Aircraft emergency landing system using inflatable structures attached to the fuselage and a friction reduction system

Abstract

The present invention relates to an adaptable emergency landing system for an aircraft that is used in the event of the failure or non-use of one or more front or rear landing gear. This system includes one or more independent compartments installed in the lower skin of the aircraft fuselage, which are independent of the compartment and mechanism of the landing gear and are closed and flush with the fuselage under normal conditions.\nIn emergency landing conditions, the hatches of the said compartments are opened and inflatable structures are deployed from them. These structures are attached to the fuselage of the aircraft and create a large contact area with the runway surface. The system can also include an air supply and guidance system to create a flow or layer of compressed air under the inflatable structures and, if necessary, a friction reduction system including foam or slippery liquid spraying.\nThe system is designed so that in the event of a landing gear failure, only the corresponding inflatable structure is activated. In the event of several or all of the front and rear landing gears failure, by simultaneously deploying one inflatable structure in the front section and two or more inflatable structures in the rear section of the aircraft fuselage, a controlled and safe emergency landing is possible without Direct metal contact of the fuselage with the runway surface is provided. This invention has industrial applications in the aerospace field and can be used in the design of new aircraft or installed as an auxiliary system on existing aircraft.

Description

Description of the invention Title of the invention Adaptive aircraft emergency landing system based on independent inflatable structures, compressed air layer and friction reduction system Technical background of the relevant invention The present invention is in the technical field of flight safety and aircraft landing assistance systems, and specifically relates to emergency landing solutions for aircraft in the event of failure or non-use of one or more front or rear landing gear. Technical problem and stating the objectives of the invention In the event that one or more of the aircraft's landing gear is not deployed or is not functioning properly, direct metal-to-metal contact between the aircraft's fuselage and the runway surface can result in severe friction, wear, heat generation, instability, and increased risk of structural damage and fire. Existing systems rely primarily on the performance of the landing gear and do not provide a flexible and proactive solution for replacing them in the event of a complete or partial failure. The purpose of this invention is to provide an independent and adaptable system that enables safe and controlled emergency landing of an aircraft without dependence on the landing gear compartment or mechanism. A description of the state of the prior art and the history of developments related to the claimed invention. In the prior art, emergency landing solutions for aircraft have mainly involved structural reinforcement of the fuselage, use of slippery surfaces, or special operational measures on the runway. Inflatable systems or air cushioning are also known in non-aviation applications such as land or sea vehicles. However, none of these solutions has been presented as an integrated, independent, and adaptable system that can replace the operation of aircraft landing gear in the event of partial or complete failure. Providing a solution to an existing technical problem along with an accurate, sufficient, and integrated description of the invention The present invention introduces a flexible emergency landing system that includes one or more independent compartments embedded in the lower skin of the aircraft fuselage. These compartments are normally closed and flush with the fuselage and are not connected to the landing gear compartments. In an emergency landing, the hatches of the compartments open and the inflatable structures are removed from them. These structures are attached to the fuselage and create a large contact surface with the runway. Simultaneously or in stages, the air supply and guidance system creates a flow or layer of compressed air under the inflatable structures to reduce friction. If necessary, the friction reduction system, including the spraying of foam or a slippery liquid, is also activated. The system is designed so that if one landing gear fails, only the corresponding inflatable structure is activated, and if several or all landing gears fail, one inflatable structure is deployed simultaneously in the front section and two or more inflatable structures in the rear section of the aircraft fuselage. Explanation of shapes, maps and diagrams Figure 1 The general view shows the aircraft in normal operating condition, with the emergency landing aid system deactivated and no airbags or inflatable structures deployed. In this state, the aircraft's landing gear can be either closed or open, and the aircraft is in standard flight or ground conditions. Figure 2 It shows the aircraft at the beginning of an emergency landing scenario where the nose gear has not been deployed due to a technical failure, while the rear gears are in the extended position. At this stage, the nose cushion under the aircraft is in the initial deployment phase, but no compressed air flow or skid-floor spray has yet been activated, and the cushion is not in direct contact with the runway surface. Figure 3 The next stage shows the emergency landing, in which the nose cushion is fully deployed and in contact with the runway surface. In this situation, the friction reduction system, including the controlled release of compressed air and the spraying of skid pad, is activated to prevent damage to the cushion and ensure a smooth, controlled and safe landing on the runway. Figure 4 It represents an emergency landing situation in which none of the aircraft's landing gear is deployed. In this scenario, one pad is deployed under the forward section of the fuselage (nose) and two pads of equal size and symmetry are deployed at the rear of the fuselage and attached to the main fuselage. In this situation, the air pressure control system and foam spray are activated simultaneously to prevent wear and damage to the pads and allow the aircraft to glide in a controlled manner on the runway. Figure 5 It shows another hybrid emergency landing scenario where the nose gear is deployed but the rear gear is not deployed due to a technical fault. In this situation, the two rear cushions are deployed symmetrically under the rear fuselage and are compressed in a controlled manner after the aircraft touches down on the runway to maintain the aircraft's longitudinal balance and ensure a smooth and safe nose-to-ground contact. A clear and precise statement of the advantages of the claimed invention over prior inventions. Elimination of direct metal contact of the body with the band surface Increased emergency landing safety in partial or complete landing gear failure scenarios Complete independence of the system from the landing gear compartment and mechanism Adaptability to aircraft types and operating conditions Possibility of industrial development and application Description of at least one implementation method for implementing the invention In one implementation, after detecting the failure of one or more landing gear by the control unit or by the pilot's command, the independent compartments of the system are opened and the corresponding inflatable structures are deployed. Then the air supply system is activated and, if necessary, the friction reduction system is also activated to perform a controlled emergency landing of the aircraft. Explicit mention of the industrial application of the invention This invention has industrial application in the aerospace industry and can be used in the design of new aircraft or installed as an auxiliary system on existing aircraft to increase emergency landing safety.

Claims

Claims What is claimed: Claim 1) The adaptive aircraft emergency landing system includes at least one independent compartment embedded in the lower skin of the aircraft fuselage, which is normally closed and flush with the fuselage and is independent of the compartment and landing gear mechanism, so that in the event of non-functioning or non-use of one or more front or rear landing gears, the compartment hatch is opened and the inflatable structure is deployed, so that the deployed structure, by maintaining internal pressure and capable of bearing the load of the aircraft until a complete stop, acts as a load-bearing member replacing the landing gear function and prevents direct metal contact of the fuselage with the runway surface. Claim 2) The system according to claim 1, wherein the independent compartments are installed in the area under the nose of the aircraft or in the rear parts of the fuselage, such that in the event of complete failure of the front and rear landing gear, at least one structure is deployed in the front part and two or more structures are deployed in the rear part of the fuselage. Claim 3) The system according to claim 1 or 2, which includes an air supply system solely for inflating and maintaining the internal pressure of the inflatable structures during the emergency landing process until the aircraft is fully stabilized and does not play any role in generating lift for the aircraft. Claim 4) The system according to any one of the preceding claims, which includes a friction reduction system comprising a controlled spraying of foam or a slippery liquid in the area of ​​direct contact of the inflatable structure with the runway surface, in such a way that, without participating in the load bearing of the aircraft, it prevents wear of the structure and provides controlled sliding of the aircraft. Claim 5) The system according to any one of the preceding claims, which is designed in such a way that in the event of a landing gear failure, only the inflatable structure corresponding to the same area is activated, and in the event of a simultaneous failure of multiple landing gears, the corresponding structures are selectively and simultaneously deployed. Claim 6) The system according to any of the preceding claims, which has a control unit and whose activation is based on the status of the landing gear, signals from aircraft warning systems, or the pilot's manual command.

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