WO2010018561A1

WO2010018561A1 - Helicopter with ejection seat

Info

Publication number: WO2010018561A1
Application number: PCT/IL2008/001117
Authority: WO
Inventors: Chibbi Naaman; Ron Ben Itshak
Original assignee: Individual
Current assignee: Individual
Priority date: 2008-08-13
Filing date: 2008-08-13
Publication date: 2010-02-18
Anticipated expiration: 2011-02-13

Abstract

A helicopter with an upward ejecting ejection seat, including, 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; an ejection seat located inside the cockpit, wherein the ejection seat is adapted to be ejected upward above the cockpit clearing the span of the rotors.

Description

HELICOPTER WITH EJECTION SEAT

FIELD OF THE INVENTION

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.

BACKGROUND OF THE INVENTION

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.

SUMMARY OF THE INVENTION

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. Optionally, 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. Alternatively, 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.

In an exemplary embodiment of the invention, 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. Optionally, the ejection seat can be activated at any altitude and at any airspeed just like an ejection seat of an airplane.

In an exemplary embodiment of the invention, 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.

In some embodiments of the invention, 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.

In some embodiments of the invention, all the ejection seats are ejected together. Alternatively, only specific ejection seats are ejected in case of emergency, for example only occupied ejection seats. Optionally, while ejecting the 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.

There is thus provided according to an exemplary embodiment of the invention, 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.

Optionally, the cockpit is located in the vicinity of the anti-torque means of the helicopter. In an exemplary embodiment of the invention, the helicopter enables access of the flight crew between the cockpit and the body of the helicopter while airborne. Optionally, the ejection seats are zero-zero ejection seats. In an exemplary embodiment of the invention, 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. Optionally, the cockpit is provided with counter rockets to counteract the rotational torque exerted by ejection of ejection seat 150.

There is thus further provided according to an exemplary embodiment of the invention, a method of using an upward ejecting ejection seat in a helicopter without colliding into the rotors of the helicopter, comprising:

Positioning the cockpit with the ejection seats of the helicopter beyond the span of the overhead rotors of the helicopter.

Optionally, the position is beyond the antitorque means of the helicopter. In an exemplary embodiment of the invention, 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

BRIEF DESCRIPTION OF THE DRAWINGS

The present invention will be understood and better appreciated from the following detailed description taken in conjunction with the drawings. Identical structures, elements or parts, which appear in more than one figure, are generally labeled with the same or similar number in all the figures in which they appear, wherein:

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; and.

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.

DETAILED DESCRIPTION

Fig. 1 is a schematic illustration of a helicopter 100, according to an exemplary embodiment of the invention. In 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. However 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. In some embodiments of the invention, 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.

In an exemplary embodiment of the invention, 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. Optionally, 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.

In an exemplary embodiment of the invention, the center of gravity of helicopter 100 is located within body 110, optionally below the middle of rotor 120 for optimal flight performance. Optionally, 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. In some embodiments of the invention 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.

In an exemplary embodiment of the invention, 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. Optionally 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. In 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. Optionally, when ejecting ejection seat 150 the roof above it is ejected with it, broken away or pushed out of the way by the ejection mechanism so that ejection seat 150 can be ejected. In some embodiments of the invention, 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.

In an exemplary embodiment of the invention, 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. Optionally, 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.

In an exemplary embodiment of the invention, 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. Alternatively, cockpit 130 may face toward body 1 10 so that the cockpit would be directed toward the same direction as in standard helicopters. In some embodiments of the invention, cockpit 130 may be designed to allow visibility in both directions and the pilot may be able to rotate his seat to enhance visibility. Optionally, 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. In some embodiments of the invention, helicopter 300 is designed with a body 310 that encases the entire aircraft. Optionally 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. In some embodiments of the invention, the pilots may leave their seats and access the rest of body 310 situated under the rotor inside body 310. Optionally, in case of emergency at a sufficient altitude they may bail out with parachutes from openings located on body 310, however 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.

It should be appreciated that the above described methods and apparatus may be varied in many ways, including omitting or adding steps, changing the order of steps and the type of devices used. It should be appreciated that different features may be combined in different ways. In particular, not all the features shown above in a particular embodiment are necessary in every embodiment of the invention. Further combinations of the above features are also considered to be within the scope of some embodiments of the invention.

It will be appreciated by persons skilled in the art that the present invention is not limited to what has been particularly shown and described hereinabove. Rather the scope of the present invention is defined only by the claims, which follow.

Claims

1. 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 said 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 said ejection seats are adapted to be ejected upward above the cockpit clearing the span of the rotors.

2. A helicopter according to claim 1, wherein said cockpit is located in the vicinity of the anti-torque means of the helicopter.

3. A helicopter according to claim 1, wherein said helicopter enables access of the flight crew between the cockpit and the body of the helicopter while airborne.

4. A helicopter according to claim 1, wherein said ejection seats are zero-zero ejection seat.

5. A helicopter according to claim 1, wherein 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.

6. A helicopter according to claim 1, wherein said cockpit is provided with counter rockets to counteract the rotational torque exerted by ejection of ejection seat 150.

7. A method of using an upward ejecting ejection seat in a helicopter without colliding into the rotors of the helicopter, comprising: positioning the cockpit with the ejection seats of the helicopter beyond the span of the overhead rotors of the helicopter.

8. A method according to claim 7, wherein said position is beyond the antitorque means of the helicopter.

9. A helicopter according to claim 7, wherein 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.