Aircraft with an integral aerodynamic configuration

Abstract

The invention relates to multimode aircraft which can be operated at supersonic and subsonic flying speeds in a wide range of flying altitudes. The primary field of use of the invention is multimode super-manoeuvrable aircraft capable of cruising at supersonic speed and having low radar visibility. The invention is intended to achieve the technical result of producing an aircraft which has low radar visibility, is highly manoeuvrable at large angles of attack, has a high aerodynamic quality at supersonic speeds while retaining a high aerodynamic quality in subsonic modes, and is capable of accommodating a large load in its internal holds. The aircraft with an integral aerodynamic configuration comprises a fuselage (1) with a leading-edge extension (2), a wing, the main planes (3) of which are continuously adjacent to the fuselage (1), a fully rotatable horizontal tail unit (FRHTU) (4), and a fully rotatable vertical tail unit (FRVTU) (5). The mid-fuselage is flattened and formed longitudinally by a set of aerodynamic profiles. The engines are arranged in engine nacelles (6) spaced apart from one another horizontally, and the axes of the engines are oriented at an acute angle to the plane of symmetry of the aircraft in the flying direction. The leading-edge extension (2) comprises controllable rotatable parts (8).

Description

technical field [0001] The present invention relates to a multi-mode aircraft that operates at supersonic and subsonic flight speeds over a wide range of flight altitudes. The invention finds particular application in multi-mode super-maneuverable aircraft capable of supercruising at supersonic speeds and having a low radar signature. Background technique [0002] The design of an air vehicle capable of performing missions over a wide range of altitudes and flight speeds, exhibiting supermaneuverability, and at the same time having a low radar signature is a difficult technical challenge. [0003] The aerodynamic configuration of the aircraft should provide maximum aerodynamic efficiency (increased lift component and reduced drag component) at subsonic and supersonic flight speeds, and ensure controllability at ultra-low flight speeds. The external shape of the airframe should provide a reduced radar signature. All of these requirements are contradictory, and there are tra...

AI Technical Summary

Problems solved by technology

[0018] - the use of fixed fins with rudders requires an increase in the necessary vertical tail area to provide directional stability in supersonic flight modes, which in turn leads to increased weight of the tail and, as a result, overall increased weight of the aircraft and increased resistance

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