Aircraft fuselages

Patent metadata

Field	Value
Publication number	US-9216807-B2
Application number	US-201213659180-A
Country	US
Kind code	B2
Filing date	Oct 24, 2012
Priority date	Oct 24, 2012
Publication date	Dec 22, 2015
Grant date	Dec 22, 2015

Abstract

Aircraft fuselages are disclosed herein. An example apparatus includes a fuselage of an aircraft having a first section and a second section to which a tail assembly is to be coupled. The second section is aft of the first section and is to extend to at least a trailing edge of a horizontal stabilizer of the tail assembly. A first width of the first section decreases from a front to a rear of the first section, and a second width of the second section is substantially constant.

First claim

What is claimed is:

1. An apparatus, comprising:
a fuselage of an aircraft to which a tail assembly is to be coupled, the fuselage having a first section, a second section aft of the first section, and a third section aft of the second section, a first width of the first section decreasing from a front to a rear of the first section, a second width of the second section being substantially constant, and a third width of the third section decreasing from a front to a rear of the third section, the second section having opposing lateral surfaces that are parallel to a longitudinal axis of the fuselage, a horizontal stabilizer of the tail assembly extending from the fuselage such that a trailing edge of the horizontal stabilizer extends from the lateral surfaces of the second section at or near an intersection of the second and third sections and a leading edge of the horizontal stabilizer extends from the fuselage along the first section;
wherein the second section extends from the first section to the third section.

2. The apparatus of claim 1 wherein the lateral surfaces of the second section are substantially parallel to a longitudinal axis of a vertical stabilizer of the tail assembly.

3. An apparatus, comprising:
a portion of a fuselage to which a tail assembly is to be coupled, the portion of the fuselage including a first section, a second section and a third section, first lateral surfaces of the first section converging inboard, the second section aft of the first section and having second lateral surfaces that are opposite and parallel to each other, the third section aft of the second section and having third lateral surfaces converging inboard, a horizontal stabilizer of the tail assembly extending from the first and second lateral surfaces of the first and second sections such that a trailing edge of the horizontal stabilizer extends from the second lateral surfaces at or near an intersection of the second and third sections and a leading edge of the horizontal stabilizer extends from the first lateral surfaces on the first section;
wherein the second section extends from the first section to the third section.

4. The apparatus of claim 3 wherein at least a portion of the first section is to be disposed fore of a leading edge of the horizontal stabilizer.

5. The apparatus of claim 3 wherein a portion the first section is to be disposed aft of the leading edge of the horizontal stabilizer.

6. An apparatus, comprising:
a first section of a fuselage of an aircraft having a first shape such that lateral surfaces of the first section are converging from a front to a rear of the first section by more than ten degrees relative to a longitudinal axis of the fuselage, a vertical stabilizer is to be disposed along a portion of the first section;
a second section of the fuselage aft of the first section, the second section having a second shape such that lateral surfaces of the second section are opposite to each other and parallel to the longitudinal axis of the fuselage, the second section to extend to at least a trailing edge of a horizontal stabilizer; and
a third section aft of the second section, the third section having a third shape such that lateral surfaces of the third section converge from a front to a rear of the third section, the horizontal stabilizer coupled to the fuselage along the first and second sections such that a trailing edge of the horizontal stabilizer extends from the lateral surfaces of the second section at or near an intersection of the second and third sections and a leading edge of the horizontal stabilizer extends from the first section;
wherein the second section extends from the first section to the third section.

7. The apparatus of claim 6 , wherein the lateral surfaces of the third section are converging by more than ten degrees relative to the longitudinal axis of the fuselage.

8. The apparatus of claim 6 wherein the first section is to extend from fore of a leading edge of the horizontal stabilizer to aft of the leading edge of the horizontal stabilizer.

Assignees

• Boeing Co

Inventors

• Detert Bruce Raymond

Classifications

• B64C1/00 Primary

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title

• B64C5/02 Primary

  Tailplanes · CPC title

• B64C1/0009

  Aerodynamic aspects · CPC title

• B64C2001/0045

  Fuselages characterised by special shapes · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title