WO2010127562A2 - Aéronef à cabine d'éjection - Google Patents

Aéronef à cabine d'éjection Download PDF

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Publication number
WO2010127562A2
WO2010127562A2 PCT/CN2010/000948 CN2010000948W WO2010127562A2 WO 2010127562 A2 WO2010127562 A2 WO 2010127562A2 CN 2010000948 W CN2010000948 W CN 2010000948W WO 2010127562 A2 WO2010127562 A2 WO 2010127562A2
Authority
WO
WIPO (PCT)
Prior art keywords
cabin
escaping
aircraft according
aircraft
passenger
Prior art date
Application number
PCT/CN2010/000948
Other languages
English (en)
Chinese (zh)
Other versions
WO2010127562A3 (fr
Inventor
高恒伟
Original Assignee
Gao Hengwei
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Gao Hengwei filed Critical Gao Hengwei
Publication of WO2010127562A2 publication Critical patent/WO2010127562A2/fr
Publication of WO2010127562A3 publication Critical patent/WO2010127562A3/fr

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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
    • B64D25/12—Ejectable capsules

Definitions

  • the present invention is a new type of safety aircraft with an escape system for a passenger aircraft.
  • the present invention will provide an effective engineering path for people to completely eliminate the above-mentioned shadows without being psychologically comforted but actual reality of the facility - from the time the passenger boarded the plane to the acceleration of the runway to the flight of the route to the landing of the aircraft, until the aircraft The passengers leave the aircraft and provide a safe escape from the aircraft.
  • the cabin and cockpit of the passenger and all crew members are designed to be emergency separated from all other parts of the aircraft (rear fuselage, fuel tank and fuel, luggage compartment and luggage, main landing gear, main wing, tail and engine)
  • the independent SJ front fuselage (referred to as the escapeable cabin in this article), and the specific escape path for the separation is designed in advance - that is, the detonation separation is performed on the separation surface to which the explosion bolts are connected (to ensure successful separation,
  • Two parallel separation surfaces can be arranged in parallel, and the force transmission structure between the two separation surfaces can be connected with the rear fuselage by a wire capable of breaking force, so that separation is achieved on both separation surfaces.
  • start fast electric fuze start - no full thrust time is less than 1/10 second
  • the escape rocket solid rocket
  • the propulsion section is about 1 ⁇ 2 seconds
  • the habitual flight is about 1 ⁇ 3 seconds.
  • the deceleration landing is immediately turned on. After the deceleration parachute is fully deployed, the front landing gear is opened and the escaped landing main bracket of the rear end face is set as the "scaffold structure buffer landing". Sense -: T God, we are finally no longer restless for the safety of flying!
  • the wing can be designed as a "forward swept-back" shape, see IS 2, or intercept the front end of the main wing as a post-stabilized aerodynamic surface of the escape cabin, such as Sound design example, see Figure 3.
  • Bolting bolts Modern explosive bolts can perform almost complete simultaneous detonation in hundreds of tens of thousands or even tens of thousands of bolts in a time period of only 1/1000 seconds under the condition of ensuring the strength of the original metal materials.
  • 3 ⁇ 4 body rocket The modern solid rocket can reach more than 200 seconds, with less charge, large thrust and quick start. The time from ignition to full thrust is only about 1/100 second, and the actual structural weight of the arrow made of high-quality steel can even be less than 1/10 of the total weight. In particular, the fuel can be stored stably for a long time at room temperature. Non-polluting safety.
  • the parachute made of modern fiber material has a very light weight.
  • the actual diameter of the canopy is only about 20 m, and the umbrella is included in the tether.
  • the total volume of a general suitcase 80cmX 60cmX 30cm
  • the aircraft has a total length of 60m, a wingspan of 46.7 meters, a wing root chord length of 11.6m, and a wing tip length of ⁇ 3m (total main wing area: 260m 2 ).
  • Outer diameter of the fuselage diameter 4m, maximum take-off weight 165T, escapeable cabin length 24m, cockpit length 4m, front single-storey luxury cabin length: 8m (50 seats), rear double-deck economy cabin length: 12 meters (150 seats) .
  • the middle section of the fuselage is the fuel tank: outer diameter 4m, length ⁇ 14m, volume ⁇ 130 cubic meters.
  • the tail section of the fuselage is the luggage compartment, the maximum diameter of the front end is ⁇ 4m, the total length of the luggage compartment is 9m, and the total volume of the luggage compartment is ⁇ 30 cubic meters.
  • Passenger including carry-on baggage
  • 20T 200 people per person weighs ⁇ 100kg
  • Double hair under the main wing
  • single thrust 23T (push to weight ratio: 10)
  • total thrust 46T control $U mode (- flight control from the cockpit to the rear fuselage):
  • Full power Transmission servo control double cable (single cable can work) at the separation surface can be self-test detachable connection port.
  • Easy cabin cockpit and passenger compartment
  • Attitude control The head of the escapeable cabin has a small attitude-controlled small rocket set (high-pressure gas cylinder "rocket") that is automatically activated in the initial stage of emergency escape and escape.
  • a small attitude-controlled small rocket set high-pressure gas cylinder "rocket"
  • the middle part of the rear end of the escapeable passenger cabin is provided with a stable umbrella of diameter ⁇ ⁇ 3 ⁇ which can be ejected about 2 seconds after separation.
  • Main Umbrella There is a front deceleration main umbrella (1 set) above the front part of the escapeable cabin (the cockpit and passenger compartment connection surface). Two main umbrellas of the same specification and purpose are provided above the rear end of the escaped passenger cabin.
  • the above three main umbrellas each have a diameter of ⁇ 20m and a single weight of "100kg.
  • the three main umbrellas can slow down the landing speed of the escapeable cabin to ⁇ 10m/s.
  • the rear end of the escapeable cabin is provided with a main emergency landing buffer bracket (two) and a pneumatic stability panel (3) that are quickly opened about 1 second after emergency separation - see Figure 6, except for the upper part
  • a main emergency landing buffer bracket two
  • a pneumatic stability panel (3) that are quickly opened about 1 second after emergency separation - see Figure 6, except for the upper part
  • the two lower stabilizing panels are attached to the emergency landing buffer bracket.
  • the front landing gear of the original machine is provided in the lower middle of the front end of the escapeable passenger cabin.
  • the landing gear is opened after the main parachute is fully deployed in the case of emergency separation, and is used for the final landing of the emergency landing buffer bracket with the rear end. buffer.

Landscapes

  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Emergency Lowering Means (AREA)
  • Body Structure For Vehicles (AREA)

Abstract

L'invention concerne un aéronef à cabine d'éjection qui est un nouveau type d'aéronef dont la partie avant (la cabine d'éjection comprenant la cabine des passagers et le compartiment du pilote) est indépendante et la seule partie dans laquelle les passagers embarquent. En cas d'accident, la cabine d'éjection peut se séparer de toutes les autres parties de l'aéronef et s'éloigner du danger par propulsion par fusée vers le haut, puis ouvrir un parachute pour freiner l'atterrissage. L'ensemble des occupants de l'aéronef peut ainsi avoir la vie sauve. Le procédé de l'invention peut être utilisé pendant toute la durée du vol, du décollage à l'atterrissage.
PCT/CN2010/000948 2010-04-26 2010-06-25 Aéronef à cabine d'éjection WO2010127562A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201010156926.1 2010-04-26
CN2010101569261A CN101927829A (zh) 2010-04-26 2010-04-26 客舱可逃逸飞机

Publications (2)

Publication Number Publication Date
WO2010127562A2 true WO2010127562A2 (fr) 2010-11-11
WO2010127562A3 WO2010127562A3 (fr) 2011-04-07

Family

ID=43050534

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2010/000948 WO2010127562A2 (fr) 2010-04-26 2010-06-25 Aéronef à cabine d'éjection

Country Status (2)

Country Link
CN (1) CN101927829A (fr)
WO (1) WO2010127562A2 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101927829A (zh) * 2010-04-26 2010-12-29 高恒伟 客舱可逃逸飞机
CN105424061B (zh) * 2015-12-12 2019-10-01 航宇救生装备有限公司 圆周阵列式火箭橇气动减速板
CN106828938A (zh) * 2017-02-16 2017-06-13 佛山市三水区希望火炬教育科技有限公司 一种专用于运送海军陆战队员的军用大飞机救生装置
CN111284712A (zh) * 2020-03-03 2020-06-16 黄思源 一种客机失事后挽救乘员生命的方法
CN113955127B (zh) * 2021-10-20 2023-06-30 襄阳宏伟航空器有限责任公司 一种飞机整体逃逸救生舱
CN118004453A (zh) * 2024-01-31 2024-05-10 北京穿越者载人航天科技有限公司 一种基于降落伞的载人飞船可重复使用逃逸系统

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10206306A1 (de) * 2002-02-12 2003-08-21 Dieter Lampart Rettungskabine für vom Flugzeugabsturz bedrohte Insassen
DE10254417A1 (de) * 2002-11-21 2004-06-09 Alois Rausch Rausch Air Safety Traffic System
CN1194882C (zh) * 2000-03-31 2005-03-30 帕夫罗斯·吉安纳科普罗斯 具有可分离式乘客逃离舱的飞机
CN101148198A (zh) * 2007-10-31 2008-03-26 翁文辉 民航客机内客舱弹射出机外的避险空降逃生方法
CN201132611Y (zh) * 2007-12-12 2008-10-15 曹刚 航空飞机脱险舱
CN101927829A (zh) * 2010-04-26 2010-12-29 高恒伟 客舱可逃逸飞机

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1194882C (zh) * 2000-03-31 2005-03-30 帕夫罗斯·吉安纳科普罗斯 具有可分离式乘客逃离舱的飞机
DE10206306A1 (de) * 2002-02-12 2003-08-21 Dieter Lampart Rettungskabine für vom Flugzeugabsturz bedrohte Insassen
DE10254417A1 (de) * 2002-11-21 2004-06-09 Alois Rausch Rausch Air Safety Traffic System
CN101148198A (zh) * 2007-10-31 2008-03-26 翁文辉 民航客机内客舱弹射出机外的避险空降逃生方法
CN201132611Y (zh) * 2007-12-12 2008-10-15 曹刚 航空飞机脱险舱
CN101927829A (zh) * 2010-04-26 2010-12-29 高恒伟 客舱可逃逸飞机

Also Published As

Publication number Publication date
CN101927829A (zh) 2010-12-29
WO2010127562A3 (fr) 2011-04-07

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