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Airplane with tailcoat tail assembly and rear engine

An engine, jet engine technology, applied in the aircraft field, which can solve problems such as damage to installation complexity

Inactive Publication Date: 2014-12-24
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0014] - impairment in terms of installation complexity;

Method used

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  • Airplane with tailcoat tail assembly and rear engine
  • Airplane with tailcoat tail assembly and rear engine
  • Airplane with tailcoat tail assembly and rear engine

Examples

Experimental program
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Effect test

Embodiment Construction

[0058] as shown in perspective view as a non-limiting example figure 1 and according to different projections Figures 2a to 2c As shown above, an aircraft 1 according to the invention comprises an elongated fuselage 2, wings 3 fixed to the fuselage and a vertical tail 4 on a part of the fuselage 2 substantially behind the wings 3 fixed to the fuselage.

[0059] According to conventions used in the field of aircraft design, for the purposes of the description, aircraft 1 is related to the aircraft coordinate system defined by the following axes:

[0060] - the axis X, which corresponds to the longitudinal axis of the aircraft 1 and the fuselage 2, positively towards the front of the aircraft in the direction of flight;

[0061] - the axis Z, which corresponds to the vertical axis of the aircraft 1 , ie the axis perpendicular to the axis X in the plane of vertical symmetry XZ of the aircraft, which is oriented positively downwards of the aircraft;

[0062] - Axis Y, which is...

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PUM

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Abstract

An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage.

Description

technical field [0001] The invention belongs to the field of aircraft, in particular aircraft comprising a fuselage to which a set of empennages and an engine are fixed in the rear part of the fuselage. Background technique [0002] In the field of aircraft, in particular of commercial transport aircraft, it is known to arrange a propulsion engine on the fuselage and substantially in the axis of the fuselage in order to increase the number of propulsion engines, without the need to respect the axial vertical plane of the aircraft relative to the aircraft Increase this amount in pairs for the overall symmetry of . [0003] This method is generally used to increase the number of engines by two to three in the plane of symmetry of the aircraft combined with some engines under the wings, for example in the Lockeed 1011 or the Mac Donnell Douglas DC10, or in the plane of symmetry This engine in the plane is combined with a number of rear engines mounted symmetrically on the side...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D27/20
CPCY02T50/12Y02T50/44B64C2001/0045B64D27/20B64C1/26B64D29/04B64C1/068B64C5/06Y02T50/10Y02T50/40B64C1/0685
Inventor O·卡扎尔斯J·让蒂德拉萨涅
Owner AIRBUS OPERATIONS (SAS)
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