KR20020093874A - An aircraft with a detachable passenger escape cabin and an aircraft with airbags - Google Patents

Abstract

The present invention relates to an airplane having a separate cabin (1) for rescue passengers when the plane suddenly descends due to a failure or fire. The cabin escapes by a smooth or rapid release and slowly descends to the ground with the aid of parachutes 13 and 14, and when it hits the ground or the sea, the airbag attached to the bottom expands to absorb the impact applied during the collision. do. In addition, the airbag boxes 72a to 72c of the present invention are mounted on the conventional aircraft 70 in which the parachute device 71 is already installed to absorb energy generated by collision with the ground during sudden descent. do.

Description

Aircraft with a detachable passenger escape cabin and an aircraft with airbags

Moreover, according to the second embodiment, the present invention also relates to a conventional airplane which is used today, i.e. an airplane which has a parachute but does not include other components such as the airbag proposed in the present invention.

Today's technology does not provide a safety system such as the safety system of the present invention to rescue passengers while the plane is falling.

When the final stage of the survival effort is due to the plane's descent or fire, the only hope is for the passengers to escape from the plane, which is considered the space necessary for their life. Until that moment, people and planes constitute a 'unitary', and detachable or ejectable escape cabins are the means by which they are 'separated' and saved their lives.

The present invention relates to safe escape and rescue while passengers of an airplane flying high in the atmosphere descend into the ground. In particular, the present invention relates to the separation from an airplane cabin for a passenger that is properly attached to the aircraft fuselage, which provides an advantageous possibility of disengagement and separation at a critical point, thereby providing an advantageous possibility of departure from the plane. At the same time, the cabin's device consists of an airbag and an injection device, such as a rocket motor, which allows for parachute and rapid release, providing passenger rescue possibilities.

1A is a perspective view of an escape cabin shown separated from the body of an airplane prior to final attachment for proper flight operation;

1B is a perspective view of the aircraft fuselage shown separately from the escape cabin prior to final attachment for proper flight operation.

1C is a perspective view of an escape cabin attached to an aircraft fuselage that is interconnected by a removable joint during normal flight of the aircraft;

FIG. 1D is a perspective view of a detached escape cabin dropping to the ground in a state where an external air bag is supported by a parachute and operated with a parachute storage area, a small rocket, a storage space of a parachute cable, and an escape cabin; FIG. Detailed drawing of the connection point.

FIG. 2A is a perspective view of the parachute system operated while the plane of FIG. 1C is falling from the sky; FIG.

FIG. 2B is a perspective view of the airplane of FIG. 2A with its main parachute fully deployed to force the plane into a horizontal flight before the escape cabin is detached from the fuselage;

FIG. 2C is a perspective view of the escape cabin of the airplane shown in FIG. 2B with the parachute lifted away from the fuselage; FIG.

FIG. 2D is a perspective view of the aircraft fuselage shown in FIG. 2B being in rapid free fall away from the escape cabin; FIG.

FIG. 2E is a perspective view of the fuselage of FIG. 2D during a dive. FIG.

2F is a perspective view of the body of FIG. 2E that has already hit the ground.

2G is a perspective view of the escape cabin of FIG. 2C being supported by a parachute and descending at a slow speed.

FIG. 2H is a perspective view of the escape cabin of FIG. 2G immediately before it hits the ground with the external airbag already approaching the ground.

FIG. 2I is a perspective view of the escape cabin of FIG. 2H in which the airbag absorbs impact energy at the point of impact on the ground; FIG.

3 is a bottom view of an escape cabin of the present invention, detailing a quick escape device housed like a box and a quick escape device on the outside of the cabin, particularly on the bottom outside thereof;

3A is a perspective view of the escape cabin of FIG. 3 in the initial stage of ejection from the aircraft body by the injection device, detailing the initial oscillation of the parachute;

FIG. 3B is a perspective view of the escape cabin of FIG. 3A during a secondary release step by the rocket motor released quickly from the fuselage as the oscillating parachute is deployed; FIG.

FIG. 3C is a perspective view of the escape cabin of FIG. 3B during the final rapid release phase of disengagement from the fuselage and with the primary parachute fully extended to allow the cabin to gently descend to the ground;

FIG. 4 is a perspective view of an airbag box, the interior of which contains elements constituting the device and the airbag is shown in cross section; FIG.

4A is a bottom view of the escape cabin of the present invention with the airbag box disposed in its socket, showing the state before the airbag box is activated as well as the rest of the quick release device;

FIG. 4B is a bottom view of the escape cabin of FIG. 4A with an airbag box, showing the airbag is fully operational to operate and absorb impact energy; FIG.

5 is a plan view of a widening jet airplane in which a descent into the ground has begun due to engine damage to the airplane;

FIG. 6A is a side view of the jet plane of FIG. 5 with a greater degree of descent and with a parachute operated; FIG.

Fig. 6B is a side view of the escape cabin separated from the widening fuselage of the jet plane, in a state in which the cabin is supported by a fully deployed main parachute;

FIG. 6C is a side view of the widened fuselage of the separated jet plane shown in FIG. 6A, which begins to dive freely towards the ground. FIG.

7A is a cross-sectional perspective view of one of the bases of the detachable joint, showing in detail the space in which the propulsion mechanism is installed;

7B is a cross-sectional perspective view of another base of the detachable joint, showing in detail the housing it constitutes.

7C is a perspective view of components that the base receives, such as a piston, fuse, and spring;

FIG. 7D is a cross sectional view of the detachable joint mechanism shown in FIGS. 7A-7C operated in propulsion mode, illustrating a method of connecting to an escape cabin and a fuselage respectively; FIG.

FIG. 7E is a cross sectional view when the material encapsulated inside the joint mechanism shown in FIG. 7D explodes, showing displacement of the piston and separation of components of the escape cabin and fuselage; FIG.

8A is a cross-sectional view before operation of a hydraulic joint actuated split joint mechanism;

8B is a cross-sectional view after operation of the instrument of FIG. 8A.

9A is a cross sectional view before operation of the detachable joint mechanism operating with compressed air;

9B is a cross-sectional view after operation of the instrument of FIG. 9A.

10A is a cross-sectional view before operation of a mechanically actuated split joint mechanism;

10B is a cross-sectional view after operation of the instrument of FIG. 10A.

11 is a perspective view of the entire shape of the vertical injection unit.

FIG. 11A is a perspective view showing one piston of the expansion piston constituting the vertical injection device shown in FIG. 11; FIG.

FIG. 11B is a perspective view illustrating another expansion piston constituting the vertical injection device shown in FIG. 11. FIG.

FIG. 11C is a perspective view showing one piston of the expansion piston of the injection apparatus shown in FIG. 11 propagated vertically by ignition; FIG.

FIG. 11D is a perspective view of another expansion piston of the injection device shown in FIG. 11, being released and linearly moved by ignition and separated from the other piston. FIG.

Fig. 11E is a bottom view of the escape cabin at vertical discharge by propulsion of the injection device.

FIG. 11F is a bottom view of the escape cabin shown in FIG. 11E during the final release step from the expansion piston and during the first release step. FIG.

Fig. 11G is a bottom view of the escape cabin in the second stage, with the rocket motor fully in operation.

11H is a perspective view of the rocket motor and its components;

Fig. 12 is a bottom view of a conventional airplane of the second embodiment of the present invention, showing that the socket opening is disposed in the bottom portion of the body to which the airbag box is fixed.

12A is a cross-sectional perspective view of an airbag box with the elements that make up the device therein, the airbag box being secured to the socket opening of the plane as shown by the arrows in FIG.

12B is a bottom view of the conventional airplane of FIG. 12 before the airbag is actuated with the airbag box secured.

12C is a bottom view of the airplane of FIG. 12B with the airbag in operation fully deployed;

Fig. 13A is a perspective view of the conventional airplane of the second embodiment of the present invention, at the time when the deployment of the parachute starts during the descent step toward the ground;

13B and 13C are diagrams of a state in which the conventional airplane shown in FIG. 13A is suspended by a fully deployed parachute and is forced into a horizontal position while approaching the ground and the airbag box is fully operational;

13D and 13E show that the airbag absorbs energy generated in the collision with the ground when the conventional airplane shown in FIGS. 13B and 13C collides with the ground.

According to the first embodiment of the present invention, safety elements are attached to the appropriate points included in the escape cabin, so that when these elements are operated, a smooth escape may occur at a specific aerial position stage of the plane, such as a reversal position or an inclined position. If the cabin is separated or the aircraft is descending or the fire breaks out, the parachute system is operated to unfold the parachute, forcing the plane to take a horizontal position, and as a result, the cabin is separated. Separation of the cabin is very important because in a matter of seconds, when the airplane is engulfed in flames and the fuel explodes and the plane is in danger of being destroyed, the safety of human life is very high. By operating an associated escape system, such as, it is possible to give a quick escape opportunity through release.

Indeed, engine failures or stalls, descents, or fires in airplanes pose a deadly threat in the air, and the provision of airplanes with escape cabins for passengers constitutes a clear need.

The escape cabin constitutes an increased safety factor for the passenger, minimizes the anxiety that is always encountered during each flight, and provides a clear answer to the passenger's "escape-rescue" problem.

As a result of the foregoing, the primary objective of the present invention is to provide separation from the passenger fuselage cabin of the plane at a critical point in the flight of the plane, which escape cabin exhibits exceptional safety factors and at the same time escapes it. Two ways of managing the release constitute the most reliable means for the rescue of passengers, and one second of the moment of pulling the abandon handle until the parachute of the escape cabin is unfolded is released. It is critical to a safe return.

In addition, the escape cabin has an external air bag, and the operation of the air bag before it hits the ground absorbs some of the energy generated during the crash so that passengers are not injured by a momentary impact on their spine or other body parts. Is done.

Thus, a second main object of the present invention is to provide a small installation space suitable for attaching airbags to the escape cabin of the plane so that these airbags are operated before the collision of the escape cabin to protect the passengers.

In addition, the lightweight cabin structure offers the possibility of moving and its weight limitation is important considering that it is supported by a parachute during the descent to the ground. This also offers the advantage of being attached to large airplanes, such as jet airplanes, as well as small lightweight airplanes in which the parachute in this case supports a relatively small weight during the descent of the cabin relative to the liftability of the entire conventional airplane. This can be achieved due to the use of composite materials and alloys that can reduce the weight of the cabin.

A second embodiment of the present invention relates to a small, four-seat, light weight conventional aircraft that is flying today and already equipped only with a parachute system, in which various forms are described in US Pat. Nos. 4050657, 4709884 and Europe. Patent No. 0599437A1 is disclosed.

The drawback with the use of parachute systems in connection with these planes is that passengers descend with the entire plane to the ground at the critical moment the plane falls. The fact is that in the event of a fire, that is, when the plane is descending due to a fire, passengers may be burned in the atmosphere before they have time to return to the ground, or even an explosion of airplane fuel may explode in the atmosphere. In this respect, it inevitably makes the application partially inefficient.

One additional drawback associated with the use of parachute systems in these conventional airplanes is the enormous loading force on the passengers during the collision with the ground when descending and the heavy weight of the airplane in relation to the above advantages of the first embodiment of the present invention. This is because the parachute descends at high speed.

Thus, there are some limitations with regard to the size and weight of the parachute that can withstand the descent of the entire plane, thus making the parachute system inefficient for future applications in large conventional aircraft.

Accordingly, a third object of the present invention is to provide a device such as a conventional airplane airbag already equipped with a parachute system, and to provide the passenger protection of the narrow installation space required with the possibility of operating before the plane hits the ground. To provide useful possibilities.

These and other objects, features, and advantages will become apparent from the following analytical description with reference to the preferred embodiments and associated accompanying drawings.

With reference to the accompanying drawings, preferred embodiments of the present invention are described.

According to a first embodiment of the invention, the shape of the escape cabin 1, shown as a separate escape cabin in FIG. 1A, is in the form of a longitudinal independent compartment rounded by a length edge. The length of the compartment is significantly longer than its width and length, and the width ratio is in the range of 2.5: 1. In addition, the separated body 4 is shown in FIG. 1B, in which the body and the escape cabin are assembled into an airplane 5.

The escape cabin 1 is a heavy duty light weighted structure made of any suitable material that is used today or may be used in the future, which is attached to the detachable joint 6 of the body 4. A detachable joint 2 for joining the cabin is provided as well as a device consisting of a parachute, a catapult, a rocket motor and an air bag.

The strong framework of the fuselage 4 together with the escape cabin 1 forms the final plane when assembled as shown in FIG. 1C, which fuses the internal hollow opening of a special shape in relation to the 2.5: 1 ratio form. 3) and having dimensions that occur with the escape cabin 1, the escape cabin penetrates into the opening 3, is assembled, and is connected to the fuselage by its outer mount 1a which extends around it. It is supported on the outer circumference 3a of the opening 3 of 4) and connected to the corresponding detachable joint 6.

In order to provide the necessary safety for the passengers of the cabin, the escape cabin 1 shown in the corresponding figures has a transparent cockpit canopy 11a, a cockpit 11 and a cockpit 11 provided with an instrument panel. It forms a compact structure having doors and portholes, and all cockpit joints, etc., which were connected to the fuselage 4 of the plane 5 at the time of departure of the cabin, are separated.

At a suitable point on the outside of the roof 34 of the escape cabin 1 a hole 32 is formed, in particular in the rear, close to the tail wing (see FIG. 1D), which is a ballistic parachute 13, 14 and the The small rocket 35 connected to the small parachute 13 is stored. In particular, the small parachute 13 that pulls the main parachute 14 must first be deployed so that the main parachute 14 can be successfully deployed, as shown in FIG. 2A, which is a small rocket pulling the small auxiliary parachute 13. This is accomplished by first oscillating (35).

The escape cabin 1 is connected by cables 36a, 36b, 36c, 36d of the main parachute at the outer points 33a, 33b, 33c of the roof, which are in the normal environment of the roof 34 of the cabin. It is stored in the special groove 34a.

The separate joints 2, 6 are separated by an explosion mechanism or hydraulically or by compressed air or mechanically, which are separated by the pilot pulling the handle 10 in the cockpit 11 at the extreme moment. (See FIG. 1D)

The propulsion release mechanism of the escape cabin 1 from the fuselage 4 of the airplane 5 of the present invention is a representative embodiment of the detachable joint mechanisms 2, 6, as shown in FIGS. 7 a, 7b, 7c, 7d. . The propulsion release mechanism consists of a connection base 2 supporting a housing 2a (FIG. 7B) which is permanently fixed in the longitudinal direction of the cabin at its four edges at a suitable point on the escape cabin 1.

Another connecting base 6 supporting the housing 6b (FIG. 7A) is permanently fixed at the corresponding point in the opening 3 of the body 4. In addition, a piston 25 having a fuse 25a and a spring 25b is shown in FIG. 7C. More analytically, the connection mode of the escape cabin 1 with the fuselage 4 is shown in cross section in FIG. 7d, where the connection base 2 is permanently fixed to the part 1b belonging to the escape cabin 1 and The connecting base 6 is shown to be permanently fixed to the part 4a belonging to the body 4. The piston 25 inside the compartment 29 holds the parts 4a, 1b tightly connected by means of a spring 25b. The housing 6b is also arranged with an initiator 27 and an explosive material 28. In order to separate the two parts 4a and 1b, the explosion of the material starts and the generated gas 26 propels and displaces the piston 25 thereby releasing the two parts 4a and 1b and the piston 25 Is locked in the housing 2a and remains there.

According to a second embodiment of the invention, this connection is similar to the previous embodiment, as shown in FIG. 8A, but in this case the disengagement is hydraulic. More analytically, in Fig. 8a the connecting base 2 is permanently fixed to the part 1b belonging to the escape cabin 1 and the other connecting base 6 is permanently attached to the part 4a belonging to the fuselage 4. It is shown to be fixed.

The piston 20 inside the compartment 19 holds the two parts 4a, 1b firmly connected with a spring 20b and also supports the fuse 20a. The pipe 23 is also fixed on the housing 6b and filled with a suitable fluid 22 and in communication with the compartment 19, in which there is a piston 20. As shown in FIG. 8B, according to a suitable system, pressure is applied to the fluid 22, which in turn releases the two portions 4a and 1b by applying pressure to the piston 20 and displaces the piston 20. Locked in 2a) and remains there.

According to another embodiment, the connection is made similar to the previous way, as shown in FIG. 9A, but the decoupling is made by compressed air. More analytically, the piston 24 shown in cross section is in communication with a pipe containing air 26a. In FIG. 9B, the air 26a is compressed by a suitable system and as a result compressed air exerts pressure on the piston 24, displacing the pistons 4 so that the two parts 4a, 1b are disengaged.

According to another embodiment, the connection is made in a similar manner as before, as shown in FIG. 10A, but the disengagement is mechanical. More analytically, the piston 16 is connected with the wire rope 18. As shown in FIG. 10B, through the wire rope 18, traction is applied to the connected piston 16 so that the piston is displaced so that the two portions 4a, 1b are disengaged.

The following describes how the cabin 1 escapes smoothly from the plane 1 when time permits, or when there is no imminent fire hazard or when no rapid release escape system is provided.

In FIG. 2A, the pilot parachute system 13, 14 has already been operated by the small rocket 35, with the aid of the small parachute 13 being pulled by the small rocket 35. As it unfolded, the plane 5 began to dive towards the ground.

In FIG. 2B, the plane is supported by the fully deployed main parachute 14 so that it is in a horizontal position and at the same time the disconnection of the detachable joints 2, 6 is automatically started.

The airplane 5 of the preferred embodiment is a lightweight passenger aircraft capable of carrying eight passengers, but the present invention is not limited to this airplane size.

In FIG. 2C, the escape cabin 1 is now separated from the fuselage 4 and descends towards the ground while being supported by the main parachute 14.

The fuselage 4, separated in FIG. 2D, rapidly descends freely towards the ground.

The fuselage 4 separated in FIG. 2E continues to descend toward the ground.

The fuselage 4 separated in FIG. 2F collides with the ground and is destroyed.

The escape cabin 1, separated in FIG. 2G, continues to descend slowly while being supported by the parachute 14.

The escape cabin 1, separated in FIG. 2H, approaches the ground and prepares for a collision with the ground 42 by the sensor 41 operating its external airbags 38a-38f at a predetermined height.

The escape cabin 1 separated in FIG. 2i reaches the ground and collides, and the airbags 38a to 38f absorb some of the energy generated during the collision to prevent the impact of the collision on the passengers sitting in the cabin. do.

Now another way is described where the cabin 1 is quickly released from the plane 5 when there is no time or when the plane is about to explode.

It is evident that the success of the escape cabin 1, which is structured to be able to be discharged vertically, depends on the effective design of the propulsion system. This is because required power must be generated for proper vertical rise. Vertical discharge, however, requires the generation of a thrust T that is greater than the weight W of the escape cabin 1 so that a safety margin of ascending potential is provided. In general, excess thrust in the 20% range is desirable to allow a certain acceleration margin, but this should not reach high acceleration values so that the generated energy does not suffer on the spine of the passenger. This specifies a minimum T / W ratio of 1.2. Vertical thrust deflection, for example in the case of rockets, is not sufficient for the rise of the escape cabin 1. The problem that results is with respect to the balance of moments arising from the fact that thrust is not applied exactly to the center of gravity of the escape cabin 1.

If the force then raises the rear part of the escape cabin 1, the force will have to occur at the front part as well. Thus, the front part of the flight deck 11 will be moved upward or downward without restriction. That is, stability about the horizontal axis is ensured.

Nevertheless, stability around the longitudinal axis must also be ensured. Therefore, the application of an appropriate force is required at the front, rear, left and right of the gravity center of the escape cabin 1 to enable the possibility of vertical rise, ie discharge. Various methods can be found based on the manner in which these forces are generated and the direction in which the forces are applied. The system to be used must be small in size and weight so as not to limit the weight of the escape cabin 1 as well as the maximum effective space allowed.

According to a preferred embodiment, the propulsion mechanism of the linear accelerated explosion operates in two stages and consists of two expansion pistons 30 and 31 (oscillation injection device 80) and a cartridge system (rocket-motor 81). .

The oscillation system of the injection device 80 and the injection device attachment points into the escape cabin and the oscillation system of the rocket motor 81 are shown in detail in FIG. 3, where the escape cabin of the present invention is shown from the bottom. .

More analytically, the vertical oscillation injection device 80 shown in FIG. 11 is accommodated like a box in the vertical opening 1d at the four corner portions 1c formed along the outer floor of the escape cabin 1 (see FIG. 3). do.

The injection device 80 consists of two pipes 30, 31, which act like telescopic pistons and one arranged in the other. As shown in FIG. 11A, the pipe 30 is closed at one end 30a of its end, opened at the other end 30b and received like a box perpendicular to the escape cabin 1 as described above. The other pipe 31 (FIG. 11B) is closed at one end 31a of its end and is open at the other end 31b and at this open end a narrow portion, ie a neck portion 31c, is formed which is thrust during expansion. To increase the. The pipe 31 has a smaller diameter than the other pipes 30 and can thus be mounted without tolerances through the interior of the pipe 30. A predetermined explosive is contained in the pipe, and when the explosive is exploded and the two pipes are separated and towed flexibly, the pipe 30 (FIG. 11C) stored in a box in the escape cabin 1 is replaced with another pipe (31). Is linearly spaced apart and is linearly released from (Fig. 11D), and the initial release of the escape cabin 1 from the fuselage 4 is achieved by acting like a strut on the fuselage 4.

In FIG. 11E, the initial stage of the separation by firing of the injection device and the escape cabin at the moment of its vertical release are shown analytically from the bottom. In FIG. 11F, the escape cabin of FIG. 11E is formed by the injection device 80. At the end of the first stage of discharge and in the final stage of separation from the expansion piston 31, a second stage of separation of the cabin from the fuselage 4 is initiated, which is carried out to the rocket engine 81. As a result of this, a quick separation from the fuselage 4 is achieved so as not to hit the rigid vertical tail (tail wing) 4.

11H shows a rocket motor 81 consisting of a cartridge complex 81a, a nozzle 81b and a firing unit 81c, which is shown in more detail in FIG. 3 and the floor of the escape cabin 1. Mounted at a good point outside.

In Fig. 11g the second stage of the detachment of the escape cabin 1 from the plane 4 is shown in a bottom view, in which the full operation of the rocket motor is shown.

3a to 3c, there is shown an embodiment of the present invention relating to the rapid escape of the cabin, where the plane 5 is an escape cabin via the operation of an escape support system such as an injection device 80 and a rocket motor 81. It shows that the cabin can be separated from the fuselage 4 at the moment when the rapid escape of (1) occurs. 3A-3C, the full unfolding of the parachute 14 is shown in which oscillation of the parachute 13, 14 is achieved by the rocket 35 and provides a safe descent of the cabin to the ground. More analytically, in FIG. 3A, the release of the escape cabin 1 from the aircraft 5 fuselage 4, the pilot handles the special handle in the cockpit 11 by firing the injection device 80. It is shown at the moment of pulling the 10 and by the small rocket 35 towing the parachute 13, 14 along its package during the first stage.

Following the foregoing, FIG. 3B shows that approximately 0.40 seconds after pulling the escape handle 10, the escape cabin 1 is now not hit by the vertical vanes 4a of the fuselage 4 with the aid of the rocket motor 81. It is shown that spaced apart and the deployment of the parachute 13, 14 is also in progress. In the last step (FIG. 3C), with respect to the escape of the cabin 1, approximately 2.90 seconds after pulling the escape handle 10, the escape cabin 1 is lifted by the main parachute 14 and now the fuselage 4 It begins to descend slowly towards the ground as it is separated from

With respect to another embodiment of the invention, the airbag box 85 is proposed as an integral component of the exterior of the floor of the escape cabin 1.

An air bag that will inflate within one second of a few minutes before the escape cabin 1 hits the ground will act as a barrier between the rough or sharp ground and the escape cabin 1 by absorbing kinetic energy. The airbag is disposed outside of the floor of the escape cabin and is designed to protect the passengers in the escape cabin 1 during collision with the ground. During a collision, loads exceeding certain limits are applied to the spinal column of the passengers, which can cause irreparable damage to them. Without an external airbag, the passenger's body would slide out of the seat and be injured. During the initial millisecond of deployment of the airbag, the escape cabin will approach the ground and will be spaced the shortest distance from the ground to ensure sufficient space for the airbag to fully inflate.

Airbag boxes suitably mounted at appropriate points outside the escape cabin 1 constitute an effective means for the passive safety of the passengers.

In order for the airbag to operate at a certain distance from the ground and before a collision occurs, a distance detection sensor 41 with infrared radiation 41a is installed in the airbag box 85 (FIG. 4), which is grounded without infrared radiation. The distance from is calculated, and from this data an assessment is made of how close the ground is to the airbag box and how close it is to the ground.

More analytically, in Fig. 3, the escape cabin 1 of the present invention is shown in a bottom view, in which the airbag box 85 and its socket openings 37a to 37f are shown in detail. In FIG. 3 socket openings 37b to 37d are shown in a state before the airbag box is fixed there, with the remaining openings supporting the airbag box 85. The socket opening 37b differs in shape since the injection device 80 is stored close to it like a box. Thus, the entering airbag box 85 may be of the same shape, and the other airbag boxes located in the other escape cabin 1 will also be of the associated type.

In FIG. 4, the airbag box 85 is shown as having a complete structure with an airbag 38 and constituting a unique structure that can be sold as a unique product on the market, thus having a parachute device but having an airbag box 85 It can be adapted to the second embodiment of the present invention, which means a conventional airplane which is already in use without a safety member such as).

In FIG. 4, the airbag 38 is properly folded and packed in its box 85 is shown in cross section. At the base of the airbag is installed a boiler apparatus 39 comprising a suitable chemical preparation 40 such as propergol as a solid fuel form or other suitable solid fuel which is known, used today and may be used in the future. have. The mechanism of the boiler 39 is completely sealed by an air bag. In the event that the escape cabin 1 impinges on the ground, the electromagnetic distance detection sensor 41 activates the electrical contact centered at the center of the boiler 39 mechanism to induce ignition of propergol, which is 35 × 10 ^{−. The} collision energy generated by burning the gas within ³ seconds and rapidly inflating the airbag 38 immediately before contacting the ground can be absorbed. In the event of a collision, the airbag inflates and is approximately 150-200 x sufficient time to prevent injuries of passengers sitting in the escape cabin 1 or passengers of another conventional airplane 70 of the second embodiment of the invention. Will be held for 10 ^-3 seconds.

The airbag 38 of the present invention is made of a special, waterproof, nonwoven fabric to retain air therein, and must also have a sufficient thickness to withstand the forces that develop during a collision. The airbag may also be made of any other suitable material that is commercially available today or may be used in the future.

4A is a bottom view of the escape cabin 1, in which all devices of the cabin, such as the airbag box 85, are arranged in the corresponding socket openings 37a to 37f, which airbag box through the distance detection sensor 41. The state before operation is shown.

In FIG. 4B the escape cabin shown in FIG. 4A is shown in a bottom view, all airbag boxes 85 are actuated, and their airbags 38a to 38f absorb the impact energy generated during collision with the ground when fully deployed. It is fully stretched out, that is, inflated.

According to another alternative of the invention, as shown in FIG. 5, the wide light jet 79 is operated to separate the passenger escape cabin 1 (FIG. 6B) from the wide plane 4 (FIG. 6C). . In this case the separation can be carried out according to the smooth escape possibility of the cabin 1 or the rapid escape possibility of the cabin 1.

Next, the application of the smooth escape of the cabin 1 is shown with reference to the accompanying drawings.

As shown in the plane of FIG. 5, the plane 79 stalls and descends to the ground due to a failure of the engine.

In the side view shown in FIG. 6A, the degree of dive of the airplane 79 is increased and as a result the airplane pilot launches the small rocket 35 to operate the ballistic parachute systems 13, 14 and thus the small rocket 35. The small rocket 13 pulled by is unfolded.

In FIG. 6B, the main parachute is fully deployed so that the plane 79 is forced into a horizontal position and the detachable joints 2, 6 automatically show the escape cabin 1 in FIG. 6C as shown in FIG. 6B. The fuselage 4 begins to fall rapidly to the ground, and the escape cabin 1 lifted by the parachute 14 descends to the ground slowly and safely, the lower part of the outer floor The airbag box 85 disposed therein absorbs the collision energy generated when the cabin collides with the ground.

The twenty-seat wide light jet 79 also represents another airplane with increased passenger capacity.

For the lightest weight for the escape cabin 1, it must be constructed of a composite or alloy, such as an alloy of aluminum-lithium, or other known materials and materials used today, or any other material that may be used in the future. .

In addition, essential safety measures for the survival of passengers will be provided in case of escapes occurring at significantly higher heights, so that compressed air is maintained therein to prevent pressure drop during the escape cabin is disconnected so that the passengers lack oxygen. Even if you suffer from a so-called "hypoxia" condition, you may have minimal time to wear the mask.

In addition, the escape cabin 1 is long enough to contain all passengers and crew seats, and is also suitably designed to float to provide the passengers with the necessary safety even when the water waves are rough when landing on water. Should be.

According to a second embodiment of the invention, as shown in FIG. 12, a conventional lightweight airplane is mounted on the outer bottom of its fuselage 70a and airbag box 86 mounted in the socket openings 71a, 71b, 71c. It is proposed to have.

In this conventional airplane, a parachute device has already been applied and, as already described, is currently in use in connection with the patent of the above-described form.

However, these conventional airplanes can supplement parachute systems used with airbag boxes, taking into account the development of loading forces that impact passengers, particularly their spinal column, causing injury while the plane descends and hits the ground. There is a need.

In FIG. 12A, an airbag box which constitutes an independent structure comprising the entire device constituting the airbag 72 and which can be used as a unique product in the market for subsequent application in an already used conventional airplane with a parachute device is shown. 86 is shown. In addition, with respect to the protection of other airplanes without such parachute arrangements and in case of a drastic landing, for example when the landing gear of a wheel is damaged, the airbag 72 operates to extract some of the energy generated by the extreme collision. Will be absorbed.

In FIG. 12A the airbag 72 is shown in cross section being properly folded and packed in its box 86. At the base of the airbag is installed a boiler apparatus 39 which comprises a suitable chemical preparation 40 such as propergol as a solid fuel form or other suitable solid fuel which is known and used today or may be used in the future. The mechanism of the boiler 39 is completely sealed by the airbag 72. In the case where a conventional airplane 70 is about to impinge on the ground, the electromagnetic distance detection sensor 41 activates an electrical contact centered at the center of the boiler 39 mechanism to induce ignition of propergol, which is 35 x 10 It is possible to absorb the collision energy generated by releasing gas which rapidly inflate the airbag 38 just before burning and contacting the ground within ^-3 seconds. In the event of a crash, the airbag will inflate and will hold for approximately 150 to 200 x 10 ^-3 seconds, which is a time sufficient to prevent injuries of passengers sitting in the conventional plane 70 of the second embodiment of the present invention.

The airbag 72 of the present invention is made of a special, waterproof, nonwoven fabric to retain air therein, and must also have a sufficient thickness to withstand the forces that develop during a collision. The airbag may also be made of any other suitable material that is commercially available today or may be used in the future.

FIG. 12 shows a bottom view of a conventional airplane 70 supporting socket openings 71a, 71b, 71c at the bottom of its fuselage 70a, with an airbag box 86 shown in FIG. 12a. As shown by the arrow.

In Fig. 12B the plane shown in Fig. 12 is shown from the bottom, but corresponding airbag boxes 86 are mounted in the socket openings 71a to 71c and these airbags are operated according to the above description.

In FIG. 12C the plane shown in FIG. 12B is shown in a bottom view, but the collision energy generated when the plane hits the ground when all devices in the airbag box 86 have been activated and their airbags 72a, 72b, 72c are fully deployed. It is fully expanded, ie expanded, to absorb it.

Next, a method of operating the airbag box 86 for the light weight conventional airplane 70 is described with respect to the second embodiment of the present invention.

In FIG. 13A the lightweight conventional airplane 70 is experiencing a significant amount of dive and thus the pilot has operated its parachute system 71.

In FIGS. 13B and 13C, the plane shown in FIG. 13 is forced into a horizontal position by the fully deployed parachute 71 and approaches the ground. At a predetermined distance from the ground 42, the distance detection sensor 41 attached to the airbag box 86 activates the external airbags 72a, 72b, and 72c to fully expand (expand) the airbag to collide with the ground 42. Absorbs the collision energy that occurs.

In FIGS. 13D and 13E, the plane 70 shown in FIGS. 13B and 13C strikes the ground 42 at a controlled speed, and the inflated airbags 72a, 72b, 72c absorb some of the generated energy. Thus, the force applied to the body of the passenger sitting in the airplane 70 is reduced.

The escape cabin 1 shown in FIGS. 1A, 1D, 3, 3A to 3C, 6B of the first embodiment of the present invention can be applied not only to the small light aircraft 5 but also to the large light aircraft 79. And even for much larger jumbo jets, proper design-modification of the escape cabin 1 and the fuselage 4 was made.

It should be noted here that the description of the present invention has been made with reference to exemplary embodiments but is not limited thereto. Thus, in the second embodiment of the present invention, the escape cabin 1, the parachute 13, 14, the injection apparatus 80, the rocket motor 81) Changes or modifications to the drawings, sizes, arrangements, materials, structural and assembly components, and techniques applicable to the structure and operation of the airbag box 85 and the airbag box 86 of the conventional aircraft 70 are claimed. As defined by the scope, it is considered to be within the scope and purpose of the present invention.

Claims (10)

A plane with a detachable passenger escape cabin that detaches when the plane suddenly falls to the ground. Consisting of a longitudinal split passenger exit cabin 1 and a split joint in the split fuselage, The plane 5 is formed with an internal opening 3 which receives and connects to the escape cabin 1, which opening 3 is formed at an appropriate position of a strong frame of the fuselage 4 of the plane 5. The opening has a shape and dimensions corresponding to the shape and dimensions of the escape cabin (1), the cabin enters and matches the opening (3), and a separate joint for supporting and connecting the escape cabin ( 6) and the periphery 3a, The escape cabin 1 has a shape and dimensions associated with the opening 3 so that it can enter and match into the opening, the escape cabin 1 being compact, strong and lightweight, having doors and portholes and having an aluminum-lithium alloy Or made of plastic or any other known material used today or used in the future, wherein the escape cabin 1 supports the external mounting support 1a and the detachable joint 2, each of which is a plane ( 5) Support and connect the cabin in the opening 3 of the fuselage 4, wherein the escape cabin 1 escapes when there is a risk of falling to the ground when the plane is still in the atmosphere or there is a risk of fire. The cabin 1 can be detached from the fuselage 4 of the plane 5 via the handle 10 in the cockpit 11 at the command of the pilot, thus allowing for a smooth and rapid release with the passengers in the atmosphere. Escapes by means of fit within the opening 3 of the fuselage 4 so that passengers have the opportunity to safely descend to the ground with the help of the parachutes 13 and 14, The detachable joints 2, 6 separate the escape cabin 1 from the plane 5 body 4 by propulsion mechanisms 27, 28, The propulsion mechanism consists of a connecting base 2 with its housing 2a, which is permanently fixed by the other connecting base 6 in the longitudinal direction of the escape cabin 1 at an appropriate point on the edge, The housing 6b of the base 6 is permanently fixed at a corresponding point in the opening of the body 4 such that the bases 2, 6 are matched and joined together and floated by the inner piston 25, The piston disengages the connected portions of the escape cabin 1 from the fuselage 4 by being displaced during the explosion of the propulsion mechanism consisting of the explosion cap or the detonator 27 and the explosive material, The hydraulic mechanism consisting of the bases 2, 6 has an internal piston 20, which is displaced under pressure exerted on it through a special fluid 22 to connect the connected parts of the escape cabin 1 to the body 4. ), The compressed air mechanism 24 composed of the bases 2, 6 has an internal piston 24, which is displaced under pressure exerted by it by the compressed air 26a to connect the connected parts of the escape cabin 1. Separated from the body (4), The mechanical device consisting of the bases 2, 6 has an internal piston 16, which is displaced under the traction of a wire rope 18 connected thereto to connect the connected parts of the escape cabin 1 to the plane 5. An airplane having a separate passenger escape cabin, which is separated from the fuselage 4. 2. The escape cabin (1) according to claim 1, wherein the escape cabin (1) has a hole (32) for accommodating and storing the parachute (13, 14), and a small rocket (35) having cables (36a, 36b, 36c), The cable is connected to the parachute 14 at one of its ends and to the points 33a, 33b, 33c of the escape cabin 1 at the other end thereof and connected to it during the launch of the small rocket 35. The parachute can be towed along a small parachute 13 which assists in opening and unfolding the main parachute 14 initially deployed and connected thereto and when detached from the fuselage 4 of the plane 5 when in the atmosphere. A plane having a separate escape cabin, which, when escaped, may support an escape cabin (1) so that the main parachute (4) can safely and slowly descend the escape cabin (1) toward the ground. 3. The plane (5) according to claim 1 or 2, wherein the plane (5) suddenly begins to descend to the ground and assumes a horizontal position with the aid of the main parachute (14), which is essentially fully deployed at any position in the atmosphere and thus an escape cabin. (1) is smoothly separated from the fuselage (4) falling to the ground by its own weight, and the escape cabin (1) lifted by the main parachute (14) slowly descends safely to the ground and seats passengers sitting therein. A plane with a detachable escape cabin to rescue. The oscillation injection according to claim 1 or 2, wherein the escape cabin (1) is quickly separated from the fuselage (4) by vertical discharge and escapes when there is no time due to a fire, and consists of pipes (30, 31). Device 80, The pipe acts as a telescopic piston, one arranged inside the other, the injection device 80 is housed in a box in a vertical opening 1d at four corners 1c in the longitudinal direction of the escape cabin 1 and The pipe 31 has a smaller diameter than the other pipe 30 so that the pipe 31 can fit through the pipe 30 without tolerance, and the pipe 30 is closed at one end 30a thereof and the other pipe 31 is closed. ) Is also closed at one end 31a, and when a predetermined amount of explosive material is stored therein, the pipes 30 and 31 are elastically separated and spaced apart, thus opening 1d of the cabin 1. The pipe 30, which is housed like a box, can be stretched apart from other pipes 31, and as these pipes are used as struts on the body 4, at the end of the initial discharge phase by the injection device 80 Initial from the fuselage 4 of the escape cabin 1 identified by Exodus is made and at the same time, and a second separation step of the escape cabin (1) starting from the body 4 to be operated by a rocket motor 81, The rocket motor 81 consists of a cartridge unit 81a, a nozzle 81b and a firing unit 81c and is attached to the outside of the floor of the escape cabin 1, during which the rocket motor is connected to the body 4 of the fuselage 4. An airplane with a separate passenger escape cabin, which launches quickly so that the impact on the wing 4a is avoided. The escape cabin (1) of the plane (5), which has started to dive to the ground, is handled at any air position in the atmosphere or at the command of the pilot in case of fire. A separate passenger escape cabin, which is rapidly released from the fuselage 4 in the atmosphere by the 10 and at the same time supported by the main parachute 14 fully deployed by the launching of the parachutes 13, 14 by the small rocket 35. Equipped plane. 6. The escape cabin (1) according to any one of claims 1 to 5, wherein the escape cabin (1) has socket openings (37a to 37f) outside of its floor, the socket openings having boxes of corresponding airbags (38a to 38f). Is installed and the airbag is inflated to absorb some of the energy generated while the escape cabin 1 hits the ground, The airbag box 85 can also be purchased as an independent item and installed in the corresponding socket openings 37a to 37f of the escape cabin 1, each airbag box 85 constitutes its own magnetic inclusion structure, Airbags 38 which may be used as permanent devices incorporated in the escape cabin 1 or may be added to conventional airplanes, made of special waterproof fabrics or other known and any materials that are in use today or in the future. The airbag 38 has a thickness and strength effective to withstand a predetermined load in the event of a crash, and is specially folded and packed to completely seal the boiler mechanism 39 and the boiler mechanism is provided with a propeller ( Suitable fuels in solid form, referred to as 40) or any other suitable solid fuels known and used today or may be used in the future. And the airbag box 85 has a distance detection sensor 41 at a particular point, which immediately activates the electrical contacts in the boiler 39 when a collision with the ground is imminent. Ignition) and the fuel is burned quickly, releasing gas and rapidly inflating the airbag 38, thereby absorbing the load generated during the collision of the escape cabin 1 when reaching the ground to prevent injuries of passengers. , Airplane with detachable passenger escape cabin. 7. The detachable passenger escape cabin according to any one of the preceding claims, wherein the escape cabin can be applied to a wide lightweight jet 79, which represents another plane with a much greater passenger transport capacity. airplane. In an airplane provided with the airbag of claim 6 for attenuating the energy generated by the collision force due to the plane's descent to the ground and for preventing a predetermined range of loads being applied to the passenger's body, The plane 70, Socket openings 71a to 71c are provided at the outer bottom of the fuselage 70a, and the openings are respectively equipped with boxes 86 of corresponding airbags 72a to 72c, and these airbags are inflated so that the plane 70 Absorb some of the energy that occurs when it hits the ground, The airbag box 86 is also usable as an independent article and is mounted in the corresponding socket openings 71a to 71c of the airplane 70, each airbag box 86 constitutes an independent magnetic inclusion structure and the It can be used as a permanent device incorporating the portion of the fuselage 70a of the plane 70 and as an additional device to a conventional plane with or without a parachute, and the airbag 72 can be used at sea level 70 ) Is made of a special waterproof fabric without holes to preserve its durability and support, or is made of other suitable materials that are known today and have sufficient thickness and strength to be used in the future to withstand certain loads in the event of a collision, The airbag 72 is specially folded and packed therein with a suitable fuel or other known form of solids referred to as propergol 4. And a boiler mechanism 39 containing a suitable solid fuel, which is used today or may be used in the future, is completely enclosed and housed, and the airbag box 86 has a distance detection sensor 41 at a particular point. Activates the electrical contacts in the boiler 39 to initiate ignition of the fuel 40 when impingement on the ground is imminent and the fuel burns rapidly and simultaneously releases gas, which inflates the airbag 72 An airplane with an airbag that absorbs a load that develops during a collision when the airplane 70 reaches the ground, thereby preventing passenger injuries. It is marketed as an independent product and has corresponding airbags 38 and 72, which can absorb the loads generated in the event of a collision with the ground and at the same time support the escape cabin 1 and the plane 70 at sea level. Air bags box, characterized in that by floating so that they do not float and sink. An airplane having the detachable passenger escape cabin and airbag of any one of claims 1 to 9, which is made of a material which can be used today or in the future and which has a detachable escape cabin (1) and a fuselage (4). 5, 79 does not constitute new inventions or contribute to the already known technological developments with respect to the drawings, sizes, devices, materials, structures and assembly components, techniques applied in conventional airplanes 7 and techniques. Any alterations or modifications are within the scope and purpose of the present invention.