CN109436345A - A kind of Aircraft Air emergency escape channel and emergency escape method - Google Patents
A kind of Aircraft Air emergency escape channel and emergency escape method Download PDFInfo
- Publication number
- CN109436345A CN109436345A CN201811500063.8A CN201811500063A CN109436345A CN 109436345 A CN109436345 A CN 109436345A CN 201811500063 A CN201811500063 A CN 201811500063A CN 109436345 A CN109436345 A CN 109436345A
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- Prior art keywords
- disembarking
- channel
- door
- aircraft
- control unit
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- 238000000034 method Methods 0.000 title claims abstract description 8
- 238000004880 explosion Methods 0.000 claims description 3
- 238000012360 testing method Methods 0.000 description 11
- 210000002105 tongue Anatomy 0.000 description 4
- 208000027418 Wounds and injury Diseases 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 208000014674 injury Diseases 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000006837 decompression Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009191 jumping Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
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
- B64D25/08—Ejecting or escaping means
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- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Emergency Lowering Means (AREA)
Abstract
A kind of Aircraft Air emergency escape channel and emergency escape method, the channel of disembarking is located under the floor of aircraft, by the control for control unit of disembarking, disembarking on the outside of channel is aircraft skin, disembarking on the inside of channel is airplane floor structure, primacord is laid on the inside of the aircraft skin on the outside of channel of disembarking, the skin areas that the primacord surrounds is greater than passway of disembarking, the primacord is connect with control unit of disembarking, the airplane floor disembarked on the inside of channel is a door, the door is connect with a pressurized strut, the pressurized strut is fixed on the airframe for passage proximate of disembarking, the pressurized strut is connect with control unit of disembarking, the door is linked together by a uplock with airplane floor, the uplock is connect with control unit of disembarking, there are one down locks in channel of disembarking, the down lock open door can be fixed on from In machine channel.
Description
Technical field
The application belongs to airplane design technical field, specifically a kind of Aircraft Air emergency escape channel and emergency escape side
Method.
Background technique
During aircraft development, flight test is that the process of product testing is carried out under the conditions of live flying.Flight examination
Content complexity is tested, sortie of taking a flight test is more, and a possibility that accident occurs is big, especially execution high risk subject, such as envelope curve extension, quivers
Vibration, stall etc. are required according to the 35th clause of CCAR-21-R3, it is necessary to consider and demonstration aircraft of taking a flight test has taken enough measure guarantees
Therefore flight crew personnel's personal safety must have enough safety precautions taking a flight test on aircraft, guarantee that aircraft occurs not
The safe escape of pilot in the case where controllable.
Aerial emergency escape be aircraft it is inoperable or i.e. will be out of control when the required measure taken, once implementation is answered in the air
It suddenly disembarks, it is meant that abandon aircraft, guarantee personnel safety.The probability of aerial emergency escape is very small, it is often the case that is trying
Fly that dedicated aerial emergency escape channel is arranged on aircraft, it is carried out after taking a flight test to remove and restore aircraft to prototype
State.
Current Normal practice both domestic and external be in the aerial emergency escape hatch door in individually designed one of airframe lower part of taking a flight test,
Hatch door is opened to inferoanterior by hydraulic actuator actuation, hatch door and is maintained at open position, and channel surrounding volume is all closed,
The channel is usually located in aircraft anallobar, therefore the hatch door is the airtight hatch door for being typically designed to non-blocking type.
The major advantage of the prior art is: hatch door can block incoming flow after opening and blow, and avoid injury to personnel, guarantee personnel
The safety withdrawn.
The major defect of the prior art is:
1) emergency escape hatch door be non-blocking type the airtight hatch door of external-open, complex structural designs, weight is big, reliability compared with
It is low；
2) this kind of hatch door usually has the structure of prominent fuselage skin when closed, has a fixing to aircraft aerodynamic characteristic
It rings；
3) emergency escape channel is usually located under floor, and one lid of setting or hatch door are still needed on floor, is increased logical
The time that road is opened；
4) airframe lower part emergency escape hatch door is difficult to restore to aircraft normal configuration state after taking a flight test, and influencing should
The sale of airplane.
Summary of the invention
The application be designed to provide it is a kind of for the Aircraft Flight Test stage for escape aerial emergency escape channel and
Emergency escape method
A kind of Aircraft Air emergency escape channel, which is located under the floor of aircraft, by control unit of disembarking
Control, which is characterized in that be aircraft skin on the outside of channel of disembarking, be airplane floor structure on the inside of channel of disembarking, disembarking
Primacord is laid on the inside of aircraft skin on the outside of channel, the skin areas which surrounds is greater than passway of disembarking, this leads quick-fried
Rope is connect with control unit of disembarking, and the airplane floor on the inside of channel of disembarking is a door, the door and a pressurized strut
Connection, the pressurized strut are fixed on the airframe for passage proximate of disembarking, which connect with control unit of disembarking, the door knot
Structure is linked together by a uplock with airplane floor, which connect with control unit of disembarking, in channel of disembarking also
There is a down lock, which can be fixed on open door and disembark in channel.
When emergency escape, pilot starts the discharge valve of aircraft by the control button for control unit of disembarking first, puts down
Pressure difference inside and outside weighing apparatus aircraft；Under conditions of permissible pressure, control unit of disembarking starts primacord, and the outside in channel of disembarking is covered
Skin explosion removal, while control unit control uplock unlock of disembarking, control pressurized strut drive door to open, door is being beaten
Another side wall in channel of disembarking is constituted under open state, and door and down lock are fixed, and is formed inside and outside connection aircraft and is escaped
Raw channel.
The beneficial effects of the present application are as follows 1) lower turning type door prominent fuselage when opening, blocks incoming flow, guarantees
Personnel safety is disembarked；2) less to the change of prototype main structure, a non-hermetically sealed door is only provided on floor, simultaneously
Primacord is installed on covering.3) pilot operator is simple, if you need to in-flight egress, it is only necessary to press the control in control unit
Button, control unit control discharge valve, primacord and pressurized strut according to aircraft inside and outside differential pressure respectively, to realize emergency
It disembarks the unlatching in channel, provides grace time for in-flight egress；4) after taking a flight test can fast quick-recovery to prototype state, it is only necessary to
The components such as primacord, pressurized strut, side wall are removed, door is replaced with floor.
Attached drawing is described in further detail the application with reference to embodiments.
Detailed description of the invention
Fig. 1 is Aircraft Air emergency escape channel design schematic diagram
Fig. 2 is Aircraft Air emergency escape channel closed state side view
Fig. 3 is Aircraft Air emergency escape channel opening state side view
Fig. 4 is down lock composition figure
Explanation is numbered in figure: 1 disembarks under control unit, 2 pressure sensors, 3 discharge valve, 4 doors, 5 uplocks, 6
Position lock, 7 primacords, 8 pressurized struts, 9 hinges, 10 side walls, 11 control buttons, 12 shells, 13 reset springs, 14 lock tongues, 15 coverings,
16 floor panel structures.
Specific embodiment
Referring to attached drawing, the Aircraft Air emergency escape channel of the application, which is located under the floor of aircraft, disembarks
It is aircraft skin 15 on the outside of channel, is airplane floor 16 on the inside of channel of disembarking, the aircraft skin 15 on the outside of channel of disembarking
Primacord 7 is laid in inside, and the skin areas which surrounds is greater than passway of disembarking, the primacord 7 and control unit of disembarking
1 connects, and the airplane floor on the inside of channel of disembarking is a door 4, and door 4 is connected to airplane floor by hinge 9 on one side
On 16, which connect with a pressurized strut 8, which is fixed on the airframe for passage proximate of disembarking,
The pressurized strut 8 is connect with control unit 1 of disembarking, which is linked together by a uplock 5 with airplane floor 16, on this
Position lock 5 is connect with control unit 1 of disembarking, and there are one down locks 6 in channel of disembarking, which can be by open door knot
Structure 4, which is fixed on, disembarks in channel.
As shown in Figure 1, channel of disembarking is a rectangular channel, three of them side wall 10 is fixed smooth siding, above-mentioned
Door 4 constitutes another side wall in channel of disembarking in the on-state.
As shown in Fig. 2, the length of door 4 is greater than the depth in channel of disembarking, so that door is in the on-state
Covering under prominent fuselage, blocks aircraft flow to realize, guarantees the safety that personnel disembark.
As shown in Figure 1, control unit 1 of disembarking can acquire the signal of pressure sensor 2, and pass through inner control logic control
The discharge valve 3 of aircraft processed, primacord 7, uplock 5, actuator 8 working condition.Discharge valve 3 is mainly used to discharge aircraft
Internal pressure, so that balance airplane inside and outside differential pressure, avoids decompression rate is excessive from causing injury to personnel.
As shown in Fig. 2, under normal circumstances, door 4 is locked on airplane floor by uplock 5, upper surface and aircraft
Floor flushes, and uses as airplane floor, and pressurized strut at this time 8 is in elongation state, and discharge valve 3 is in close state.
When emergency escape, pilot presses the control button 11 disembarked in control unit, and control unit of disembarking 1 is according to pressure
The information collected of sensor 2 judges that (P0 is held according to human body during aircraft emergency pressure relief to aircraft inside and outside differential pressure △ P and P0
By ability determine) relationship.As aircraft inside and outside differential pressure △ P≤P0, control unit of disembarking 1 directly controls the work of primacord 7,
By forming opening on Cut blasting fuselage skin；As cabin inside and outside differential pressure △ P > P0, control unit controls releasing for aircraft first
Pressure valve is opened to reducing aircraft inside and outside differential pressure, when aircraft inside and outside differential pressure reaches predetermined range, when △ P≤P0, disembarks
The control unit control work of primacord 7 removes outer skin explosion, is open to be formed in fuselage；Then it disembarks control unit
1 control uplock 5 unlocks, while controlling the contraction of actuator 8, so that final position is opened and be locked in door 4, forms connection
Escape route inside and outside aircraft；Pilot by sequence of disembarking, successively from aerial emergency escape channel, disembark by parachute jumping.
Shell 12, lock tongue 14 and the reset spring 13 that the down lock contains, shell 12 are fixed on channel side wall of disembarking
Suitable position on, the side of door is equipped with card slot corresponding with the lock tongue 14 of down lock, and door is when opening, down lock
Lock tongue door can be locked by the card slot, form a side wall of escape route.
After taking a flight test, by primacord 7, pressurized strut 8, channel side wall 10, uplock 5, down lock 6, control unit of disembarking 1
It removes, door 4 is replaced with airplane floor.
Claims (4)
1. a kind of Aircraft Air emergency escape channel, which is located under the floor of aircraft, by the control for control unit of disembarking
System, which is characterized in that it is aircraft skin on the outside of channel of disembarking, is airplane floor structure on the inside of channel of disembarking, it is logical disembarking
Primacord is laid on the inside of aircraft skin on the outside of road, the skin areas which surrounds is greater than passway of disembarking, the primacord
Control unit is connect with disembarking, and the airplane floor on the inside of channel of disembarking is a door, and the door and a pressurized strut connect
It connects, which is fixed on the airframe for passage proximate of disembarking, which connect with control unit of disembarking, the door
It is linked together by a uplock with airplane floor, which connect with control unit of disembarking, in channel of disembarking also
Open door can be fixed on and disembark in channel by one down lock, the down lock.
2. Aircraft Air emergency escape as described in claim 1 channel, which is characterized in that the channel of disembarking is a square
Shape channel, three of them side wall are fixed smooth siding, and above-mentioned door constitutes the another of channel of disembarking in the on-state
A side wall.
3. Aircraft Air emergency escape as described in claim 1 channel, which is characterized in that the length of the door be greater than from
The depth in machine channel.
4. a kind of Aircraft Air emergency escape method, it is characterised in that: 1) there is the channel of disembarking being located under airplane floor, by
The control for control unit of disembarking is aircraft skin on the outside of the channel of disembarking, is airplane floor structure on the inside of channel of disembarking,
Primacord is laid on the inside of the aircraft skin disembarked on the outside of channel, the skin areas which surrounds is greater than passway of disembarking, should
Primacord is connect with control unit of disembarking, and the airplane floor on the inside of channel of disembarking is a door, the door and a work
Dynamic cylinder connection, the pressurized strut are fixed on the airframe for passage proximate of disembarking, which connect with control unit of disembarking, should
Door is linked together by a uplock with airplane floor, which connect with control unit of disembarking, in channel of disembarking
Open door can be fixed on and disembark in channel by down lock there are one interior, the down lock；2) when emergency escape, pilot
Start the discharge valve of aircraft, the pressure difference inside and outside balance airplane first by the control button for control unit of disembarking；3) allowing
Under conditions of pressure difference, control unit of disembarking starts primacord, the outer skin explosion in channel of disembarking is removed, while control of disembarking
Unit controls uplock unlock, and control pressurized strut drives door to open, and door constitutes channel of disembarking in the on-state
Another side wall, and door and down lock are fixed, form the escape route inside and outside connection aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811500063.8A CN109436345A (en) | 2018-12-07 | 2018-12-07 | A kind of Aircraft Air emergency escape channel and emergency escape method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811500063.8A CN109436345A (en) | 2018-12-07 | 2018-12-07 | A kind of Aircraft Air emergency escape channel and emergency escape method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109436345A true CN109436345A (en) | 2019-03-08 |
Family
ID=65557986
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811500063.8A Pending CN109436345A (en) | 2018-12-07 | 2018-12-07 | A kind of Aircraft Air emergency escape channel and emergency escape method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109436345A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113006440A (en) * | 2021-02-26 | 2021-06-22 | 中建二局第一建筑工程有限公司 | Portable quick installation operation platform of assembled steel construction frame component |
| CN113335535A (en) * | 2020-03-02 | 2021-09-03 | 中航西飞民用飞机有限责任公司 | Airplane air emergency parachute jumping slideway system and lifesaving method |
| CN114486320A (en) * | 2022-04-15 | 2022-05-13 | 中国飞机强度研究所 | Emergency processing system and method for pressure imbalance for aircraft testing |
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|---|---|---|---|---|
| GB609229A (en) * | 1942-09-05 | 1948-09-28 | Roger Aime Robert | Improvements in or relating to aircraft |
| US3331571A (en) * | 1964-04-22 | 1967-07-18 | British Aircraft Corp Ltd | Emergency exit arrangements in aircraft |
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| RU1816722C (en) * | 1972-12-08 | 1993-05-23 | Ю.В.Баландин | Shaft escape system of a flying vehicle having a pressure cabin |
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| CN105217013A (en) * | 2014-06-27 | 2016-01-06 | 空中客车运营简化股份公司 | There is the aircraft being furnished with internal security hatch of two open controller |
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2018
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|---|---|---|---|---|
| GB609229A (en) * | 1942-09-05 | 1948-09-28 | Roger Aime Robert | Improvements in or relating to aircraft |
| US3331571A (en) * | 1964-04-22 | 1967-07-18 | British Aircraft Corp Ltd | Emergency exit arrangements in aircraft |
| US3454245A (en) * | 1967-03-08 | 1969-07-08 | Explosive Tech | Emergency egress system for vehicle |
| RU1816722C (en) * | 1972-12-08 | 1993-05-23 | Ю.В.Баландин | Shaft escape system of a flying vehicle having a pressure cabin |
| US20020162916A1 (en) * | 2001-05-02 | 2002-11-07 | Jerome Baderspach | Fast evacuation device for aircraft |
| CN101481012A (en) * | 2009-02-16 | 2009-07-15 | 中国人民解放军理工大学工程兵工程学院 | Safeguard structure of passenger plane service module for exploding and cutting covering during aerial emergency pressure relief |
| CN105217013A (en) * | 2014-06-27 | 2016-01-06 | 空中客车运营简化股份公司 | There is the aircraft being furnished with internal security hatch of two open controller |
| CN105857566A (en) * | 2015-02-11 | 2016-08-17 | 空中客车运营简化股份公司 | Airplane flight deck equipped with an emergency escape |
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| Title |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113335535A (en) * | 2020-03-02 | 2021-09-03 | 中航西飞民用飞机有限责任公司 | Airplane air emergency parachute jumping slideway system and lifesaving method |
| CN113006440A (en) * | 2021-02-26 | 2021-06-22 | 中建二局第一建筑工程有限公司 | Portable quick installation operation platform of assembled steel construction frame component |
| CN114486320A (en) * | 2022-04-15 | 2022-05-13 | 中国飞机强度研究所 | Emergency processing system and method for pressure imbalance for aircraft testing |
| CN114486320B (en) * | 2022-04-15 | 2022-06-24 | 中国飞机强度研究所 | Emergency processing system and processing method for pressure imbalance for aircraft testing |
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Application publication date: 20190308 |