DE2949778C2 - Device for rapid and simultaneous severing of the wall of a means of transport, in particular the fuselage wall of an aircraft - Google Patents

Description

tion chamber (10) is connected

F i g. 2 shows the device in longitudinal section and FIG. 3 shows the flow conditions in the combustion chamber in section.
The one shown in Fig. 1 adjacent to an aircraft

3. Device according to claim 1 or 2, marked 30 device consists of a container 1, which is a vessel

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characterized by a in the punching gripper (8) in front of it, in the area of its punching end opening channel (16) which can be connected to an extinguishing agent source (vessel 4).

Contains 2 for hydrogen, a container 3 for oxygen and a container 4 for extinguishing agents, which have been tried and tested Hoses 5 are connected to a cutting torch 6, to which a punch 8 and a fuse 35 direction in the form of spark plugs 7 is assigned.

The cutting torch 6 has the shape of a torus

Circular cross-section. The interior of the tom forms one Combustion chamber 10, which is a slot-shaped

The invention relates to a device for cutting cutting nozzle 9, which has one to be cut through len and at the same time severing the wall of a wall 17 is arranged opposite. On the incineration means of transport, in particular, the fuselage wall of a voltage chamber is on the opposite of the cutting nozzle 9 ~ lying side an annular oxygen supply line 11, which with the combustion chamber 10 through

Aircraft, according to the preamble of claim 1.

It is already known that a slot 12 or nozzles are connected to both in an aircraft wall Wall areas consisting of plastic along one side of the cutting nozzle 9 sit on the outside of the wall of the

Combustion chamber 10, hydrogen supply lines 13, which are connected to chambers 14 via a slot standing, which from the wall of the combustion

closed contour, one to be broken out
Wall section corresponds to installing a fusible link, which in the event of an accident of a very high
Current flows through, which due to the thereby
generated heat are the breaking out of the wall 50 and which chambers 14 via slots 15 with the cut along the fusible conductor (DE-OS combustion chamber 10 are connected.

In Fig. 3 are the flow of oxygen and hydrogen illustrated by arrows.

chamber 10 and the wall of the cutting nozzle 9 is limited

In the center of the cutting torch 6 forming to-

26 12 574).

The known device allows a wall section to be removed, but only at a fixed one Place, regardless of whether this place after 55 rus sits over spokes held a punch an accident and after removing the wall section 8, the extension in the direction of the cutting nozzle 9 Stäfür the occupants of the vehicle are accessible or not. be 19 and centrally with a channel 16 for supply

The object on which the invention is based is the introduction of the extinguishing agent from the vessel 4 and one

therefore it says that the device of the initially explosive device 18 is provided with a battery

called type so that it is connected to any eo for ignition.

Position of the outer wall of a means of transport, in particular the device according to the invention is with its

those of an aircraft fuselage, for a fast and for cutting torch 6, as in FIG. 1 shown on the wall 17

the occupants safe cutting out a wall of an aircraft positioned, the distance from the

Incision can be set. Wall 17 is defined by the rods 19. By ignition

This task is carried out with the identification of the Pa- h5 training of the explosive device 18 with the help of the ignition

tentanspruchs 1 specified features solved. pulses of the battery, the punch 8 is through

The device according to the invention has the advantage that the wall 17 is pushed through, so that the extinguishing agent is removed

that with the punch gripper they can safely and quickly reach the vessel 4 of the container 1 via one of the hoses 5

and the channel 16 can be introduced into the interior of the aircraft in order to protect the occupants from the effect of the Cutting torch 6 to protect.

At the same time, hydrogen of the combustion chamber fO from the vessel 2 via one of the hoses 5, the Feed line 13 and the chambers 14, while on the other hand the oxygen into the combustion chamber 10 from the vessel 3 via one of the hoses 5, the feed line 11 and the slots 12 are inserted. The mixture is ignited by sparks generated by the spark plugs 7. The hot combustion gases then flow out through the cutting nozzle 9 directed against the wall 17 and cut an opening into the Wall 17. The cut-out part is held by the punch 8 and by the reaction force of the cutting torch 6 pulled away from the fuselage to the outside. The cutting nozzle 9 is thereby through the line 13 supplied hydrogen outside and cooled by the chambers 14 inside

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1 sheet of drawings

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Claims (2)

Claims: can be set, fixed and held at any chosen point on the outer wall of the means of transport, while the hot gases flowing out of the cutting nozzle cut a parting line along a closed predetermined contour that extends through the entire wall in a very short time, the detached wall section being pushed out of the rest of the wall due to the recoil of the hot gases emerging through the cutting nozzle. 1. Device for rapid and simultaneous severing of the wall of a means of transport, in particular the fuselage wall of an aircraft, with a closed wall section to be separated corresponding contour, adapted to the curvature of the wall, heat for the Severing-generating device, as a result of which io is pounded, since the severed wall section of characterized in that the device is held in the punch gripper on the Cutting torch (6) is. which is attached to a hydrogen cutting nozzle source (vessel 2) and an oxygen source (vessel With the measure according to claim 2 on the one hand 3) connectable and an ignition device (spark plug - a cooling of the cutting nozzle and on the other hand a ze 7) having combustion chamber (10) for uniform mixture formation in the combustion chamber raw this associated cutting nozzle (9) of the chamber guaranteed The contour is formed following and the one with the measure according to claim 3 is achieved through the wall (17) within the separating contour that extinguishing agent can be repelled in the interior of the wall section Punch gripper (8) is kept spraying that the vehicle occupants are hot 2. Apparatus according to claim 1, characterized in that 20 melt drops and the hot cutting gas are protected draws that the cutting nozzle (9) are to the side of Kam-. mern (14) is limited with a hydrogen supply based on the drawing is an exemplary embodiment Driving line (13) and through slots (15) explained in more detail in the area of the invention. It shows Inner wall of the combustion chamber (10) with the F i g. 1 in a front view schematically an aircraft ser are connected, and one of the cutting nozzle (9) 25 with a device attached to the fuselage, opposite, on the combustion chamber
(10) provided oxygen supply line (11), which along a slot (12) with the combustion