RU2213027C2 - Helicopter - Google Patents

Abstract

FIELD: aviation; means for rescue of passengers and flying vehicles; manufacture of advanced helicopters at high safety of passengers. SUBSTANCE: proposed helicopter has hermetic self-contained compartment in fuselage which is made in form of passenger cabin. Elongated shaped charges are located in fuselage along its case and over circumference between nose part with pilot cabin, central part with autonomous capsule and tail part and at point of attachment of propeller to fuselage. Nose part with pilot cabin is provided with parachute and rear side of central fuselage is provided with opening doors for placing the autonomous compartment in central fuselage. In case of evacuation, doorways of autonomous compartment are closed and explosive cutting of fuselage is performed by means of shaped charges. As a result, autonomous compartment is separated from propeller, nose part with pilot cabin, tail part and fuselage skin, after which parachute is deployed. EFFECT: extended field of application; enhanced efficiency at low altitude. 4 dwg

Description

 The invention relates to aviation, means of rescuing passengers from an aircraft and can be used to create promising helicopters with increased passenger safety.

 A device for rescuing a high-speed aircraft is known, comprising a parachute and a rocket connected in series, connected to the hull by three cables (US patent 3721408, class B 64 D 17/37, 03.20.73).

 The disadvantages of this technical solution is the inability to use at low altitude, can not be used for a helicopter, because propeller blades will cut the parachute.

 The purpose of the present invention is to expand the range of helicopter emergency situations in which the rescue of passengers and cargo becomes real.

 This goal is achieved in that the helicopter contains an integral fuselage and is configured to accommodate a passenger compartment in the fuselage, which consists of a sealed autonomous compartment-capsule, which is placed in the helicopter through the opening flaps of the rear of the fuselage. The fuselage contains devices made with the possibility of separating (cutting) parts of the helicopter body from an autonomous capsule compartment. An autonomous compartment capsule is placed in the fuselage along horizontal guides. The doorways of the autonomous compartment-capsule are made interfaced and with the possibility of their forced (automatic or mechanical) closure and water resistance. Between the autonomous compartment-capsule and the fuselage body are placed shock-absorbing devices and materials. Devices that ensure separation (cutting) of the parts of the helicopter body from an autonomous compartment-capsule are configured to use the cumulative effect and / or the effect of a directed explosion. The self-contained compartment capsule contains a parachute system.

 In accordance with the foregoing, as a means of evacuating passengers from an emergency helicopter, an autonomous compartment located in its fuselage as a passenger cabin is proposed, which, after separation from the helicopter, is capable of descent and soft landing. In connection with their new functionality and design, the autonomous compartment is proposed to be called the Aviation Passenger Autonomous Rescue Capsule (APAX).

 In FIG. 1 shows a diagram of a General view of the helicopter and the placement of devices for separating the capsule from the parts of the helicopter.

 In FIG. 2, 3 shows a diagram of the separation of the capsule from the tail and nose of the helicopter, propeller and skin and the bottom of the fuselage.

 In FIG. 4 depicts a descent diagram of a capsule with a parachute.

 The helicopter contains a housing 1, a screw 5 with blades (figure 1). The fuselage of the helicopter consists of a bow 2, a central 3 and a tail 4 parts. In the central part 3, there is an aviation passenger autonomous rescue capsule 8 (hereinafter referred to as the capsule), made in the form of a sealed (with closed doorways) autonomous compartment of the passenger compartment. In the upper part of the capsule is placed a parachute 10, ejected through the hatch 9. In the bottom of the capsule, it is possible to place inflatable shock-absorbing cylinders having an autonomous gas filling system. The walls of the capsule 8 are made insulated and power. The capsule can be equipped with a lighting and air conditioning system, operating from an autonomous energy supply system after separating the capsule from the fuselage. The capsule makes up the passenger cabin of the helicopter. The capsule is connected to the body by the power beams of the fuselage floor through horizontal guides that are located along the inner surface of the helicopter fuselage body and determine the position of the capsule, fix them, provide the “capsule - fuselage” design rigidity. The capsule 8 is placed (inserted) into the fuselage of the helicopter even during its construction through the opening flaps 6 located on the rear side of the central part 3 of the fuselage, and through which the capsule 8 is removed for maintenance, repair or replacement. The dimensions of the valves 6 correspond to the size of the capsule 8.

 The guide capsules are installed in the reciprocal guides of the fuselage body in a strictly horizontal direction, and therefore, during emergency evacuation of the capsule, they will not impede and delay the separation of parts of the cut fuselage skin from the oncoming oncoming air stream.

 In the fuselage along its body and the circles between the pilot's cabin, the capsule and the tail are placed (built-in) devices (means) 7, providing separation (cutting) of the fuselage body to release the capsule in case of emergency. For example, these can be built-in charges (cumulative, powder, pyro-cartridges, etc.) of directional action, cutting the fuselage skin around the circumference and along the horizontal. For example, devices 7 can be elongated cumulative charges (KZU), the detonation of which (using an electric detonator) performs an almost instantaneous explosive cutting of the helicopter body, which will lead to the separation of the tail and nose parts from the rescue capsule, the lining of the fuselage of the helicopter. It is envisaged to place devices 7 at the points of attachment of the helicopter screw to the fuselage for its separation from the helicopter.

 Powerful on-board computers of the helicopter equipped with appropriate programs reflecting the entire experience of emergency situations accumulated by aviation and possible accident scenarios should evaluate the degree of accident situation, make decisions on the evacuation of passengers. After assessing the situation as emergency, on-board computers, depending on the altitude of the helicopter, its speed of fall, the time required to bring the capsules ready for evacuation, use the evacuation options. The main thing here for choosing an option will be the time necessary to ensure inhibition of the speed of the descent capsule to an acceptable landing surface before it touches.

 Consider a capsule emergency evacuation scheme.

 After assessing the specific situation as emergency and requiring the evacuation of passengers, the on-board computers begin the implementation of the corresponding program for the evacuation of the capsule and which will be carried out as a general approximation as follows. Initially an emergency alarm is announced, after which, depending on the available time reserve, the doorways of the capsule are forcibly closed immediately or several seconds later. Then, in a certain sequence, commands are given to operate the devices 7, first cutting off the tail part 4 and the helicopter screw 5 (not shown) from the fuselage, and then from the pilot's cabin 2 capsule 8 (Fig. 2). This order of separation of the parts of the helicopter is caused by safety reasons for the evacuated capsule, taking into account the direction and speed of flight. In parallel with the separation of the capsule from the pilot's cabin around the circumference of the fuselage, the fuselage sheathing devices 7 cut along the length of the fuselage (FIG. 3). The result of the operation of the devices 7 and the incoming air flow will be quick, in a split second after the explosive cutting, the capsule is released from the cut parts of the fuselage skin. At the command of the on-board computer, taking into account the position of the capsule in space, a parachute 10 is displayed and the soft landing stage begins (Fig. 4). To accelerate the withdrawal of the parachute from the capsule, you can use devices already known in practice, for example, a mini-rocket. After landing (splashdown) of the capsule, the corresponding emergency means of communication, signaling, and life support are activated. In the bow of the helicopter it is necessary to provide for the possibility of sealing the cockpit, placing a parachute of sufficient power to ensure its soft landing or bailout of the crew.

 If there is not enough time to use the above-described rescue equipment (if a helicopter falls from a small height of several tens of meters), to reduce the consequences of accidents, it is necessary to provide for the placement of shock-absorbing materials in the walls between the capsule walls and the fuselage body.

Claims (1)

 A helicopter containing a propeller with blades and a fuselage, consisting of a bow with a cockpit, a central and aft parts, where the passenger compartment is located in the central part, made in the form of a sealed autonomous compartment with a parachute, designed to be placed in the fuselage with the possibility of separation from the bow with a cockpit and a tail, characterized in that it is equipped with elongated cumulative charges located in the place of attachment of the propeller to the fuselage, along and around the fuselage to separate the propeller, of the hull, nose with the cockpit and fuselage skin from the aforementioned compartment in an emergency, while the bow with the cockpit is made with a parachute, the rear side of the central part of the fuselage is made with drop-down sashes designed to accommodate an autonomous compartment in the central part of the fuselage.

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