RU2646030C2 - Method for saving the aircraft in case of the accident, the device for its implementation and the roll-off sensor - Google Patents

Abstract

FIELD: aviation; security facilities.

SUBSTANCE: group of inventions refers to the field of aviation. Method is characterized by the fact that before taking off of the aircraft the folded Kevlar amortization platform with the inclined forward sections is laid into the compartment, which is located under the front part of the aircraft fuselage, with the rear transversely located splitting. In case of emergency roll-off of the aircraft at the angle, which exceeds the predetermined value, the pressurization of the shock-absorbing platform is switched on using the compressed air from the airplane compressors and/or from the compressed air lines and it is released from the compartment through the transverse splitting of the front aircraft fuselage. Device contains the compressors, the compressed air supply lines and the roll-off sensor. It further comprises the front compartment of the fuselage, the lockable compartment with the rear splitting, in which the folded Kevlar shock-absorbing platform with its folds placed ahead is mounted, it is attached to the body of the aircraft and connected via the roll-off sensor and the switch in the cockpit with the air compressors and/or compressed air lines. Thickening is designed in the front section of the Kevlar shock-absorbing platform, and the central cutout – in its rear section. Roll-off sensor is made in the form of the horizontal sealed box with the two sections, which are separated with the barrier, each of which is filled with the electrically conductive non-freezing liquid. Lower and upper contacts, which are connected through the switch to the compressors and/or compressed air lines, are located on the front vertical wall of the box above each other.

EFFECT: group of inventions is aimed at increasing the efficiency of the aircraft crew and passengers rescue.

3 cl, 5 dwg

Description

The present invention relates to aviation and, in particular, can be used to rescue the crew and passengers of aircraft during aircraft accidents caused by external and internal factors.

There is a known problem of frequent aircraft crashes caused by various causes, terrorist attacks, pilot errors, bad weather and other factors.

A known method of ensuring aircraft safety, including attaching one or two reservoirs of synthetic fabric when folded to the cavity of the reservoirs, connected through locking taps with carbon fiber cylinders with compressed helium, on the upper part of the cabin, securing the upper reservoir with a volume of 2/3 of the total helium, laying the tank in the folded state and helium cylinders in empty places above the aircraft cabin, attaching to the lower part of the aircraft cabin a lower tank with a volume of 1/3, installing hinged hatches and two switching devices: one for “phased activation”, the second for “emergency activation”, while the “phased activation” is carried out by the pilot at high altitudes and at high speeds and includes 3 stages: 1 stage - deployment of the upper tank, 2 stage - slow filling of the upper tank with helium, stage 3 - deployment and filling with helium of the lower tank; “Emergency turn-on” implies a one-stage quick deployment of both tanks and their fast filling with helium, is activated by the pilot at low altitudes with one touch of a lever, the possibility of heating the helium with chemical reagents, in the alternative, helium can be replaced with hot air or any gas, see “Airbag for an airplane ", RU 2013147981, B64D 45/04 dated 10.28.2013.

There is a method of rescue of an emergency aircraft, including the emission from the aircraft of an elastic container connected to the aircraft by a cable system and a gas supply system into it is lighter than air, the gas supply to the vessel is lighter than air, when approaching the landing site, the vertical speed reduction of the aircraft is suppressed by starting brake jet engines installed in the lower part of the aircraft body, at the same time ensuring the maximum possible decrease in the horizontal speed of the aircraft, maintaining the position of the aircraft relative to the surface of the earth necessary to ensure its planning, the choice of the location of the included brake jet engines installed in the lower part of the aircraft body, and the amount of thrust developed by them based on the conditions of maintaining the plane when landing a horizontal position, the installation of an air-rubber system on the bottom of the aircraft to compensate for impact the airplane’s body at the moment of its contact with the earth’s surface, turning off the aircraft’s engines at the time of the release of the elastic capacity, resetting the aircraft’s engines and fire, or a preliminary translation aircraft fuel drain it in a nonflammable condition and release of the brake parachutes cm. RU 2009139433, B64D 25/08, from 26.10.2009.

However, the known solution, selected as a prototype, has certain disadvantages. First of all, the long lead time for all or some of the listed rescue operations. In case of a transiently developing accident or an emergency situation at a low flight altitude, the military pilot only has time to realize the emergency situation and enable bailout. In the event of an emergency with a passenger plane, the pilot can only have time to look at the nearest space in order to choose the place of landing or planning. As well as a drawback, it should be noted that the claimed method does not show technical operations to ensure storage, safe disposal of the listed equipment from the aircraft, without violating the tightness of the aircraft, which is fraught with instant death of the crew and passengers. The operations to ensure the possibility of storing and ejecting from the aircraft an elastic tank connected to the aircraft by a cable system are not reflected, and the operation of supplying gas to the tank is lighter than air. In addition, the functional limitations of the method, i.e. the impossibility of saving the aircraft in other types of accident, for example, a breakdown of the front landing gear.

The aim of the present invention is to achieve a technical result to increase the efficiency of rescue of the crew and passengers of the aircraft in various emergency situations by expanding the list of used technical means in an accident, for example, when the landing gear of the front wheel is destroyed, as well as accelerating the response of rescue equipment and choosing the optimal placement of means rescue without violating the tightness and aerodynamics of the aircraft, etc.

The specified technical result for the method is achieved by the fact that in the known method, including installation on an airplane and the use of an inflatable system, it is previously proposed, before taking off the airplane, to be folded with, tilted into the compartment with the rear, transversely located slit located under the front of the fuselage of the aircraft forward sections, a Kevlar cushioning platform, in case of an emergency roll of the aircraft at an angle exceeding the specified value, include inflating the cushioning platform with compressed air compress ditch and / or lines of compressed air of the aircraft and the release from the transverse gap of the cavity, depreciation platform.

The claimed technical result for the device is achieved by the fact that it is proposed to use compressors and / or air lines for supplying compressed air to the known device containing an elastic cavity, additionally introduce a roll sensor, execute a lockable compartment with a rear slit under the front of the fuselage, lay it folded into the compartment with folds tilted forward, a Kevlar cushioning platform attached to the aircraft body and connected via a roll sensor and a switch in the cockpit with compressors and / or m gistralyami compressed air, while the front of the platform serves Kevlar amortization perform thickening, and in its rear central recess. In this case, the roll sensor is proposed to be made in the form of a horizontal sealed box with two sections separated by a barrier, each of which is proposed to be filled with electrically conductive non-freezing liquid, on the front vertical wall of the box, to place the lower and upper contacts one above the other, which through the switches are proposed to be connected to compressors and compressed lines air.

The invention is illustrated in graphic materials. Figure 1 presents the image of the aircraft with the deployed and deployed cushioning platform, Figure 2 shows the cushioning platform, folded with sections tilted forward, Figure 3 shows a top view of the cushioning platform in the deployed state, Figure 4 shows a block diagram of the inclusion compressed air lines, Figure 5 shows the design of the roll sensor.

A device that implements a method of rescuing an aircraft in an accident with the designations in the figures includes:

1) a compartment under the front of the fuselage of the aircraft;

2) depreciation platform with a thickening in the front;

3) a center cutout at the rear of the cushioning platform;

4) a gap transverse to the longitudinal axis of the aircraft;

5) roll sensor;

6) compressed air line;

7) conductive fluid roll sensor;

8) roll sensor contacts;

9) a barrier separating the liquids of the roll sensor;

10) switches of compressed air lines and compressors;

11) compressors;

12) section of the depreciation platform.

A device that implements an airplane rescue method consists of a roll sensor 5, a switch 10, compressors 11 and / or compressed air lines 6 and a lockable compartment 1 located under the flight cabin and the front of the aircraft fuselage, in which, in the initial state, it is folded forward, Kevlar cushioning platform 2, connected to the compressed air lines 6. The cushioning platform 2 is attached to the aircraft body, has a thickening in the front part and a center cutout 3 in the rear part, designed to grip the broken aircraft front wheel strut. Compartment 1 in the body of the aircraft is low, because sections 12 of the cushioning platform 2 folded with the tilt forward are stacked in it. This design of the compartment 1 does not violate the aerodynamics of the aircraft. The roll sensor 5 is made in the form of a horizontal, two-section, separated by a barrier 9, sealed box, each of the sections of which is filled with an electrically conductive non-freezing liquid 7. On the front vertical wall of the box are located one above the other lower and upper contacts 8, which are connected via compressors 10 to compressors 11 or highways 6 of compressed air.

The way to save the aircraft in an accident is implemented as follows. Aircraft accidents often occur for various reasons, equipment failure, fracture of the landing gear of the front wheel of the landing gear, impossibility of landing due to failure to release the landing gear, bird falling into the turbine of an airplane, terrorist attacks, etc.

Consider each of these cases. First of all, at the stage of preparing the aircraft for take-off onto the inner surface of the lid of the autonomous compartment 1, under the front part of the fuselage of the aircraft, they lay sectionally, with an inclination forward, the Kevlar shock-absorbing platform 2, which is attached to the aircraft body without breaking its tightness, connected to compressors 11 and highways 6 compressed air and close the compartment lid 1. In the inflated state, the platform 2 and its front thickened part are located under the lower part of the fuselage and the flight cabin of the aircraft, see FIG. one.

In the event of an emergency due to equipment failure leading to the crash of the aircraft, the pilot, if he is alive, having exhausted all the possibilities of saving the aircraft, decides to go to the landing. To do this, he switches, located in the cockpit of the aircraft, includes, depending on the design of the aircraft, the supply of compressed air from the mains 6 of compressed air and / or from the compressors 11 of the aircraft into the shock absorption platform 2. At the same time, its first section is instantly filled, which is in its volumetric form pushes the remaining sections toward the rear slit 4 in compartment 1 and pushes the last section out of it, see FIG. 2. A powerful oncoming air stream picks it up, pulls the entire cushioning platform 2 from the cavity 1 outward, at the same time filling and inflating it with compressed air. Thus, the platform 2 almost instantly assumes its flat working position. Further, the oncoming air flow tightly presses the platform 2 to the lower surface of the fuselage of the aircraft. Thus, under the front of the fuselage, a support structure is formed that protects the aircraft, significantly mitigating its impact upon landing or splashdown.

When a strut (not shown) of the front wheel of the aircraft landing gear fractures, the cushioning platform 2, with its center cutout 3 at the rear of the platform 2, wraps around the broken strut and, acting as a support, allows the aircraft to land without destroying its bow and sunbathing.

In an accident, when the pilot is incapacitated, the connection of the compressed air lines 6 and / or compressor to the cushioning platform 2 is carried out from the roll sensor 5. In this case, with a sharp fall of the plane, the roll of the roll sensor 5 is tilted at an angle exceeding the set critical value and distant from the contacts 8, the electrically conductive liquid 7 overflows through the separation barrier 9, see FIG. 5 and merging with the electrically conductive liquid 7 located near the first contact 8, closes the contacts 8, thereby switching the compressors 11 and / or compressed air lines 6 to the cushioning platform 2. When the aircraft is brought in, the cushioning platform 2 becomes a pontoon, which gives the crew some time aircraft to stay afloat and carry out rescue operations.

The claimed method and the device implementing it are new, previously unknown, which indicates their compliance with the patentability criterion - novelty.

The proposed method and the device implementing it can be performed by specialists using well-known technical means, which indicates their compliance with the patentability criterion - industrial applicability.

Claims (3)

1. A method of rescuing an aircraft in an accident, including installing an inflatable system on the aircraft to compensate for impacts on the aircraft body at the moment of its contact with the surface of the earth or water, characterized in that prior to take-off of the aircraft into the cavity with a rear transverse slot located under the head part of the fuselage of the aircraft, stack the Kevlar cushioning platform folded with sections tilted forward in front of the aircraft, in case of emergency roll of the aircraft at an angle exceeding the specified value, the cushioning plate Orm inflated with compressed air from the compressors and / or compressed highways aircraft air discharged from the cavity and outwards. 2. A device for implementing the method of rescuing an aircraft in an accident according to claim 1, comprising an elastic cavity, characterized in that it contains compressors and compressed air supply lines and a roll sensor, a lockable cavity with a rear slit is made in the cavity under the cockpit and the front of the fuselage a kevlar cushioning platform folded with forward inclined folds is fixed, attached to the aircraft body and connected via a roll sensor and a switch in the cockpit with compressors and compressed air lines, m in the front part of the depreciation platform a thickening was made, and in the back part, a center gap. 3. The roll sensor of the aircraft rescue device according to claim 2, characterized in that it is made in the form of a horizontal, airtight duct with two longitudinally spaced sections separated by a barrier, each of which is filled with a conductive non-freezing fluid, on the front vertical wall of the duct there are lower and upper contacts, which are connected through a switch to compressors and compressed air lines.

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