
| FR2457525A3 (en) | Protective alarm device for use by taxi driver - comprises roof-mounted flashing light operated by concealed switch to raise alarm in case of assault | |
| US20150274279A1 (en) | Method and system for control input detection | |
| US3820064A (en) | Aircraft collision avoidance system | |
| Linkous | Master Minimum Equipment List (MMEL) |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |