RU1816718C - High-payload flying vehicle - Google Patents

Abstract

The invention relates to aeronautical engineering, in particular to transport aircraft. The aim of the invention is to increase the coefficient of extensive load. The heavy-load aircraft contains side fuselages 1 and a central fuselage 2 with a crew cabin, a profiled bearing surface 4 in the form of a delta with a slot, relative to which the position of the fuselage 2 is regulated by movement along the longitudinal axis, engines 6 and blocks consisting of nacelles 7 and additional forks of the chassis located on the bearing surface 4, the front 9 and rear 10 of the chassis mounted on three fuselages, plumage 11, stiffeners on the bearing surface and a quick coupler e zhah hull 13 by kotbryh accomplished fuselage ments contact with the supporting surface. 5 ill.

Description

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The invention relates to aircraft manufacturing, in particular to the layout of aircraft, mainly for transport purposes and can be used to transport passengers and all kinds of goods in the national economy.

The purpose of the invention is to increase the coefficient of extensive load of an airplane.

The goal is achieved in that the operations of unloading and loading are eliminated, and therefore, the number of hours is reduced simply due to the fact that when the aircraft is made of three fuselages, fastened during the transport of goods by an autonomous profiled bearing surface - a wing in the shape of a double delta sweeps with engines mounted on it and additional landing gear supports, the supporting surface - the wing is disconnected by means of a quick disconnect from the fuselages, allowing their replacement in advance e-loaded hull typical Jamie, just as is done for the carriage of goods by rail.

In FIG. 1 depicts a large-capacity aircraft, side view; in FIG. 2 - aircraft, front view; in FIG. 3 is a profiled bearing surface with engines and additional landing gear, front view; in FIG. 4 - front fusel g, front view; in FIG. 5 - aircraft, top view,

The heavy-load aircraft contains side fuselage 1 and a central fuselage 2 with a crew cabin 3, a profiled supporting surface 4 in the form of a delta with a slot 5, relative to which the position of the fuselage 2 is regulated by movement along the longitudinal axis, engines 6 and blocks consisting of gondolas 7 and additional fork struts of the chassis 8 located on the supporting surface 4, the front chassis 9 and the rear chassis 10 mounted on three fuselages, plumage 11, stiffeners 12 on the bearing surface 4 and quick-connect connections 13 on the fuselages, through which the fuselage is in contact with the bearing surface.

The transportation of goods is as follows. Before landing the aircraft, the front landing gear 9 and the rear landing gear 10 of the central fuselage 2 and the side fuselage 1 are released. When landing, touch the concrete strip first, the rear landing gear 10 of the side fuselage 1, then the rear landing gear 10 of the central fuselage 2, and a little later, the front landing gear

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9 side fuselages - 1 and, finally, the front landing gear 9 of the central fuselage 2.

After the aircraft is stopped and the engines 6 are turned off, eight-wheel additional landing gears of the landing gear 8 are lowered from the nacelles 7 and the quick disconnect connections of the fuselages 1 and 2 with the profiled bearing surface 4, consisting of stiffeners 12 and devices 13, are opened. fuselage assignments 1 and 2, if necessary, are partially or fully towed to a specialized platform for unloading, and pre-loaded standard fuselages are rolled on front and rear wheels chassis 9 and 10 in tow to the bearing surface - wing 4. Using stiffeners 12 located on the wing 4, and devices 13 located on the fuselages 1 and 2, the fuselage 1 and 2 are connected to the wing 4. Central 1 and lateral fuselage 2 have the ability to move along the longitudinal axis of the aircraft, which provides longitudinal alignment of fuselages 1 and 2 relative to wing 4, the ability to move the central fuselage 2 with empennage 11 relative to wing 4 is due to the presence of a slot 5 in wing 4. Transverse alignment is ensured by stnym manner due to the thrust of the engine, ailerons, etc.

Replacing the fuselage is not necessary. The need for replacement depends on the type of transport, the nature of the cargo, the load on the fuselage, and other factors.

After the fuselages 1 and 2 are docked with the wing 4, the additional landing gear 8 are retracted into the nacelles 7, the crew is located in the cockpit 3 of the central fuselage 2. Engines 6 are turned on. The take-off of the aircraft is carried out in the reverse order. First, the front landing gear 9 of the central fuselage 2 is torn off from the runway, then the front landing gear 9 of the side fuselage 1 is torn off, after which the rear landing gear 10 at the beginning of the central fuselage 2 and then the rear landing gear 10 of the side fuselage 1 are torn off. stability during take-off and landing.

The improvement of economic indicators in the proposed aircraft heavy duty in comparison with the known due to:

an increase in the coefficient of extensive load, which characterizes the degree of use of the aircraft and represents the ratio of the number of hours of operation of the aircraft (in flight) for the reporting period to the total calendar number of hours of this period;

a decrease in the cost of fuselages due to the lack of engines on them, since the engines are placed on a bearing surface;

an increase in the assortment of transported goods - the fuselage can be passenger and modular.

Claims (1)

The claims Heavy-duty aircraft containing at least two fuselages with a chassis and a wing with engines, characterized in that, in order to increase the coefficient of extensive load, the fuselage is connected to the wing by means of a quick coupler, and the wing is equipped with additional landing gears and is located above the fuselage. a ppq vP9 3 M 70 S Y S 70 Fig. 1 Fig.Z FIG. G