RU2111897C1 - Airbus - Google Patents

Abstract

FIELD: aeronautical engineering; manufacture of vertical takeoff and landing aircrafts. SUBSTANCE: airbus includes at least two fuselages connected by means of transversal beams of aerodynamic profile. Two stages of wings together with two rows of gas-turbine engines mounted in front of them form thrust lift complexes. Wings are secured between fuselages by means of cantilevers for turn about their longitudinal axes. Rear thrust lift complex is located above front one. EFFECT: extended ranged of service characteristics of airbus. 2 cl, 2 dwg

Description

 The invention relates to aircraft and can be used in the manufacture of aircraft with vertical take-off and landing.

 Wide-body airbuses are known, the take-off, flight and landing of which are possible only with their translational motion.

 Known aircraft (SU, patent, 1804415, CL B 64 C 39/04, 1993) containing two fuselages, a wing, where the fuselages are connected in the bow and tail.

 The disadvantage of the prototype is that it does not provide vertical take-off and landing.

 The purpose of the invention is the expansion of the operational characteristics of the prototype (or known airbus).

 This goal is achieved by the fact that in an airbus containing at least two fuselages connected by transverse beams of the aerodynamic profile, two cascades of wings, together with two rows of gas turbine engines placed in front of them, form traction and lifting systems, the wings are fixed by consoles between the fuselages with the possibility of rotation around of its longitudinal axes, the rear towing and lifting complex is located above the front.

 A positive effect is the ease of control of the wings, the ability to perform them with a thin profile, as they are attached at the edges, in the exclusion of disruption of air flows from the ends of the wings and their vibrations.

In FIG. 1 shows a plan view of an airbus;
in FIG. 2 is a longitudinal section A - A of FIG. 1.

 The fuselages 1 are connected by beams of the aerodynamic profile 2. The beams are installed with optimal angles of attack for horizontal flight. Gas turbine engines 3 are placed on the beams, with the front set of engines - under the front beam 2, and the rear - above the middle beam 2. Between the fuselages, their wings are mounted with the possibility of rotation around their longitudinal axes 4. Engines 3 are moved forward in front of the cascades of wings 4. Engines 3 with wings 4 form traction and lifting complexes. The airbus is equipped with steering wheels 5 and chassis 6.

 The invention works as follows.

 With vertical take-off and landing, the wings 4 are deployed at supercritical angles of attack (shown by dashed lines in Fig. 1) and create lift under the action of gas flows from engines 3. When moving to horizontal flight, wings 4 are set to the optimal angle of attack and together with the beams 2 support the airbus in the air. Gas and air flows from the front towing and lifting complex do not fall on the rear, which provides normal power to the rear row of engines 3 by air. Turns are provided by the action of the rudders 5.

Claims (2)

 1. An airbus containing at least two fuselages connected by transverse beams of an aerodynamic profile, characterized in that two cascades of wings together with two rows of gas turbine engines placed in front of them form traction and lifting systems, the wings are fixed by consoles between the fuselages with the possibility of rotation around their longitudinal axles, the rear towing and lifting complex is located above the front.  2. Airbus according to claim 1, characterized in that the engines of the front complex are installed under the front beam, and the rear one is above the middle beam.

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