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Aircraft wing body fairing and construction method thereof

A construction method and fairing technology, applied in the field of aircraft wing body fairing and its construction, can solve the problems of small fairing size, reduced aerodynamic resistance, inconvenient and precise control of curved surface shape, etc. Effect

Pending Publication Date: 2018-11-23
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The technical difficulties in the shape design of the wing-body fairing of existing business jets include: the fairing usually adopts a three-section shape design technology, which is not convenient to accurately control the change of the curved surface shape; in order to reduce aerodynamic drag, the size of the fairing is relatively small, which is not conducive to More fuel is loaded; there is no fairing belt between the fairing and the wing, which cannot further reduce the aerodynamic interference resistance
The above-mentioned technical difficulties hinder the development of wing body fairing shape design technology

Method used

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  • Aircraft wing body fairing and construction method thereof
  • Aircraft wing body fairing and construction method thereof
  • Aircraft wing body fairing and construction method thereof

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Embodiment 1

[0040] As a preferred embodiment of the present invention, with reference to the attached figure 1 to attach Figure 5 , the present embodiment discloses a kind of aircraft wing-body fairing, and the present embodiment comprises:

[0041] An aircraft wing-body fairing is characterized in that: it comprises a wing-body fairing main body and a fairing strip between the wing-body fairing main body and the wing, and the wing-body fairing main body successively includes a filling curved surface j49 and a conical sweeping curved surface h45 , conic sweep surface g43, conic sweep surface i47 and filled surface k51;

[0042] The fairing includes a bridging curved surface q67, a bridging curved surface r70 and a multi-section curved surface 76; there are two wing-body fairing main bodies, which are symmetrically arranged on both sides of the aircraft fuselage.

[0043] The total longitudinal length of the conic sweep surface h45 and the filling surface j49 is DI; the longitudinal len...

Embodiment 2

[0046] As a preferred embodiment of the present invention, with reference to the attached figure 1 to attach Figure 5 , present embodiment discloses a kind of construction method of aircraft wing body fairing, present embodiment comprises:

[0047] A construction method of an aircraft wing-body fairing, characterized in that it comprises the following steps:

[0048] A. Construct a coordinate system, take the vertex of the aircraft nose as the coordinate origin; the X-axis is located in the aircraft reference plane, parallel to the fuselage axis, and point to the tail; the Y-axis is perpendicular to the fuselage reference plane and points to the right, and the Z-axis is on the plane The vertical X-axis in the reference plane points upward;

[0049] B. Make the longitudinal guide line 1 of the wing-body fairing in the X-Z plane;

[0050] C. Make the longitudinal guide line 2 of the wing-body fairing in the X-Z plane;

[0051] D. Make the projection of the longitudinal guid...

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Abstract

The invention relates to the technical field of aircraft configuration, in particular to an aircraft wing body fairing and a construction method thereof. The aircraft wing body fairing comprises wingbody fairing main bodies, and rectifying belts respectively arranged between the wing body fairing main bodies and wings, wherein each wing body fairing main body sequentially comprises a filling curved surface j, a conical sweeping surface h, a conical sweeping curved surface g, a conical sweeping surface i, and a filling curved surface k; each rectifying belt comprises a bridge connection curvedsurface q, a bridge connection curved surface r and a multi-section curved surface; the two wing body fairing main bodies are available and are symmetrically arranged at the two sides of an aircraftfuselage. The aircraft wing body fairing provided by the invention is simple in principle and high in implementability, thus being suitable for being popularized and used.

Description

technical field [0001] The invention relates to the technical field of aircraft shape, in particular to an aircraft wing body fairing and a construction method thereof. Background technique [0002] The method of installing a fairing between the fuselage and the wing of a business jet is the most effective technical means to reduce the interference resistance of the wing body and increase the range and flight time of the business jet. The volume within the wing-body fairings can also be used to carry fuel. [0003] The technical difficulties in the shape design of the wing-body fairing of existing business jets include: the fairing usually adopts a three-section shape design technology, which is not convenient to accurately control the change of the curved surface shape; in order to reduce aerodynamic drag, the size of the fairing is relatively small, which is not conducive to More fuel is loaded; there is no fairing belt between the fairing and the wing, which cannot furth...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C7/00B64F5/00
CPCB64C7/00B64F5/00
Inventor 梁爽聂暾滕杰刘庆杰刘世钰
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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