Aircraft nose with arrises

Abstract

The invention relates to an aircraft nose with arrises, which comprises an upper nose surface, the arrises, and the lower nose surface, the arrises divide the nose into the upper nose surface and the lower nose surface by means of large-curvature splines, and the upper nose surface and the lower nose surface are bridged by large-curvature curves; and the arrises are arranged on both sides of the nose, and extend from the front edge of the nose along a designed direction from the front to the back. The arrises delay and weaken the vortex strength of the nose, so that the maximum available attack angle and operability of an aircraft are effectively increased; moreover, the forward and anterolateral RCS (Radar Cross-Section) values of the aircraft are reduced, the distance at which the aircraft can be detected is reduced, and thereby the stealth performance and survivability of the aircraft are enhanced.

Description

Technical field [0001] The invention relates to the technical field of aircraft manufacturing, in particular to an aircraft nose with edges. Background technique [0002] In order to reduce the impact of shock waves, transonic and supersonic aircraft use a slender nose. In the case of a high angle of attack (greater than or equal to 30°), the air flow easily generates an asymmetric nose vortex in the nose. Towing backwards causes the aircraft to produce a yaw moment, and the yaw moment increases with the increase in the angle of attack, and even exceeds the corrective maneuvering torque that the aircraft can provide, thereby causing the aircraft to lose heading stability and maneuverability, endangering flight safety . Summary of the invention [0003] The technical problem solved by the present invention is to provide an aircraft nose with edges to solve the above-mentioned shortcomings in the background art. [0004] The technical problem solved by the present invention is reali...

AI Technical Summary

Problems solved by technology

[0002] In order to reduce the impact of shock waves, transonic and supersonic aircraft adopt a slender nose. It is easy to generate an asymmetrical nose vortex at the nose, and the nose vortex is dragged out backwards, prompting the aircraft to generate a yaw moment, and the yaw moment increases with the increase of the angle of attack, even exceeding the correction torque that the aircraft can provide , so that the aircraft loses directional stability and maneuverability, endangering flight safety

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