RU2443604C1 - Fast-operation damping system for aircraft emergency landing - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft shock absorbers. Proposed system comprises gas filling source and envelopment with inflatable element with its one base attached to aircraft fuselage bottom at its center of gravity. Envelopment with inflatable element is made up of the main inflatable device made up of closed pneumatic-carcass damping loop filled by gas from said source and consisting of top and bottom inflatable torus-like bases connected by inflatable posts and additional inflatable damping device made up of envelopment communicating with ambient medium via bypass holes arranged on outer lateral surface and arranged inside pneumatic carcass damping loop. Top base of the latter features smaller diameter than bottom base and is attached to aircraft fuselage bottom.

EFFECT: lower load in emergent landing.

7 cl, 3 dwg

Description

The invention relates to devices intended for use in air transport and aviation sports in conjunction with high-speed parachute systems to mitigate the impact, mainly aircraft (LA) in emergency situations in contact with the surface.

High-speed shock absorption system (BSA) is designed to dampen shock loads when the aircraft lands with the crew and passengers in the case of special emergency rescue high-speed parachute systems (BPS).

The possibility of parachute rescue of the crew and passengers along with the aircraft, as well as the constant relevance of the problem of reducing the time the parachute was put into operation, has led to the creation of a separate type of parachute technique - high-speed parachute systems of aircraft (BPS aircraft), which is characterized by a decrease in the time of the stage of pulling the parachute system beyond due to the use of forced pull accelerators.

The emergence and use of BPS revealed a number of additional advantages, such as:

- exclusion from the scheme of saving the exit and separation stages from people, which significantly reduces the time and the minimum safe altitude from the moment a decision is made to the moment the parachute system is put into operation;

- more comfortable and safer for people (physiologically and psychologically) conditions with the introduction of the parachute system in action, with a decrease and emergency landing, because the crew and passengers remain in the seats on board the aircraft;

- there is no need for individual parachute training of the crew and passengers;

- there is no need to purchase rescue parachute systems for individual use.

BSA is an additional means of increasing aircraft safety when using BPS in the event of an emergency landing.

The technical result of the invention of the BSA is to increase the safety of the crew, passengers and the aircraft itself, providing the ability to land on any surface and reduce the loads acting on passengers and crew during landing, to increase the buoyancy properties of aircraft on the water surface, including in strong winds and waves , as well as the safety of the aircraft after landing and reducing the likelihood of causing material damage and personal injury during emergency landing of the aircraft.

A device for emergency rescue of an aircraft is known, comprising a parachute which is intended to be connected to the upper part of the fuselage, and a soft shell of a pneumatic shock absorber, consisting of a first section, which is intended to be fixed on the lower part of the fuselage, a second intermediate section and a third section, which is intended for interaction with the surface during the descent, the attachment point of the aforementioned first section of the shell on the lower part of the fuselage (RU 2180639 C1, B64D 1/14, 2002).

To absorb shock, it is supposed to use a soft shell, the volume of which is much larger than the volume of the aircraft, and therefore, equipment for pressurization with a gas source of large weight is necessary.

Also known is a cushioning system for emergency landing of an aircraft, mainly equipped with a high-speed parachute system having a forced pull accelerator, containing a gas source and a shell with an inflatable element, one of the bases of which is attached to the bottom of the fuselage of the aircraft (US 5944282 A, B64D 1/14 , 1999).

The equipment necessary for this system increases the weight of the aircraft, and therefore reduces the weight of the payload, and it takes a long time to pressurize a large soft shell.

The objective of the invention is to improve safety during emergency landing of various types of aircraft while reducing the weight of additional equipment and increase the speed of the emergency rescue device.

The technical result consists in increasing the safety of the crew, passengers and the aircraft itself, providing the possibility of landing on any surface and reducing the load acting on passengers and crew during landing, in increasing the buoyancy properties of the aircraft above the water surface, including in strong winds and waves , as well as the safety of the aircraft after landing and reducing the likelihood of causing material damage and personal injury when the aircraft falls on the surface span of land, private and public facilities.

The invention is illustrated by a specific example, which, however, is not the only possible, but clearly demonstrates the possibility of achieving the above set of essential features of the above technical result.

The invention is illustrated by drawings, where:

figure 1 shows the location of the parachute and high-speed shock absorption system for emergency landing of the aircraft before hitting the surface;

figure 2 - arrangement of a high-speed shock absorption system for emergency landing of the aircraft before hitting the surface;

figure 3 - diagram of a high-speed depreciation system for emergency landing of the aircraft after hitting the surface.

The proposed BSA in a laid state is in a closed volume in the lower part of the aircraft, mainly in the region of its center of gravity, and contains: a gas supply and injection source; transformable pneumatic frame, the upper base of which is attached to the lower part of the fuselage of the aircraft; freely damping shell filled with overboard air, fastened with a pneumatic frame.

The BSA principle of operation is the additional (with respect to the use of BPS) quenching of the kinetic energy of the emergency aircraft during its landing by using a rapidly filled pneumatic frame shock absorber and a damper connected with it and smoothed out by it during pressurization.

In order to achieve a technical result for reducing loads during emergency landing of an aircraft equipped with BPS, the BSA uses a transformable pneumatic shock-absorbing frame made from an infeed and gas supply source (ejector type gas filling system), made in the form of an inflatable device, which is a closed single-volume circuit consisting of from the lower and upper inflatable toroidal bases connected by inflatable needles.

The filled damping shell is an additional shock-absorbing device, which is a shell freely filled with overboard air with bypass openings on. its outer side surface, located inside the pneumatic frame shock-absorbing circuit, while the upper base of the pneumatic frame is made with a smaller diameter than the lower base, and is attached to the lower part of the fuselage of the aircraft. In addition, it is preferable that:

- the gas source for the inflatable element was made in the form of an automatically or manually activated gas filling system with an air ejector;

- air ejectors were placed in the cavities of the upper and lower bases and / or in inflatable needles;

- filled damping shell was made single-volume or multi-section;

- the upper base was attached to the lower part of the fuselage of the aircraft by means of a support element made in the form of a lower contour of the fuselage in the form of a skin to ensure uniform pressure at the time of landing, attached to the upper base by fastening.

BSA 1 (Fig. 1) for emergency landing of LA 2 (Figs. 1-3), equipped with BPS 3 with suspension elements 4, contains at least one gas source (not shown) and shells with inflated and filled elements.

The pneumatic frame is made in the form of an inflatable device, which is a closed pneumatic frame shock-absorbing circuit filled with a gas source, consisting of the lower 5 and upper 6 inflatable toroidal bases connected by inflatable needles 7. The filled damping element in the form of a shell representing an additional shock-absorbing device 8 located inside pneumatic frame and associated with it, made of durable airtight material with calibrated bypass holes 9 d For the initial intake of air from the atmosphere when filling the pneumatic shock-absorbing frame and the outflow of air 10 from the shell 8 and bleeding off the excess pressure at the time of landing. The upper base 6 of the pneumatic carcass is made of a smaller diameter than the lower base 5 and is attached to the lower part of the fuselage of the aircraft 2 by means of a support element made in the form of the lower contour of the aircraft fuselage in the shape of the skin to ensure uniform pressure at the time of landing attached to the upper base 6 by fastening.

The ejector-type gas filling system for a pneumatic shock-absorbing frame can be placed in the lower part of the LA 2 fuselage and made in the form of one or more actuating elements of the gas filling system (air ejectors), which can be placed directly in the cavities of the upper 6 and lower 5 bases or inflatable spokes 7 The gas filling system is activated automatically when the BPS comes into operation or manually if necessary. The activation process may be mechanical, electrical, or electromechanical. The constructive solution of both the ejector type gas filling system itself and its activation system are not considered in the framework of this application, because relate to known means.

The process of gas filling and deployment of BSA should be fast, which is ensured by the characteristics of the ejector-type gas filling system. The total time required for deploying a rolled-up and packed BSA device, activating the gas filling system and full BSA inflation should not exceed 10 seconds.

The freely filled shell 8 may have cavities formed by horizontal and vertical partitions made in the form of honeycombs and having bypass openings.

Also, the device can be equipped with a foaming mechanism in communication with the cellular cavities of the shell 8 for filling them with quickly hardening or other foam.

The BSA device operates as follows.

Before flying LA 2, the parachute system 3 is compactly placed in a parachute container above the upper part of the fuselage, and BSA 1 for emergency landing of LA 2 is compactly packed using means to fix the folded position under the lower part of the fuselage in the region of its center of gravity.

The sequence of actions of the device during an emergency landing aircraft.

The crew and passengers are located during landing in the aircraft, as during the flight in a sitting position in regular places. In the event of an aircraft 2 crash, the pilot manually or automatically activates BPS 3 and BSA 1, a gas filling system that fills the closed pneumatic frame with active gas and outside air by means of air ejectors located in each isolated cavity: upper 6 and lower 5 bases and inflatable spokes 7, creating excess pressure by deploying and filling the shell 8, which can be made in the form of a single-volume or multi-section. During the descent, the aircraft 2 stabilizes and lands approximately in a horizontal position (figure 2).

At the time of landing, the inertial mass of the aircraft 2 through the upper membrane presses on the inflatable pneumatic carcass and the filled shell 8, which are designed to reduce the value of the shock load to a safe level, creating excess pressure that provides the quenching of the kinetic energy of the saved aircraft 2 with the crew and passengers at the time BSA touch with the ground.

Upon contact of the lower base 5 with the earth's surface, the kinetic energy of the aircraft 2 is extinguished due to the outflow of air from the cavity of the filled shell 8 through calibrated bypass holes 9. In this case, the quenching of kinetic energy is supplemented by deformation of the upper 6 and lower 5 bases. With such a sequentially combined process of depreciation, nonlinear quenching of the kinetic energy of the emergency landing aircraft 2 occurs. During the landing process, the BSA device provides effective braking of the aircraft 2 to a speed of less than 1.5 m / s.

Depending on the flight mass of the aircraft, the cavities of the filled damping shell 8 formed by internal soft horizontal and vertical partitions can be made in the form of honeycombs and have bypass openings.

BSA can also be (depending on the flight weight of the aircraft) equipped with a foaming mechanism that works simultaneously with gas filling of the pneumatic frame from the gas source and refills the cavity of the filled damping shell 8 with quick-hardening or other foam until the volume of plastic material required for amortization is formed.

Upon contact of the filled shell 8 having a honeycomb structure with the earth's surface, the kinetic energy of the emergency aircraft is extinguished by bleeding air from the cell cavities through the bypass holes between the horizontal and vertical soft internal partitions and the bypass holes of the outer surface of the shell 8.

Upon contact of the filled shell 8 filled with porous foam, the kinetic energy of the emergency aircraft is suppressed due to the deformation of this material.

The permissible amount of overload affecting a person and an aircraft during landing is achieved by changing the size of the holes in the lower part of the filled shell, the height of the creased layer of foam or porous foam.

This design allows you to increase the safety of the crew, passengers and the aircraft itself, to provide the opportunity to land on any surface, to reduce the loads acting on passengers and crew during landing, and also to save the aircraft after landing.

The invention meets the condition of patentability "industrial applicability", since its implementation is possible using existing means of production using known technological processes.

Claims (7)

1. High-speed cushioning system for emergency landing of an aircraft, mainly equipped with a high-speed parachute system, containing at least one gas source and a shell with an inflatable element, one of the bases of which is attached to the bottom of the fuselage of the aircraft, characterized in that the shell with the inflatable element is made in the form of a main inflatable device, which is a closed pneumatic frame shock-absorbing circuit connected to a gas source and consists of consisting of lower and upper inflatable toroidal bases, interconnected by inflatable needles, and an additional damping element, which is a freely filled casing, connected and placed between the above toroidal bases and spokes, and bypass holes are made on the outer side surface of the casing of the damping element, with the upper base of the pneumatic frame shock-absorbing circuit is made of a smaller diameter than the lower base, and is attached to the lower part of the fuselage of the predominant apparatus in the region of its center of gravity. 2. The system according to claim 1, characterized in that the gas source for the main inflatable device is made in the form of an automatically or manually activated gas filling system with one or more air ejectors. 3. The system according to claim 2, characterized in that the air ejectors of the gas filling system are located in the cavities of the upper and lower bases and / or racks of the closed pneumoframe shock-absorbing circuit made in a single-volume or multi-section. 4. The system according to claim 1, characterized in that the additional freely filled damping element is made one-volume or multi-section with cavities formed by solid soft radially located vertical partitions. 5. The system according to claim 4, characterized in that the cavities formed by horizontal and vertical soft partitions are made in the form of honeycombs and have bypass openings. 6. The system according to claim 4, characterized in that the additional damping element in the form of a closed shell located inside the pneumatic frame shock-absorbing circuit and associated with it, is filled using the foaming mechanism that communicates with it, quickly hardening or other foam. 7. The system according to claim 1, characterized in that the upper base of the pneumatic frame shock-absorbing circuit is attached to the lower part of the fuselage of the aircraft by means of a support element made in the form of a casing of the lower contour of the fuselage to ensure uniform load distribution at the time of landing.

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