KR20110131379A

KR20110131379A - A device of emergency escape for aircraft

Info

Publication number: KR20110131379A
Application number: KR1020100050784A
Authority: KR
Inventors: 변상복
Original assignee: 변상복
Priority date: 2010-05-31
Filing date: 2010-05-31
Publication date: 2011-12-07

Abstract

The present invention relates to an emergency escape device of an aircraft. When exiting the high altitude as in the prior art, a safe landing is possible because the parachute expands well, but in the vicinity of the low altitude, there is no time for the parachute to unfold so it falls and suffers a disaster.
The present invention has been conceived for the purpose of allowing the pilot to jump with the seat just before colliding with the ground in case of falling into the ground due to night flight or dark fog, causing only the pilot to escape. Immediately before colliding with the vehicle, the claw 8 held at both ends of the pilot seat plate 4 is automatically released by the operation of the motor 3 associated with the ultrasonic or infrared sensor, so that the pilot seat plate 4 is in a contracted state below it. As the spring rebounds rapidly due to the strong repulsive force of the installed spring 5, the upper back 14 of the seat plate 4 pushes the hatch 15 down. At this moment, one end of the seat plate 4 is inclined in the inclined state by being caught by the catching jaw 17, and only the pilot springs up and collides with a normal air bag installed in the fuselage, thereby relieving the high-speed acceleration force and landing safely.

Description

Emergency escape device of aircraft {A DEVICE OF EMERGENCY ESCAPE FOR AIRCRAFT}

The present invention relates to an emergency escape apparatus of an aircraft, and relates to an emergency escape apparatus of an aircraft, which has been made for the purpose of causing the pilot to escape to the outside urgently from the seat immediately before the collision with the ground due to an unexplained visibility and engine failure in the low air condition.

As in the prior art, when escaping rapidly from high altitude, such as an engine failure, the parachute spreads well, so that it is possible to land safely. However, there is no time for the parachute to unfold in the vicinity of the low altitude, and when the field of view is unclear, accidents and accidents that inadvertently hit the ground such as mountainsides occur.

It is an object of the present invention to provide a device for allowing the pilot to automatically escape from the seat immediately before colliding with the ground due to an engine failure or unclear vision due to farming.

According to the present invention, when an accident occurs during the night or during the farming, when an accident occurs, the hooks on both sides of the pilot's seat are automatically released by the motor of the electric circuit related to the infrared sensor in front of the aircraft. The spring springs under the pilot's seat cause the seat to spring up. At this moment, the top of the back of the pilot's seat pushes the hatch over and the pilot also bumps into the airbag, releasing high-speed acceleration and escaping outside. Therefore, the pilot has the characteristic of landing safely.

The present invention has the effect that when the aircraft crashed to the ground, even if the aircraft is broken, only the pilot escapes immediately before the ground crash to avoid the devastation.

1 is a longitudinal sectional view of the present invention;
2 is a cross-sectional view taken along the line AA of FIG.

Hereinafter, the present invention will be described in detail with reference to the accompanying drawings.

The semiconductor circuit 2 and the electric motor 3 related to the conventional ultrasonic or infrared sensor 1 are installed at the head of the aircraft, and a strong spring 5 is installed under the pilot's seat plate 4 and the seat plate ( 4) At both ends, the L-shaped hook (8) is slightly bitten on the upper end of the L-shaped lever (7) supported by the shaft (6) so that the spring (5) is always in a contracted state, and at the bottom of the left lever (7) The rack 9 formed in the horizontal section 7 'is engaged with the pinion 10 fixed to the central axis of the motor 3, and the U-shaped annual 11 is provided in the horizontal section 7' on the left and right sides. It is supported by the shaft 12 and connected with the pin 13, and the upper end of the backrest 14 of the pilot seat plate 4 is brought into contact with the hatch 15 and is caught by the inner wall of the fuselage 16 above the seat plate 4. By installing the jaw (17).

In the drawings, reference numeral 18 denotes an electric switch, 19 a hinge, 20 a seat plate, 21 a spring, and 22 an airbag.

The operation of the present invention configured as described above is as follows.

If the aircraft is sailing at night or during farming and accidentally falls, an electric motor (3) associated with a conventional semiconductor circuit (2) is operated when a conventional ultrasonic or infrared sensor (1) installed at the head of the aircraft immediately before a collision occurs. The pinion (4) fixed to the shaft of the rotation to move the rack (9) engaged with it, the L-shaped hook (8) formed on the top of the b-shaped lever (7) supported by the shaft (6) is the pilot seat The moment of departure from the bite state of the plate 4, the seat plate 4 of the pilot springs sharply by the large repulsive force of the spring (5). At this moment, the upper end of the backrest of the seat plate 4 pushes against the hatch 15 and the right end of the seat plate 4 hits the upper locking jaw 17 so that the seat plate 4 is tilted. At this moment, the pilot will bounce off the side of the fuselage 16 safely.

And in the cabin behind the cockpit is installed a strong spring 21 under the seat plate, the back of the chair in front of the chair is safer than the front pilot seat because the normal airbag 22 is installed.

In carrying out the present invention, when the aircraft departs, the electric switch 18 installed in front of the cockpit is closed, and when the aircraft lands safely on the airfield, the switch 18 is opened and shut off.

In carrying out the present invention, since the acceleration is applied when the pilot escapes to the outside, a normal airbag is installed next to the aircraft fuselage to mitigate the acceleration shock and land more safely.

Explanation of Reference Numbers
1: ultrasonic or infrared sensor 2: semiconductor circuit
3: electric motor 4: pilot's seat
5: spring 6: shaft 7: angled lever
8: angled hook 9: rack
10: Pinion 11: U-shaped year
15: hatch

Claims

The semiconductor circuit 2 and the electric motor 3 related to the normal infrared sensor 1 are installed at the head of the aircraft, and a strong spring 5 is installed under the pilot's seat plate 4, and the seat plate 4 is installed. ) At both ends, the spring (5) is always slightly contracted with the L-shaped hook (8) on the top of the B-shaped lever (7) supported by the shaft (6), and the bottom of the left lever (7) horizontally. The rack 9 formed in the rod 7 'is engaged with the pinion 10 fixed to the central axis of the motor 3, and the U-shaped annual ends are formed at one end of the horizontal rod 7' on the left and right sides. (11) is supported by the shaft (12) and connected by pins (13), the upper end of the backrest (14) of the pilot seat plate (4) is in contact with the hatch (15), the fuselage above the seat plate (4) (16) The emergency escape apparatus of the aircraft, characterized in that by installing the locking step (17) on the inner wall.