CS244177B1 - Involvement of pyrotechnic devices for dropping overlap of airplane cabin - Google Patents

Abstract

Connection of pyrotechnic devices for throwing the canopy of the aircraft cabin from the trajectory area of the ejection seat using two separate, smaller in volume and mass, subsequently operating pyrotechnic devices, the essence of which is that the pyromechanism (1) is connected to the lock opening cylinder (2) and to two canopy throwing cylinders (3), while the piston rod (4) of the lock opening cylinder (2) rests in the working position on the thumb (5) of the transverse shaft of the lock control mechanism (6) and is connected to the carrier (7) of the switch (8) of the electrical ignition circuit (9) of the rockets (10).

Description

using two separate pyrotechnic devices, which are smaller in volume and in weight, which consists in that the pyromechanism (1) is connected both to the cylinder of the opening of the locks (2) and to the two cylinders of ejection of the canopy (3); (4) the lock opening cylinder (2) engages the thumb (5) of the transverse shaft of the lock control mechanism (6) in working position and is coupled to the carrier (7) of the ignition circuit switch (8) of the rocket (9) ignition circuit (10).

244 177

- 1 244 177

The invention relates to the engagement of pyrotechnic devices for ejecting an aircraft canopy from the trajectory of a ejection seat, using two separate, smaller, volume-and-weight pyrotechnic devices.

So far known and used methods of solution of emergency ejection of the canopy with pyrotechnic device, from the trajectory area of the subsequently ejected pilot in the seat, are two:

ejection of canopy using pyromechanisrn and working rolls * ejection of canopy using rockets ..

The disadvantage of these methods is that with a single-stage (undivided) engagement of the pyrotechnic devices, with an overlap of greater weight and the required time to free the ejection space for the ejection seat, the weight and volume of the pyrotechnic devices increases. This significantly worsens the possibility of their installation on board the aircraft. For the installation of the said pyrotechnic devices are increasing demands on space, which in turn leads to a further increase in the weight of the airplane shell. Also, the use of larger impulse rockets, necessary to eject a heavier overlap, increases the risk to the aviator on the ejection seat in the cabin by the thermal and dynamic effects of the effluent gases from the nozzles. This danger increases with the time of the rocket burning and the flyover overlap during the maneuver flight nu.

These disadvantages are eliminated by the use of pyrotechnic devices for ejecting the canopy of an airplane with pyromechanism and at least two rockets according to the invention, which is based on the fact that the pyrom chani smus is connected both to the cylinder opening the locks and to two cylinders the opening of the locks abuts in a working position on the transverse shaft of the lock control mechanism and is coupled to the switch of the electric missile ignition circuit switch.

The advantage of the proposed solution is that by dividing and connecting the pyrotechnic devices, the resulting impulse necessary for the ejection of the canopy is distributed. Thus, the rockets can use shorter burning times, which leads to eliminate the risk of burning flyer thyromechánic devices are smaller and therefore more suitable for installation in the cabin. Do not require extraordinary adjustments to the shell and to

- 2 aircraft will result in overall weight loss. 244 177

An exemplary embodiment of the invention is shown schematically in the accompanying drawing, in which Fig. 1 shows the overall engagement and Fig. 2 shows the connection of the lock opening cylinder with the lock control mechanism.

The pyrotechnic device consists of a pyromechanism 1, a lock opening cylinder 2, two canopy ejection cylinders 3, an electric ignition lock control mechanism 6 and two rockets 10. The pyromechani smus 1 is connected both to the lock opening cylinder 2 and to the two discharge cylinders The cylinder 6 of the lock opening cylinder 2 abuts in the working position on the transverse shaft thumb 6 of the lock control mechanism 6 and is connected to the carrier 2 of the ignition circuit switch f of the rocket ignition 10.

During the electric firing of the pyromechanism 1, the combustion products are fed to the pistons of the cylinder 2 and the cylinders J. The pressure of the combustion products on the piston of the cylinder 2 gradually moves the piston rod 6 which rotates the transverse shaft of the lock control mechanism 6. switch 8 of ignition circuit J of rockets 10. Turning the transverse shaft opens the canopy locks and throws it with two cylinders J. On the sides of the canopy are located two missiles 10, which during the canopy movement burns from the electrical pulse switch 8 and accelerate release path .

The wiring according to the invention can be used on airplanes where an emergency ejection of the airplane canopy is required.

Claims (1)

SUBJECT OF THE INVENTION 244 177 Involvement of pyrotechnic devices for ejecting the canopy with pyromechanism and at least two rockets, characterized in that the pyrom chani smus (1) is connected both to the cylinder of opening of locks (2) and to two cylinders of ejection of canopy (3), the piston rod ( 4) the cylinder of opening the locks (2) dose in the working position per inch (5) of the transverse shaft of the lock control mechanism (6) and is connected to the carrier (7) of the switch (8) of ignition circuit (9) of rockets (10).