High-invisibility lifting-body configuration aircraft without horizontal tail

Abstract

The invention discloses a high-invisibility lifting-body configuration aircraft without a horizontal tail. The high- invisibility lifting-body configuration aircraft comprises a fuselage(1), a left main wing (21) and a right main wing (22) on both sides of the fuselage (1), a nozzle (3) located on the rear part of the fuselage, and air inlet ducts (41,42)located on the side parts of the fuselage (1), wherein a left winglet (51) is arranged at one end, away from the fuselage (1), of the left main wing (21), and a right winglet (52) is arranged at one end, away from the fuselage (1), of the right main wing (21); the appearance of the left winglet (51) is the same as the appearance of the right winglet (52); the camber angle of left winglet (51) is parallel to the camber angle of the lip of the air inlet duct (41) on the left part of the fuselage (1); and the camber angle of the right winglet (52) is parallel to the camber angle of the lip of the air inlet duct (42) on the right part of the fuselage (1). The high-invisibility lifting-body configuration aircraft without the horizontal tail disclosed by the invention is high in aerodynamic performance and good in invisibility effect.

Description

technical field [0001] The invention belongs to the technical field of stealth fighters, in particular to a high-stealth aircraft with no horizontal tail lifting body layout, which has strong aerodynamic performance and good stealth effect. Background technique [0002] The aircraft with no horizontal tail lifting body layout includes the aircraft with canard layout or tailless delta wing layout. In order to improve the yaw stability and yaw control of the aircraft with small aspect ratio, high lift and non-horizontal lift body layout, and to improve the stealth performance, an area smaller than the vertical tail area of ​​conventional fighter jets is set above the side of the tail nozzle of the rear fuselage. Class, flared twin vertical tails. [0003] The double vertical tail structure will produce a reverse pressure gradient on the upper surface of the tail of the fuselage, and the loss of lift coefficient will increase; the detachment vortex from the front of the fusela...

AI Technical Summary

Problems solved by technology

[0009] 3. In order to ensure the yaw control moment when the aircraft is in transonic and subsonic maneuvering flight and post-stall flight state, only axisymmetric vector nozzles can be used, and rectangular cross-section nozzles cannot be used to obtain better stealth performance

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