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Laminar flow control technology-based wing body fusion layout passenger plane layout method

A technology of wing-body fusion and layout method, which is applied in the field of passenger aircraft layout with wing-body fusion layout, can solve the problems of difficult application of large-scale high-speed aircraft, poor stability and maneuverability of the aircraft body, and achieves good laminar flow control effect and good three-dimensional flow. Axis stability and maneuverability, the effect of improving maneuverability and flight quality

Inactive Publication Date: 2021-04-16
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

Although the traditional wing-body fusion layout aircraft can reduce frictional resistance, the tailless layout makes the aircraft body less stable and maneuverable
Laminar flow control technology is restricted by many factors, it is difficult to apply on large high-speed aircraft

Method used

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  • Laminar flow control technology-based wing body fusion layout passenger plane layout method
  • Laminar flow control technology-based wing body fusion layout passenger plane layout method

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Embodiment Construction

[0030] This part is the embodiment of the present invention, which is used to explain and illustrate the technical solution of the present invention.

[0031] A passenger aircraft layout method based on the wing-body fusion layout of the laminar flow control technology, including the fuselage, wings and engine 16, the fuselage and the wings adopt the wing-body fusion layout, and the wings are divided into the passenger cabin section wing and the outer wing , the wing of the cabin section is integrated with the fuselage, the outer wing is arranged on both sides of the wing of the cabin section, the engine 16 is arranged at the rear of the fuselage, and a small V-shaped tail 12 is installed on the trailing edge of the wing of the cabin section; method.

[0032] The key methods of airliner layout include performance index design method, top-level parameter design method, wing plane layout design method, laminar flow control design method, control system design method and power sy...

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Abstract

The invention belongs to the technical field of aircraft design, and discloses a laminar flow control technology-based wing body fusion layout passenger plane layout method, which comprises a fuselage, wings and an engine, the fuselage and the wings adopt a wing body fusion layout, the wings are divided into cabin section wings and outer side wings, the cabin section wings are fused with the fuselage, the outer wings are arranged on the two sides of the cabin section wings, the engine is arranged on the rear portion of the fuselage, and the small V-shaped empennages are installed on the rear edges of the cabin section wings. The invention further discloses a passenger plane layout key method. According to the wing body fusion passenger plane designed by the invention, the frictional resistance is reduced by 46% compared with a conventional layout passenger plane, is reduced by 32% compared with the conventional wing body fusion layout passenger plane, the cruise lift-drag ratio reaches 28 and is increased by 47% compared with the conventional layout passenger plane, the adverse effect of increase of the attack angle and the speed on laminar flow transition is inhibited, and the drag reduction effect of a laminar flow control technology is fully exerted.

Description

technical field [0001] The invention belongs to the technical field of aviation aircraft design, and relates to a layout method of a passenger aircraft with wing-body fusion layout, in particular to a passenger plane layout method with wing-body fusion layout based on laminar flow control technology. Background technique [0002] The aerodynamic performance of modern large subsonic airliners is already very high, with a cruise lift-to-drag ratio of around 19, and there is limited room for improvement in aerodynamic efficiency. Wing-body fusion technology and laminar flow control technology are currently the two most effective drag reduction technologies. Although the traditional wing-body fusion layout aircraft can reduce frictional resistance, the tailless layout makes the aircraft body less stable and maneuverable. Restricted by many factors, laminar flow control technology is difficult to apply on large high-speed aircraft. Contents of the invention [0003] In order ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C39/10B64C3/36B64C5/00B64C9/18B64C9/00B64F5/00
Inventor 张声伟王延风谭玉婷丁兴志
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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