WO2009039787A1 - Aéronef doté d'un système de sauvetage - Google Patents

Aéronef doté d'un système de sauvetage Download PDF

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Publication number
WO2009039787A1
WO2009039787A1 PCT/CN2008/072448 CN2008072448W WO2009039787A1 WO 2009039787 A1 WO2009039787 A1 WO 2009039787A1 CN 2008072448 W CN2008072448 W CN 2008072448W WO 2009039787 A1 WO2009039787 A1 WO 2009039787A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuselage
tail
aircraft
parachute
wing
Prior art date
Application number
PCT/CN2008/072448
Other languages
English (en)
Chinese (zh)
Inventor
Dequan Lin
Original Assignee
Dequan Lin
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 Dequan Lin filed Critical Dequan Lin
Publication of WO2009039787A1 publication Critical patent/WO2009039787A1/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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/006—Safety devices

Definitions

  • the present invention relates to an aircraft, and more particularly to a safety rescue aircraft, which belongs to the field of aircraft design.
  • the technical problem to be solved by the present invention is to overcome the deficiencies in the prior art, and to design a simple, advanced, practical, economical and reliable, suitable for all large, medium and small aircraft, including fixed wings.
  • large and medium-sized aircraft cabins use at least two layers of channel-shaped floors.
  • the seats can be placed horizontally or vertically.
  • the emergency rescue system will be started, and the wings, tails and fronts will be abandoned.
  • the landing gear, the parachute and the airbag are opened, and the outer airbag of the rotor helicopter fuselage is fired, so that the fuselage can be smoothly and safely landed or stopped.
  • the fixed-wing aircraft can be abandoned or the front landing gear and the tail can be discarded.
  • the tail is not discarded during the ground taxiing; the rotor helicopter abandons the tail
  • tail system It is characterized by an early warning device, an emergency rescue button, a signal transmission line, an explosion bolt for fixing the tail and the fuselage, an umbrella cabin at the tail of the tail, an explosion bolt for the tail control link, and a cable cutter.
  • the rotorcraft engine is mounted on the top of the fuselage and integrated into the tail, and the fuel tank is installed at the tail. If the aircraft abandons the tail during the ground taxiing, the fuselage hinders the tail from sliding forward, and there is a risk that the tail will crash, so the aircraft does not abandon the tail during the ground taxiing.
  • the fixed-wing aircraft of the present invention can either discard the tail or discard the tail; the rotor helicopter discards the tail.
  • Airframe system It is characterized by an early warning device, an emergency rescue button, a signal transmission line, a cockpit, a passenger cabin, a battery, a top cabin of the fuselage, a bottom of the fuselage and a lower airbag compartment on both sides, and the outer part of the rotor helicopter There is a rocket.
  • a plurality of sealed boxes are arranged on the fuselage bulkhead, and the connecting rods or cables and electrical cable lines are passed through the sealed box; the rear door of the fuselage is connected to the tail compartment.
  • the present invention also uses at least two channel-shaped floors for large and medium-sized aircraft cabins in order to reduce cost and reduce fuel consumption and save operating costs.
  • the warning device is connected to the emergency rescue button and installed in the cockpit And connected to the rocket through a signal transmission line.
  • At least one top and at least one layer of parachute are installed according to the size of the aircraft.
  • the parachute is opened from the back to the front to buffer the pulling force of the plane when the parachute is opened.
  • the 1 square meter area parachute can carry 20 kilograms of weight.
  • the Chinese Shenzhou spacecraft has a parachute area of 1,200 square meters and weighs 90 kilograms, which can carry 24 tons of weight.
  • each cutter cuts off the cable line leading to the wing and the nose landing gear. Then the wing and the nose gear are abandoned.
  • the parachute is quickly opened.
  • the parachute is opened more than two times from the back to the front.
  • the generated resistance is evenly distributed through the umbrella ropes fixed on the rings of different parts of the fuselage.
  • the body is stable and slow down.
  • the fuselage is stably and slowly stopped under the action of the parachute and the airbag, thus achieving the purpose of safety and lifesaving, and effectively ensuring the safety of the occupants and the fuselage.
  • the mechanical control system of the invention is a helicopter helicopter.
  • an early warning device installed in the cockpit alarms, the driver verifies and judges the danger. If the air crash is about to occur, the driver presses the air rescue button to start the emergency rescue.
  • the signal is transmitted through the signal transmission line and controls the explosion bolts leading to the tail of the tail and its operating link, the explosion of the explosion-proof bolts on the bottom of the fuselage and the lower part of the airbag cover, and the cover is opened instantaneously to inflate the airbag, and the airbag has sufficient strength. After it is inflated at high altitude, it will not break.
  • Figure 3 is a longitudinal sectional view of the parachute cabin of the present invention.
  • Figure 4 is a cross-sectional view of a two-story passenger cabin of the present invention.
  • the rocket of the cabin (8) is launched.
  • the fly-by-wire aircraft of the present invention is a warning device installed in the cockpit (10) when it is distressed on the ground.
  • the alarm the driver verifies and judges the danger. If the air crash is about to occur, the driver presses the ground rescue button (2) to activate the emergency rescue system.
  • the signal is transmitted and controlled via the signal transmission line (3) for fixing the wing (4).

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Mechanical Engineering (AREA)
  • Emergency Lowering Means (AREA)

Abstract

La présente invention concerne un système de sauvetage qui peut être adapté pour un aéronef à voilure fixe et un giravion. Dans le cas d'un aéronef de taille grande ou moyenne, deux planchers en forme de canaux au moins sont prévus. Lorsque l'aéronef est en danger, celui-ci peut déclencher des boulons explosifs (13) au niveau des ailes (4), de l'empennage (6) et du train d'atterrissage avant afin de couper les liens d'actionnement et les fils électriques qui les rattachent, ce qui permet de se débarrasser de l'empennage, du train d'atterrissage et des ailes comportant les moteurs, les réservoirs et le train d'atterrissage arrière. Au même moment, les parachutes (20) installés sur la partie supérieure du fuselage et de l'empennage sont ouverts et les airbags présents sur la partie inférieure du fuselage sont gonflés. Le fuselage peut donc atterrir en douceur et de manière stable à l'aide des parachutes et des airbags, et la sécurité des passagers et du fuselage est garantie avec efficacité.
PCT/CN2008/072448 2007-09-21 2008-09-22 Aéronef doté d'un système de sauvetage WO2009039787A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CNA2007101545299A CN101391654A (zh) 2007-09-21 2007-09-21 安全救生飞机
CN200710154529.9 2007-09-21

Publications (1)

Publication Number Publication Date
WO2009039787A1 true WO2009039787A1 (fr) 2009-04-02

Family

ID=40492205

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2008/072448 WO2009039787A1 (fr) 2007-09-21 2008-09-22 Aéronef doté d'un système de sauvetage

Country Status (2)

Country Link
CN (1) CN101391654A (fr)
WO (1) WO2009039787A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102431645A (zh) * 2011-12-06 2012-05-02 李新民 一种防坠毁单人直升机
CN112722288A (zh) * 2019-10-29 2021-04-30 上海浦东临港智慧城市发展中心 一种安全降落飞机

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101811576A (zh) * 2010-04-30 2010-08-25 赵军 可应急解决飞机空难的飞机及应急处理方法
CN103112590B (zh) * 2011-11-16 2015-09-23 宋学恭 一种安全降落飞机
CN102514714B (zh) * 2011-12-29 2016-09-28 青岛宏百川金属精密制品有限公司 降低旋翼无人直升机失控危害的装置与方法
CN103538725B (zh) * 2012-07-16 2016-04-27 中国人民解放军军械工程学院 直升机应急逃生***
CN103204127A (zh) * 2013-03-21 2013-07-17 李彦征 安全防护运输工具
CN104309808A (zh) * 2014-09-25 2015-01-28 安徽科耀智能科技有限公司 一种无人机安全碰撞装置
EP3674218A4 (fr) * 2017-08-24 2021-05-26 Nippon Kayaku Kabushiki Kaisha Dispositif de sécurité d'engin volant et engin volant
CN107985597A (zh) * 2017-11-03 2018-05-04 西北工业大学 一种具有模块化货舱的货运无人机
CN113650810B (zh) * 2018-08-13 2023-06-09 蓝箭航天空间科技股份有限公司 航天运载器舱段堵盖、舱段结构和航天运载器
CN111377048B (zh) * 2018-12-29 2023-06-02 西安谷禾航空科技有限公司 一种逃生座舱盖结构及座舱盖分离螺栓抛放方法
CN110758748B (zh) * 2019-11-15 2020-12-22 吉林大学 一种直升机及弹射逃生缓冲装置
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
WO2022095335A1 (fr) * 2020-11-05 2022-05-12 北星空间信息技术研究院(南京)有限公司 Algorithme de priorité reposant sur un véhicule aérien sans pilote à rotors multiples pour accessoires pouvant être largués

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4699336A (en) * 1986-05-08 1987-10-13 Peter Diamond Airplane safety body passenger compartment
US5356097A (en) * 1993-05-10 1994-10-18 Stefan Chalupa Segmented safety aircraft
US5568903A (en) * 1995-01-18 1996-10-29 Pena; Jesus S. Plane saddle for a safety airplane
CN2491331Y (zh) * 2001-04-18 2002-05-15 吕广治 分体式客机
CN2564472Y (zh) * 2002-08-26 2003-08-06 赵小荣 一种机舱可与机体分离的飞机
CN1450969A (zh) * 2000-03-31 2003-10-22 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和具有气袋的飞机
CN1709767A (zh) * 2005-05-31 2005-12-21 徐丽岗 一种分体式客机及其逃生装置

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4699336A (en) * 1986-05-08 1987-10-13 Peter Diamond Airplane safety body passenger compartment
US5356097A (en) * 1993-05-10 1994-10-18 Stefan Chalupa Segmented safety aircraft
US5568903A (en) * 1995-01-18 1996-10-29 Pena; Jesus S. Plane saddle for a safety airplane
CN1450969A (zh) * 2000-03-31 2003-10-22 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和具有气袋的飞机
CN2491331Y (zh) * 2001-04-18 2002-05-15 吕广治 分体式客机
CN2564472Y (zh) * 2002-08-26 2003-08-06 赵小荣 一种机舱可与机体分离的飞机
CN1709767A (zh) * 2005-05-31 2005-12-21 徐丽岗 一种分体式客机及其逃生装置

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102431645A (zh) * 2011-12-06 2012-05-02 李新民 一种防坠毁单人直升机
CN112722288A (zh) * 2019-10-29 2021-04-30 上海浦东临港智慧城市发展中心 一种安全降落飞机
CN112722288B (zh) * 2019-10-29 2024-02-09 上海浦东临港智慧城市发展中心 一种安全降落飞机

Also Published As

Publication number Publication date
CN101391654A (zh) 2009-03-25

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