JP2002114197A - Emergency escape system by rotor.blade separation of helicopter - Google Patents

Abstract

PROBLEM TO BE SOLVED: To solve problems in an emergency escape system for a helicopter, wherein we have no effective emergency escape system from the helicopter in spite of the development of the aircraft technology, and a person must get out from a door and wait for the opening of a parachute while naturally falling under a condition that the helicopter starts the filling soon because it does not glide being different from an airplane, when the emergency occurs in the helicopter. SOLUTION: In a case of an incident of emergency in the helicopter, an escape switch is turned on first of all to disconnect a rotor blade and a rotor head caught by the centripetal force. Then, a speed is changed to the outer tangential line of a rotor turning circle from the inertia force of the centrifugal force. Here, the rotor blade is blown away more quickly and powerfully when the explosion force of the explosive is added. Whereby, the environment for allowing a pilot to escape to the sky by a rocket motor mounted under a seat, can be quickly prepared. In this way, the emergency escape can be achieved by separating the rotor blade and the rotor head.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a system for creating an environment where an emergency escape from a helicopter is possible by separating a rotor blade of the helicopter from a rotor head.

[0002]

2. Description of the Related Art Effective escaping systems from helicopters in the era of aviation technology around the world have never been considered. for that reason,
In the event of a helicopter emergency, there is no emergency escape except by jumping out of the doorway and waiting for the parachute to open naturally.

[0003]

At present, an airplane, especially for an emergency escape of a jet fighter, escapes by injection by a rocket motor mounted on a seat simply by turning on an escape switch, or for safety. Can be escaped by the injection of a rocket motor installed under the floor along with the cockpit. This is possible even at zero altitude, and after escape, the parachute opens and the pilot is saved. In helicopters, the primary reason preventing safe escape by rocket motor injection is the high speed rotation of the rotor blades used to lift the aircraft above the cockpit or pilot sitting in the driver's seat. It is impossible to escape upward. That said, if you're escaping forward, sideways, or down, helicopters are generally flying low and working near or between mountains and buildings. There are many things. For this reason, when the pilot escapes from the rocket motor in the forward, lateral, or downward directions, the altitude is insufficient for the parachute to open, or the vehicle crashes into a mountain or building wall. However, when the ejection seat is used upward as it is, the rotor blades are rotating at a high speed above the head, so that not only the cockpit is destroyed but also the pilot itself has a serious accident. This is why helicopter emergency escape devices have not been developed until now.

[0004]

SUMMARY OF THE INVENTION The present system creates an environment that enables an emergency escape of a seat or cockpit to a height at which a parachute is opened by a rocket motor or the like in the event of a helicopter emergency. System. Therefore, the operation sequence of the present system will be described below with reference to the simplified flow of the system shown in FIGS. 1, 2 and 3. FIG. 1 is a view of a normal flight equipped with a device for operating the system of the present invention. Continue to Figure 2
Fig. 3 is a diagram illustrating the operation of the system of the present invention in the event of an emergency. To explain this, when the pilot (4) of the helicopter (1) switches on the escape switch (5) from the off state, The electric current, the exhaust gas pressure, the mechanical operation or a combination thereof is used as signal energy, and passes through the transmission path (9) as shown by a thick arrow. When the device of the transmission path (9) cannot be installed, the signal energy of radio waves or laser light is sent. When this signal energy reaches the separation head (7), the safety device (8) receiving the energy is disengaged. The separation head (7) referred to here means explosive, exhaust gas, flammable gas, hydraulic pressure, magnetism, mechanical operation when receiving signal energy such as electric current, exhaust gas pressure, mechanical operation, radio wave, laser light or a combination thereof. Or a combination of these to transmit the power of the explosion and the force of the repelling to the safety device (8),
A device for removing the safety device (8) and separating the rotor blade (3) from the rotor head (2). The safety device (8) is a pin (10), a slide hook (14),
A device that does not come off easily unless signal energy is transmitted at a hook, glue, weld, swage, or combination thereof. When explosive power such as gunpowder is strong, the separating head (7) has a strong effect of ejecting the rotor blade (3) from the center of rotation outward from the rotor head (2) after removing the safety device (8). Can work. The slide hook (14) is a device that normally functions as a hook, but slides out of the role of a hook when signal energy reaches. Next, at the same time as the rotating rotor blade (3) comes off from the rotor head (2), the rotor blade (3), which has been trapped by centripetal force, becomes circumscribed by the centrifugal force due to the inertial force of the centrifugal force. The speed in the direction becomes and it is rushed. At this time, when calculating the approximate speed and distance at which the rotor blade (3) is blown per time, the radius n of the rotating rotor is 4 m, and the number of revolutions n per unit time of a constant time circular motion is 2 When the rotation speed / sec, the angular velocity ω (rad / sec), and the radius r (m) are given, the speed V at which the rotor blade (3) is thrown is represented by Formula 1 and the angular speed ω is represented by Formula 2. π = 3.1415, and therefore the velocity V is given by the equation (3). Therefore, the velocity V is 50.264
(M / sec) and instantly move sufficiently away from the pilot's head. Subsequently, as shown in FIG. 3, there is no obstacle above the pilot's head when the pilot escapes. Since the obstacles to escape have been eliminated, the vehicle can safely escape upwards afterwards by injection of a normal rocket motor or the like.

[0005]

(Equation 1)

[0006]

(Equation 2)

[0007]

(Equation 3)

[0008]

DESCRIPTION OF THE PREFERRED EMBODIMENTS In order to carry out the present invention, it is necessary to use a material which can withstand a sudden twisting force or an outward pulling force. ) And the rotor blade (3) usually never come off. However, the escape switch (5)
If you put in, it is easy to come off. Therefore, the first embodiment is a cross-sectional view of FIG. In this figure, since the rotor blade (3) is inserted into the sheath-shaped rotor head (2) and surrounds the rotor blade (3), it can withstand a strong twist. In addition, by applying a pin (10) which is a safety device (8) made of a material that is not cut by the rotor head (2) and the rotor blade (3), the outward pulling force is stopped, and the rotor blade (3) comes off. It will not be. In order to remove the pin (10) at the time of emergency escape, the pin is removed using the explosive power of the explosive (12), and then the explosive explosive (16) explodes. The rotor blade (3) that has come off the pin (10) moves away from the pod-shaped rotor head (2) instantaneously from above the cockpit due to inertial force and explosive force. At this time, the state shown in FIG. 5 is reached, and the wind receiver (11) mounted on the rotor blade (3) is opened by the spring (13) and does not fly too far due to air resistance. Therefore, it is hard to harm surrounding objects. FIG. 6 is a sectional view of a second embodiment. In this figure, the rotor head (2) is sandwiched between clips (15) mounted on a rotor blade (3). The clip (15) is always opened by the spring (13). The clip (15) is stopped by a slide hook (14) which is a safety device (8) so as not to be opened. At the time of emergency escape, the slide hook (14) is shifted. At the same time, the explosive (12) explodes and the clip (15) opens. Subsequently, the explosive powder (16) explodes. When the clip (15) is opened, the rotor blade (3) is vigorously blown out by inertia and explosive force. At this time, the state shown in FIG. 7 is reached, and the clip (15) is open, so that it does not fly too far due to air resistance and is therefore less likely to harm surrounding objects. In this way, an environment can be created in which the rotor blade (3) can be safely escaped to the sky by the injection of the rocket motor (6) under the seat immediately after the rotor blade (3) is flew in the first or second form. Incidentally, the explosive (12) in the description of the present invention is easy to handle when it is of a cartridge type.

[0009]

According to the present invention having the above-described system configuration, when the escape switch (5) is turned on in the event of an emergency in a helicopter, the rotor blade (3), which has been trapped by centripetal force, becomes Deviated from the rotor head (2), the inertia force of the centrifugal force caused the rotor to move in the tangential direction of the rotation circle of the rotor, and the rotor (3) disappeared immediately above the pilot (4). It can escape to the sky by injection of the motor (6). The time from when the escape switch is turned on to when the player escapes is from one second to at least two seconds later, the user has escaped into the air.

[Brief description of the drawings]

FIG. 1 is a side view of a helicopter (1) equipped with the device of the present invention and in a normal flight state.

FIG. 2: Turn on the escape switch (5) in an emergency,
FIG. 9 is a side view in which the signal is transmitted as indicated by a thick arrow and a rotor blade (3) is removed.

FIG. 3 is a side view showing a state in which a pilot (4) has escaped with a seat after a rotor blade (3) has come off.

FIG. 4 is a cross-sectional view of the embodiment using the first pin (10) of the present invention, in which the device has not yet been activated.

FIG. 5 is a cross-sectional view of the embodiment using the first pin (10) of the present invention, in which the rotor blade (3) is detached by explosion of explosive.

FIG. 6 is a cross-sectional view of an embodiment of the present invention using a second slide hook (14), in which the device has not yet been activated.

FIG. 7 is a cross-sectional view of the embodiment using the second slide hook (14) of the present invention, in which the rotor blade (3) is detached by explosive explosive.

[Explanation of symbols]

1 Helicopter 2 Rotor head 3
Rotor blade 4 Pilot 5 Escape switch 6
Rocket motor 7 Separation head 8 Safety device 9
Transmission path 10 Pin 11 Wind receiver 1
2 gunpowder 13 spring 14 slide hook 1
5 clips 16 release gunpowder

Claims (1)

[Claims] 1. A system for creating an emergency escape environment by separating a helicopter rotor blade (3) from a rotor head (2).