CN202400290U - Plane distress separate cabin escape device - Google Patents
Plane distress separate cabin escape device Download PDFInfo
- Publication number
- CN202400290U CN202400290U CN2011203920799U CN201120392079U CN202400290U CN 202400290 U CN202400290 U CN 202400290U CN 2011203920799 U CN2011203920799 U CN 2011203920799U CN 201120392079 U CN201120392079 U CN 201120392079U CN 202400290 U CN202400290 U CN 202400290U
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- cabin
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- plane
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Abstract
The utility model relates to a plane distress separate cabin escape device which consists of an escape door, a separate cabin, a slideway, an electric lifting bulge, a hydraulic arm device, a plane control room, an electric cabin door, a plane body, a pneumatic ejection device, a rotating shaft and a door latch. The escape door is in rotating connection with the plane body; a separate cabin is positioned inside the plane body; the slideway is fixedly connected with the plane body; an ejection type parachute is in movable connection with the top of the separate cabin; the pneumatic ejection device is arranged on the side surface of the interior of the plane body; the hydraulic arm device is arranged inside the plane body; and an inflatable air cushion is fixedly connected with the separate cabin. The plane distress separate cabin escape device mainly solves the problems of difficulty in escape caused by low escape fficeincy and large escape difficulty confronted in the air escape. The plane distress separate cabin escape device has the advantages of novel concept, reasonable structure, quick reaction, safety, reliability and strong practicability and can be suitable for the escape on various plane models.
Description
Technical field:
Escape device technical field under the utility model relates in particular to a kind of aircraft distress separation type cabin escape device.
Background technology:
Known, along with being showing improvement or progress day by day of science and technology, it is more and more convenient that people's trip also becomes.As the long-term travel instrument, aircraft becomes only selection naturally, but because the danger of high-altitude flight and uncertain makes the hedging ability of aircraft and the ability of emergency escape all receive great restriction.
For example, on June 1st, 2009, Air France one built on stilts objective A330 passenger plane is from Rio de Daneiro, BRA flies to the Paris, FRA way, in the overhead crash of Atlantic Oceanic Region.Have 216 passengers and 12 crews on the passenger plane, comprising 9 Chinese passengers.228 people are all wrecked on the machine, cast an Air France the most heavy in history airplane crash in 75 years.
Can aircraft distress be escaped? Does aircraft escape receive the restriction of those factors again? At first it requires the people and the crew of escape promptly to make a response, thereby is preferably preparation fully of escape; It receives the constraint of survival equipment again on the other hand, is not that everyone can both skillfully use for the escape device as the parachute, so can bring certain difficulty to escape virtually; The success or not of A Man Escaped also receives environmental constraints, and should there be different escape modes in different landing sites, for example ocean and land, and we are with regard to can not be same so!
Summary of the invention:
To the deficiency of above-mentioned existence, the utility model proposes the way of solution.Its technical scheme is: a kind of aircraft distress separation type of the utility model cabin escape device; Mainly form by emergency exits, separation type cabin, slideway, electric up-down projection, hydraulic arm device, aircraft control cabin, electronic hatch door, fuselage, pneumatic catapult-launching gear, turning cylinder, knocker; Said separation type cabin comprises ejection type parachute, mechanical interface, gas filled device, free wheel flutter, inflatable air cushion, distress light, wireless installation, electronic sealing hatch door, shock absorption device, and said slideway comprises longitudinal slipway, sideslipway, slideway infall.Said emergency exits and fuselage are and are rotationally connected; Said separation type cabin is positioned at fuselage interior; Said slideway is with fuselage captives joint, and the top in said ejection type parachute and separation type cabin is movably connected, and said pneumatic catapult-launching gear is arranged on the fuselage interior side; Said hydraulic arm device is arranged on fuselage interior, and said inflatable air cushion is with the separation type cabin captives joint.
The technical scheme of the utility model is to realize ground like this:
The aircraft cockpit of a kind of aircraft distress separation type of the utility model cabin escape device adopts multistage cabin separate design; During the aircraft encounter dangerous situation; The passenger and crew can the emergency escape original position focus on inside the separation types at different levels cabin of fuselage interior; And carry out separating controlling by the in-to-in control setup of crew through the separation type cabin, and handle master cock and realize manually slipping away cabin ...
Scheme 1: the pattern of laterally escaping.The step of control: 1, with being connected adjacent separation type cabin and separating, simultaneously the electronic sealing hatch door of both sides, separation type cabin is closed with mechanical interface between the aircraft control cabin, make the separation type cabin be in an osed top state; 2; Control setting is upwards opened at the electronic hatch door of tail; And control simultaneously is positioned at electric up-down projection that final section separation type cabin afterbody is used for fixing the separation type cabin and removes fixingly, makes the separation type cabin partly to carry out side travel at the sideslipway of slideway; 3; The hydraulic arm device that control is positioned at plane nose part promotes first segment separation type cabin in order; Thereby make separation types at different levels cabin move to tail; Because aircraft still is in state of flight, so according to the relative motion principle in the physical knowledge, the separation type cabin can be by the effect of relative motion and part thrust skidding off from the outlet of the electronic hatch door unlatching of tail step by step.
Scheme 2: the pattern of vertically escaping.The step of control: 1; With being connected adjacent separation type cabin and separating with mechanical interface between the aircraft control cabin; Simultaneously the electronic sealing hatch door of both sides, separation type cabin is closed, make the separation type cabin be in an osed top state, 2; Regulate the free wheel flutter of bottom, separation type cabin slideway infall, make it in longitudinal slipway, to move; 3; Start pneumatic catapult-launching gear, pneumatic catapult-launching gear can produce enough big moment thrust, makes that the separation type cabin can side travel and rush open knocker; And making emergency exits to open around turning cylinder, the separation type cabin just can skid off through the emergency exits of opening.But because the wing on the fuselage, so have only the cooresponding separation type of the safety door of wing both sides cabin vertically to escape, so we need focus on the personnel on the machine this several cabins.
After the separation type cabin is left, thus the change that the separation type cabin can be through the monitoring acceleration/accel opening the ejection type parachute and starting gas filled device inflatable air cushion is put on the air voluntarily.Just can slow down under the double action of ejection type parachute and inflatable air cushion in the separation type cabin.
The difference of environment according to landing: 1, when dropping to the land, inflatable air cushion and the shock absorption device of bottom, separation type cabin just can carry out buffer protection, and when the generation of landing is overturn, and the shock absorption device of separation type nacelle top also can the while participation protective; 2, in the time of on dropping to the water surface, the separation type cabin can utilize the inflatable air cushion of bottom to swim on the water surface.And being provided with distress light and wireless installation at the top in separation type cabin, the people in the cabin can utilize it to send an SOS and carry out distress call.
The beneficial effect of the utility model is:
The utlity model has novel, rational in infrastructure, handle simple, be swift in response, safe and reliable, practical, numerous advantages of using applicable to the escape of different types of machines.(the whole concept that has particularly adopted the separation type cabin to replace the integral type cabin to realize escaping with utilizing ejection system that the separation type cabin is implemented promptly to launch; And meanwhile unite again and adopted parachute, inflatable air cushion and damping interlayer multi-stage speed-reducing and shock absorption device to implement safety guard-safeguard in all directions, can reach the purpose that increases the escape chance of success so effectively.It is novel, practical, can be widely used in various airline carriers of passengerss and aircraft).
Description of drawings:
Below in conjunction with accompanying drawing and embodiment the utility model is further specified
Fig. 1: the position view that is the emergency exits of a kind of aircraft distress separation type of the utility model cabin escape device.
Fig. 2: the external structure scheme drawing that is a kind of aircraft distress separation type of the utility model cabin escape device.
Fig. 3: the scheme drawing that is the side sectional view of a kind of aircraft distress separation type of the utility model cabin escape device.
Fig. 4: the side schematic three dimensional views that is a kind of aircraft distress separation type of the utility model cabin escape device slideway.
Fig. 5: the scheme drawing that is the birds-eye view of a kind of aircraft distress separation type of the utility model cabin escape device slideway.
Fig. 6: the scheme drawing that is the part sectional view before a kind of aircraft distress separation type of the utility model cabin escape device is laterally escaped.
Fig. 7: the scheme drawing that is the part sectional view of a kind of aircraft distress separation type of the utility model cabin escape device when laterally escaping.
Fig. 8: the preceding effect scheme drawing of vertical escape that is a kind of aircraft distress separation type of the utility model cabin escape device.
Fig. 9: the effect scheme drawing that is vertical when escape of a kind of aircraft distress separation type of the utility model cabin escape device.
Figure 10: be the scheme drawing after a kind of aircraft distress separation type of the utility model cabin escape device is opened fully.
Among the figure 1, emergency exits, 2 separation type cabins, 2 (1) ejection type parachutes, 2 (2) mechanical interfaces, 2 (3) gas filled devices; 2 (4) free wheel flutters, 2 (5) inflatable air cushions, 2 (6) distress lights, 2 (7) wireless installations, 2 (8) electronic sealing hatch doors, 2 (9) shock absorption devices; 3 slideways, 3 (1) longitudinal slipways, 3 (2) sideslipwaies, 3 (3) slideway infalls, 4 electric up-down projections, 5 hydraulic arm devices; 6 aircraft control cabins, 7 electronic hatch doors, 8 fuselages, 9 pneumatic catapult-launching gears, 10 turning cylinders, 11 knockers.
The specific embodiment:
In Fig. 1, emergency exits 1 evenly are arranged on the both sides of fuselage outer side wing.
In Fig. 2, ejection type parachute 2 (1) is arranged on the middle part at 2 tops, separation type cabin, around it, also is installed with a distress light 2 (6) and radio 2 (7) devices simultaneously.Gas filled device 2 (3) is arranged on separation type cabin 2 exterior lateral sides, and links to each other with the inflatable air cushion that is installed in 2 bottoms, separation type cabin 2 (5).Four free wheel flutters 2 (4) fixedly are assemblied in the bottom in separation type cabin 2, and mechanical interface 2 (2) is arranged on the transverse side in separation type cabin 2.
In Fig. 3; Damping interlayer 2 (9) is fixedly connected on 2 in-to-in top and bottom, separation type cabin; Electronic sealing hatch door 2 (8) is symmetric mode and is installed in the position that separation type cabin 2 in-to-in transverse sides link to each other with mechanical interface 2 (2), and slideway 3 is fixedly mounted on the bottom of fuselage inner face.In Fig. 4; Slideway 3 is to be processed by ganoid material, and slideway 3 adopts the groove type design, and slideway is divided into sideslipway 3 (2) and longitudinal slipway 3 (1); Sideslipway 3 (2) is mutual each other vertical with longitudinal slipway 3 (1), and the infall of slideway 3 can be to the conversion of free wheel flutter travel direction.
In Fig. 5, all horizontal the or vertical width with the separation type cabin is identical for 3 (1) width between width between each group sideslipway 3 (2) or longitudinal slipway.
In Fig. 6, the aircraft control cabin 6 that is positioned at head section links to each other through the mechanical interface 2 (2) in mechanical interface 2 (2) and separation type cabin 2, and it is continuous also to pass through cooresponding mechanical interface 2 (2) between the adjacent separation type cabin 2.Above aircraft control cabin 6, be provided with a hydraulic arm device 5, the end of hydraulic arm device 5 and first segment separation type cabin 2 are to pressing close to.Be provided with an electronic hatch door 7 at the tail end, be respectively arranged with an electric up-down projection 4 in the bottom in first segment and final section separation type cabin.
In Fig. 7, the mechanical interface 2 (2) on the aircraft control cabin and the mechanical interface 2 (2) in separation type cabin 2 separate, and cooresponding mechanical interface 2 (2) is separated from one another between the simultaneously adjacent separation type cabin 2.Hydraulic arm device 5 promotes 2 motions of separation type cabin, and the electronic hatch door 7 of tail is opened, and fuselage is left in separation type cabin 2 one by one.
In Fig. 8, emergency exits 1 link to each other with fuselage 8 through fixed installation turning cylinder 10 in the top, and knocker 11 is arranged on emergency exits 1 and fuselage 8 junctions.Set inside in fuselage 8 one sides has a pneumatic catapult-launching gear 9, and pneumatic catapult-launching gear 9 is pressed close to separation type cabin 2 mutually.
In Fig. 9, pneumatic catapult-launching gear 9 acts on the separation type cabin 2, and emergency exits knocker 11 is opened, and emergency exits 1 are opened certain angle around turning cylinder 10, and separation type cabin 2 skids off fuselage gradually.
In Figure 10, ejection type parachute 2 (1) umbrella covers fully open, inflatable air cushion 2 (5) bottom 2 expansions in the separation type cabin.
Claims (6)
1. aircraft distress separation type cabin escape device; Form by emergency exits, separation type cabin, slideway, electric up-down projection, hydraulic arm device, aircraft control cabin, electronic hatch door, fuselage, pneumatic catapult-launching gear, turning cylinder, knocker; It is characterized in that: said emergency exits and fuselage are and are rotationally connected, and said separation type cabin is positioned at fuselage interior.
2. a kind of aircraft distress separation type according to claim 1 cabin escape device, it is characterized in that: said slideway is with fuselage captives joint.
3. a kind of aircraft distress separation type according to claim 1 cabin escape device, it is characterized in that: the top in said ejection type parachute and separation type cabin is movably connected.
4. a kind of aircraft distress separation type according to claim 1 cabin escape device, it is characterized in that: said pneumatic catapult-launching gear is arranged on the fuselage interior side.
5. a kind of aircraft distress separation type according to claim 1 cabin escape device, it is characterized in that: said hydraulic arm device is arranged on fuselage interior.
6. a kind of aircraft distress separation type according to claim 1 cabin escape device is characterized in that: said inflatable air cushion is with the separation type cabin captives joint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203920799U CN202400290U (en) | 2011-10-14 | 2011-10-14 | Plane distress separate cabin escape device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203920799U CN202400290U (en) | 2011-10-14 | 2011-10-14 | Plane distress separate cabin escape device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202400290U true CN202400290U (en) | 2012-08-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011203920799U Expired - Fee Related CN202400290U (en) | 2011-10-14 | 2011-10-14 | Plane distress separate cabin escape device |
Country Status (1)
| Country | Link |
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| CN (1) | CN202400290U (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103085964A (en) * | 2013-02-27 | 2013-05-08 | 王愐荣 | Method for manufacturing safe passenger plane |
| CN104007451A (en) * | 2014-05-27 | 2014-08-27 | 曹宇 | Wrecking position recording reporting device |
| CN105292497A (en) * | 2015-10-28 | 2016-02-03 | 吴然 | Automatic escape seat for passenger planes |
| CN105292496A (en) * | 2015-11-19 | 2016-02-03 | 郑启凡 | Air disaster prevention and anti-hijacking safety system of large-scale aircraft |
| CN105947223A (en) * | 2016-05-05 | 2016-09-21 | 莫国斌 | Split airplane |
| CN106081126A (en) * | 2016-06-13 | 2016-11-09 | 王晨 | Bionical cellular active safety escape compartment embeds application and the design of aviation aircraft |
| CN106364678A (en) * | 2016-10-15 | 2017-02-01 | 荆门创佳机械科技有限公司 | Safe and fast separated airplane passenger compartment and transferring system |
| CN106828944A (en) * | 2017-02-06 | 2017-06-13 | 佛山市三水区希望火炬教育科技有限公司 | A kind of special automatic downhill type air bag system of helicopter pilot escape |
| CN106927053A (en) * | 2017-03-24 | 2017-07-07 | 蒋昊维 | Passenger plane high altitude escape system |
| WO2017181302A1 (en) * | 2016-04-21 | 2017-10-26 | 刘继军 | Modular, detachable ejection seat allowing aircraft passenger escape |
| RU2750340C1 (en) * | 2020-03-02 | 2021-06-28 | Андрей Анатольевич Саприн | High security aircraft |
-
2011
- 2011-10-14 CN CN2011203920799U patent/CN202400290U/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103085964A (en) * | 2013-02-27 | 2013-05-08 | 王愐荣 | Method for manufacturing safe passenger plane |
| CN104007451A (en) * | 2014-05-27 | 2014-08-27 | 曹宇 | Wrecking position recording reporting device |
| CN104007451B (en) * | 2014-05-27 | 2016-06-08 | 曹宇 | Wrecked position record report device |
| CN105292497A (en) * | 2015-10-28 | 2016-02-03 | 吴然 | Automatic escape seat for passenger planes |
| CN105292496A (en) * | 2015-11-19 | 2016-02-03 | 郑启凡 | Air disaster prevention and anti-hijacking safety system of large-scale aircraft |
| CN105292496B (en) * | 2015-11-19 | 2018-03-23 | 郑启凡 | A kind of anti-airplane crash Convention for the Suppression of Unlawful Seizure of Aircraft security system of airdreadnought |
| WO2017181302A1 (en) * | 2016-04-21 | 2017-10-26 | 刘继军 | Modular, detachable ejection seat allowing aircraft passenger escape |
| CN105947223A (en) * | 2016-05-05 | 2016-09-21 | 莫国斌 | Split airplane |
| CN106081126A (en) * | 2016-06-13 | 2016-11-09 | 王晨 | Bionical cellular active safety escape compartment embeds application and the design of aviation aircraft |
| CN106364678A (en) * | 2016-10-15 | 2017-02-01 | 荆门创佳机械科技有限公司 | Safe and fast separated airplane passenger compartment and transferring system |
| CN106364678B (en) * | 2016-10-15 | 2018-05-04 | 荆门创佳机械科技有限公司 | A kind of safe and efficient separate type birdman cabin and transporting system |
| CN106828944A (en) * | 2017-02-06 | 2017-06-13 | 佛山市三水区希望火炬教育科技有限公司 | A kind of special automatic downhill type air bag system of helicopter pilot escape |
| CN106927053A (en) * | 2017-03-24 | 2017-07-07 | 蒋昊维 | Passenger plane high altitude escape system |
| RU2750340C1 (en) * | 2020-03-02 | 2021-06-28 | Андрей Анатольевич Саприн | High security aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| DD01 | Delivery of document by public notice |
Addressee: Wang Xiaojin Document name: Notification to Pay the Fees |
|
| DD01 | Delivery of document by public notice |
Addressee: Wang Xiaojin Document name: Notification of Termination of Patent Right |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120829 Termination date: 20141014 |
|
| EXPY | Termination of patent right or utility model |