Aircraft with integrated aerodynamic configuration

Abstract

The invention relates to multimode aircraft operated at supersonic and subsonic flight speeds in a wide range of flight altitudes. The invention is particularly applicable in multimode super-maneuverable aircraft capable of cruising at supersonic speed and having low radar signature. The technical effect to be achieved by the invention is to provide an aircraft which has low radar signature, is super-maneuverable at high angles of attack, has high aerodynamic efficiency at supersonic speeds while keeping high aerodynamic efficiency at subsonic modes, and can accommodate bulky cargo in its internal compartments. The integral aerodynamic configuration aircraft comprises fuselage (1) with strake (2), wing with panels (3) smoothly blended into fuselage (1), all-moving horizontal tail (AMHT) (4), and all-moving vertical tail (AMVT) (5). Mid-fuselage is flattened and formed longitudinally by a set of aerodynamic profiles. Engines are arranged in engine nacelles (6) spaced apart from each other horizontally, and centerlines of engines are oriented at an acute angle to the plane of symmetry of the aircraft in the direction of flight. Strake (2) comprises controlled pivoting portions (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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