WO2010018561A1 - Hélicoptère à siège éjectable - Google Patents

Hélicoptère à siège éjectable Download PDF

Info

Publication number
WO2010018561A1
WO2010018561A1 PCT/IL2008/001117 IL2008001117W WO2010018561A1 WO 2010018561 A1 WO2010018561 A1 WO 2010018561A1 IL 2008001117 W IL2008001117 W IL 2008001117W WO 2010018561 A1 WO2010018561 A1 WO 2010018561A1
Authority
WO
WIPO (PCT)
Prior art keywords
helicopter
cockpit
ejection
rotors
ejection seat
Prior art date
Application number
PCT/IL2008/001117
Other languages
English (en)
Inventor
Chibbi Naaman
Ron Ben Itshak
Original Assignee
Chibbi Naaman
Ron Ben Itshak
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 Chibbi Naaman, Ron Ben Itshak filed Critical Chibbi Naaman
Priority to PCT/IL2008/001117 priority Critical patent/WO2010018561A1/fr
Publication of WO2010018561A1 publication Critical patent/WO2010018561A1/fr

Links

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
    • B64D25/10—Ejector seats
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/006—Safety devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft

Definitions

  • the present invention relates generally to the design of a helicopter to incorporate ejection seats for the flight crew, and more specifically wherein a typical upward ejection seat is used.
  • Typical helicopters are lifted and propelled by one or more horizontal rotors positioned above the body of the helicopter. This constitutes a problem in using a typical ejection seat, since typical ejection seats are generally extracted upward, and could collide with the rotor.
  • a typical ejection seat is generally propelled out of the aircraft by an explosive charge or rocket motor with the person occupying the seat. The ejection seat is ejected upward clearing the aircraft and then deploys a parachute, so that the user may land safely.
  • a zero-zero ejection seat is designed to extract its occupant upward and land him/her safely even from the ground (e.g. zero altitude) and from a stationary position (e.g. zero airspeed), for example if the pilot needs to bail out before the plane managed to take off.
  • Older ejection systems operated in two stages. First the canopy above the person is opened and then the seat is ejected. In newer models, such as employed in many US fighter planes (e.g. A-IO, F- 15 and F- 16), the canopy and seat are ejected in a single action to increase ejection speed.
  • US patent No. 3,926,388 to Johnson et al. dated December 16, 1975 discloses a mechanism for sequentially ejecting helicopter blades in a predetermined direction during a single rotor revolution to permit personnel ejection. This however can be quite dangerous to nearby vehicles and might delay ejection until the blades are out of the way. Sometimes a fraction of a second can make the difference between life and death.
  • US Patent No. 3,222,015 to Larsen et al. dated December 7, 1965 discloses lateral escaping means from a helicopter. This method requires a clear area around the helicopter and/or that the helicopter be positioned at a high enough altitude.
  • An aspect of an embodiment of the invention relates to a helicopter with a standard ejection seat that ejects the user upward from the cockpit.
  • the cockpit of the helicopter is located beyond the span of the rotors of the helicopter so that the ejection seat will no collide with it.
  • the cockpit is positioned in the vicinity of the antitorque means of the helicopter away from the span of the rotors, for example within a meter of the antitorque means from any side.
  • the cockpit may be positioned closer to the motor and further away from the antitorque means as long as it is beyond the span of the rotors.
  • the flight crew sits in ejection seats in the cockpit and in case of emergency they are ejected upward clearing the span of the rotor.
  • the ejection seat can be activated at any altitude and at any airspeed just like an ejection seat of an airplane.
  • the cockpit is facing away from the body of the helicopter, so that forward motion for the flight crew would be considered reverse motion for an observer comparing the flight of the helicopter with a standard helicopter, for example Bell 206.
  • the flight crew may face the body of the helicopter and use electronic viewing equipment to view areas blocked by the body of the helicopter.
  • all the ejection seats are ejected together.
  • only specific ejection seats are ejected in case of emergency, for example only occupied ejection seats.
  • counter rockets are fired in the opposite direction of the motion of the ejection seat to counteract the torque exerted by the ejection of the ejection seat.
  • a helicopter with an upward ejecting ejection seat comprising:
  • a body positioned at least partially under one or more rotors that provide the helicopter with the ability to fly;
  • a cockpit coupled to the body, wherein the span of the rotors does not reach above the position of the cockpit;
  • At least one ejection seat located inside the cockpit for seating the flight crew, wherein the ejection seats are adapted to be ejected upward above the cockpit clearing the span of the rotors.
  • the cockpit is located in the vicinity of the anti-torque means of the helicopter.
  • the helicopter enables access of the flight crew between the cockpit and the body of the helicopter while airborne.
  • the ejection seats are zero-zero ejection seats.
  • the cockpit is facing away from the tail of the helicopter, so that forward flight of the helicopter can be considered reversed to the direction of flight in a standard helicopter.
  • the cockpit is provided with counter rockets to counteract the rotational torque exerted by ejection of ejection seat 150.
  • a method of using an upward ejecting ejection seat in a helicopter without colliding into the rotors of the helicopter comprising:
  • the position is beyond the antitorque means of the helicopter.
  • the cockpit is facing away from the tail of the helicopter, so that forward flight of the helicopter can be considered reversed to the direction of flight of a standard helicopter
  • Fig. 1 is a schematic illustration of a helicopter with a cockpit in the antitorque area, according to an exemplary embodiment of the invention
  • Fig. 2 is a schematic illustration of a helicopter with an ejected ejection seat, according to an exemplary embodiment of the invention
  • Fig. 3 is a schematic illustration of a helicopter with an alternative design, according to an exemplary embodiment of the invention.
  • Fig. 4 is a schematic illustration of a helicopter with an alternative design wherein the ejection seat is deployed, according to an exemplary embodiment of the invention.
  • Fig. 1 is a schematic illustration of a helicopter 100, according to an exemplary embodiment of the invention.
  • helicopter 100 is designed as a standard helicopter with the motor and controls of the helicopter positioned in a helicopter body 110 below the rotors 120.
  • the cockpit 130 of the helicopter is positioned in the anti-torque area beyond the span of the helicopter rotors 120, for example after a tail rotor 140 or next to the tail rotor 140.
  • tail rotor 140 may be ducted or anti-torque may be provided by side ducts on the sides of helicopter 100 without having a tail rotor.
  • cockpit 130 is designed to accommodate the flight crew, for example the pilot and co-pilot, one or more ejection seats 150 and any equipment required to be positioned within reach of the pilot.
  • baggage and equipment required for the operation of helicopter 100 but not required to be in the cockpit 130 during flight, will be positioned in the body 110 of helicopter 100.
  • the center of gravity of helicopter 100 is located within body 110, optionally below the middle of rotor 120 for optimal flight performance.
  • the weight of the motor and load of helicopter 100 will optionally be of magnitude of a few tons, whereas the cockpit with the weight of the pilots will be only a few hundred kilograms.
  • a connecting body 160 between body 1 10 and cockpit 130 will be reinforced to accommodate cockpit 130 in addition to the standard antitorque apparatus.
  • helicopter 100 can be designed with the center of gravity in any position along the length of helicopter 100 and the body of helicopter 100 may be of any shape and design.
  • the controls of helicopter 100 will be adjusted to compensate for any deviation as a result of positioning a cockpit in the anti-torque position.
  • Fig. 2 is a schematic illustration of helicopter 100 with an ejected ejection seat 150, according to an exemplary embodiment of the invention.
  • ejection seat 150 uses standard methods to be ejected from helicopter 100, for example rockets 210, explosives, compressed air, springs or any other known method.
  • counter rockets 220 are placed under the tail of helicopter 100, below the position of ejection seat 150. Counter rockets 220 are activated simultaneously when ejecting ejection seat 150, to counteract the rotational torque exerted by ejection of ejection seat 150.
  • ejection seat 150 is designed to be ejected high enough so that ejection seat 150 can then open a parachute and allow the occupants to land safely.
  • standard ejection seats used today in many aircrafts may be used to implement the invention, for example a zero-zero ejection seat such as used in F- 15 and F- 16 airplanes. Standard seat today allow ejection from the ground to a sufficient height, opening a parachute and floating down safely to the ground.
  • cockpit 130 faces away from body 110 so that flying forward with helicopter 100 would be considered flying backward for a standard helicopter wherein the cockpit is situated on body 110 under rotors 120, for example the Bell 206.
  • cockpit 130 may face toward body 1 10 so that the cockpit would be directed toward the same direction as in standard helicopters.
  • cockpit 130 may be designed to allow visibility in both directions and the pilot may be able to rotate his seat to enhance visibility.
  • electronic cameras or other viewing devices may be placed on body 1 10 and adapted to provide the pilots with the view that is blocked by body 110 when cockpit 130 is facing it.
  • Fig. 3 is a schematic illustration of a helicopter 300 with an alternative design, according to an exemplary embodiment of the invention.
  • helicopter 300 is designed with a body 310 that encases the entire aircraft.
  • a cockpit 330 is located inside body 310; however cockpit 330 will be situated toward the rear of body 310 so that it is not situated under the span of the rotors of helicopter 300.
  • the pilots may leave their seats and access the rest of body 310 situated under the rotor inside body 310.
  • ejection with an ejection seat may only take place from ejection seats positioned in the rear of helicopter 300 located out of the span of the rotors.
  • Fig. 4 is a schematic illustration of helicopter 300 wherein the ejection seat is deployed, according to an exemplary embodiment of the invention.

Landscapes

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

Abstract

La présente invention se rapporte à un hélicoptère comportant un siège éjectable à éjection ascendante, comprenant un corps positionné au moins en partie sous un ou plusieurs rotors qui permettent à l’hélicoptère de voler ; un cockpit accouplé au corps, la longueur des rotors n’arrivant pas au-dessus de la position du cockpit ; un siège éjectable situé à l’intérieur du cockpit, le siège éjectable étant conçu pour être éjecté vers le haut au-dessus du cockpit dégageant la longueur des rotors.
PCT/IL2008/001117 2008-08-13 2008-08-13 Hélicoptère à siège éjectable WO2010018561A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/IL2008/001117 WO2010018561A1 (fr) 2008-08-13 2008-08-13 Hélicoptère à siège éjectable

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IL2008/001117 WO2010018561A1 (fr) 2008-08-13 2008-08-13 Hélicoptère à siège éjectable

Publications (1)

Publication Number Publication Date
WO2010018561A1 true WO2010018561A1 (fr) 2010-02-18

Family

ID=41668758

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IL2008/001117 WO2010018561A1 (fr) 2008-08-13 2008-08-13 Hélicoptère à siège éjectable

Country Status (1)

Country Link
WO (1) WO2010018561A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104260893A (zh) * 2014-09-22 2015-01-07 郝金东 一种直升机逃生系统及人用冲伞炮和直升机用冲伞炮
RU2679693C1 (ru) * 2018-04-19 2019-02-12 Михаил Сергеевич Беллавин Вертолёт
DE102017007678A1 (de) * 2017-08-12 2019-02-28 Frank Christophè Baumann Schlleuder Sitz für Hubschrauber
RU187446U1 (ru) * 2018-11-15 2019-03-06 Евгений Станиславович Фокин Безопасный вертолёт фокина

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2031876A (en) * 1935-02-19 1936-02-25 Burnelli Aircraft Ltd Airplane
GB470650A (en) * 1936-02-25 1937-08-19 Airspeed 1934 Ltd Improvements in or relating to aircraft
GB1010709A (en) * 1962-12-13 1965-11-24 Svenska Aeroplan Ab Rocket propelling device for aircraft ejector seats
US3662978A (en) * 1970-10-22 1972-05-16 Kaman Aerospace Corp Aircraft ejection seat vehicle stowed rotor
US3701503A (en) * 1970-04-16 1972-10-31 James Martin Parachute harness and release mechanism therefor
US4813634A (en) * 1985-01-05 1989-03-21 Zuck Daniel R Flying emergency ejection seat

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2031876A (en) * 1935-02-19 1936-02-25 Burnelli Aircraft Ltd Airplane
GB470650A (en) * 1936-02-25 1937-08-19 Airspeed 1934 Ltd Improvements in or relating to aircraft
GB1010709A (en) * 1962-12-13 1965-11-24 Svenska Aeroplan Ab Rocket propelling device for aircraft ejector seats
US3701503A (en) * 1970-04-16 1972-10-31 James Martin Parachute harness and release mechanism therefor
US3662978A (en) * 1970-10-22 1972-05-16 Kaman Aerospace Corp Aircraft ejection seat vehicle stowed rotor
US4813634A (en) * 1985-01-05 1989-03-21 Zuck Daniel R Flying emergency ejection seat

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104260893A (zh) * 2014-09-22 2015-01-07 郝金东 一种直升机逃生系统及人用冲伞炮和直升机用冲伞炮
CN104260893B (zh) * 2014-09-22 2016-01-06 郝金东 一种直升机逃生系统及人用冲伞炮和直升机用冲伞炮
DE102017007678A1 (de) * 2017-08-12 2019-02-28 Frank Christophè Baumann Schlleuder Sitz für Hubschrauber
RU2679693C1 (ru) * 2018-04-19 2019-02-12 Михаил Сергеевич Беллавин Вертолёт
RU187446U1 (ru) * 2018-11-15 2019-03-06 Евгений Станиславович Фокин Безопасный вертолёт фокина

Similar Documents

Publication Publication Date Title
US20190375505A1 (en) Detachable Pilotable Capsules and Aircrafts Including Detachable Pilotable Capsules
US5836544A (en) Emergency soft-landing system for rotor-type aircraft
EP3140190B1 (fr) Aéronef à décollage et atterrissage verticaux
US3298633A (en) Separable aircraft
US9027879B1 (en) Modular adaptive configured helicopter
US7234667B1 (en) Modular aerospace plane
US3142455A (en) Rotary vertical take-off and landing aircraft
US10807706B2 (en) Jettisonable emergency exit for a vehicle
US3289974A (en) Manned spacecraft with staged re-entry
EP3740427B1 (fr) Système de sécurité multi-mode pour aéronef vtol
US6817579B2 (en) Passenger transport module system for supersonic aircraft
US20200262553A1 (en) Hybrid electric-jet powered
WO2012047327A1 (fr) Avion vtol à trois ailes et six propulseurs basculants
GB2576248A (en) Aircraft
CN101857089A (zh) 飞机降落伞
WO2010018561A1 (fr) Hélicoptère à siège éjectable
CN110997487A (zh) 竖直起降飞行器配置
US20130200218A1 (en) Rotorcraft escape system
WO2007133182A2 (fr) Avion aérospatial modulaire
WO2017036080A1 (fr) Autogire équipé d'un parachute et procédé de fabrication
US20210229794A1 (en) Vehicle with at least one emergency exit system
CN204956905U (zh) 伞降自转旋翼机
EP3378773A1 (fr) Système de secours à parachute
US20160194080A1 (en) Tethercraft
US11767108B2 (en) Aircraft (drone)

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 08789791

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 08789791

Country of ref document: EP

Kind code of ref document: A1