Blended wing body aircraft

A wing-body fusion and aircraft technology, applied in the field of wing-body fusion aircraft, can solve problems such as reducing aircraft lift

Pending Publication Date: 2019-12-31
BOMBARDIER INC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

existing solutions to overcome this problem may cause adverse effects in terms of drag, weight and / or system complexity, and in some cases, may reduce aircraft lift

Method used

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  • Blended wing body aircraft
  • Blended wing body aircraft
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Embodiment Construction

[0031] Blended wing-body aircraft designs are sometimes referred to as "wing-body hybrid" aircraft designs. In this specification (including the claims), it is to be understood that the term "fused wing body" encompasses aircraft designs sometimes referred to as "blended wing body" aircraft designs or "non-interrupted chord" aircraft designs. A non-interrupted chord aircraft is an aircraft in which the change in chord length of multiple span-wise sections is substantially smooth spanwise from the plane of symmetry of the wing to the wing tip. Such aircraft are also characterized by a smooth change in thickness of the spanwise section from the plane of symmetry of the wing to the wingtip.

[0032] With reference to the accompanying drawings, and in particular to figure 1 , an exemplary blended wing body aircraft is shown at 10 . Aircraft 10 has a central fuselage 12 that may have lift generating properties. The center fuselage 12 has a front end and an opposite rear end. Ce...

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PUM

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Abstract

The invention discloses a blended wing body aircraft including a center body having a lower side and an upper side opposed to the lower side. The center body has a central chord extending from a leading edge to a trailing edge of the center body. The lower side has a lowest point located between a first location forward of a pivot point about which the aircraft rotates during take-off and a secondlocation aft of the pivot point. The first location is at a first distance corresponding to about 10% of a length of the central chord forward of the pivot point.

Description

technical field [0001] The present invention relates generally to aircraft, and more particularly to blended wing body aircraft. Background technique [0002] A blended wing body (BWB) aircraft is an aircraft with an airfoil center fuselage capable of generating lift. This differs from conventional aircraft, where the fuselage is generally cylindrical and produces very little lift. Some BWB aircraft may have less efficient pitch moment control because such aircraft typically have shorter lever arms from the control surfaces to the center of gravity compared to conventional empennage aircraft. Therefore, more force is required to obtain an equivalent pitch change than in conventional aircraft. Existing solutions to overcome this problem may cause adverse effects in terms of drag, weight and / or system complexity and, in some cases, may reduce aircraft lift. Therefore, there is still room for improvement. Contents of the invention [0003] In one aspect, there is provided...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C39/10B64C3/10
CPCB64C39/10B64C3/10B64C1/0009B64C2039/105B64C3/14B64C25/32
Inventor 伊恩·奇蒂克马克·拉科维茨托马斯·雷斯特
Owner BOMBARDIER INC
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