High-invisibility lifting-body configuration aircraft without horizontal tail

A lift body and flat tail technology, applied in the field of stealth fighter jets, can solve the problem of inability to adopt the stealth performance of a rectangular section nozzle, and achieve the effects of low tail modification resistance, reduced lift coefficient loss, and good lift-drag characteristics.

Inactive Publication Date: 2017-03-22
戈晓宁
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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

Method used

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  • High-invisibility lifting-body configuration aircraft without horizontal tail
  • High-invisibility lifting-body configuration aircraft without horizontal tail
  • High-invisibility lifting-body configuration aircraft without horizontal tail

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Embodiment Construction

[0024] Such as figure 1 , 2 , 3, the present invention's high-stealth non-horizontal lift body layout aircraft includes a fuselage 1, a left main wing 21 positioned at both sides of the fuselage 1 and a right main wing 22, a spout 3 positioned at the rear of the fuselage, and a fuselage 1 side. The air intakes 41, 42 at the top of the left main wing 21 are provided with a left winglet 51 at the end of the left main wing 21 away from the fuselage 1, and at the end of the right main wing 22 away from the fuselage 1, a right winglet 52 is provided. 51 has the same shape as the right winglet 52, the camber angle of the left winglet 51 is parallel to the camber angle of the lip of the air inlet 41 on the left side of the fuselage 1, and the camber angle of the right winglet 52 is parallel to that of the air inlet duct on the right side of the fuselage 1. 42 lip camber parallel.

[0025] The present invention changes the conventional double vertical tail structure into winglets wi...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C15/02B64C3/36
CPCB64C15/02B64C3/36
Inventor 戈晓宁
Owner 戈晓宁
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