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US 2016/0107741 A1Published application
Aircraft fuselages
AssigneeThe Boeing Company
InventorBruce Raymond Detert
Life of this patent
Estimating the term…
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.
Claims20
An aircraft comprising:
- a tail portion of a fuselage, the tail portion including 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;
- and
- a horizontal stabilizer extending from lateral surfaces of the tail portion along the second section such that a leading edge of the horizontal stabilizer is at an intersection of the first section and the second section and a trailing edge of the horizontal stabilizer is at an intersection of the second section and the third section.
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 substantially parallel second lateral surfaces, the third section aft of the second section and having third lateral surfaces converging inboard, the second section to extend from a leading edge of a horizontal stabilizer of the tail assembly to a trailing edge of the horizontal stabilizer of the tail assembly.
A method of enhancing aerodynamic performance comprising:
- directing first lateral surfaces of a first section of a fuselage of an aircraft to be converging inboard from a front to a rear of the first section;
- directing second lateral surfaces of a second section of the fuselage to be substantially parallel, the second section aft of the first section;
- directing third lateral surfaces of a third section of the fuselage to be converging inboard from a front to a rear of the third section, the third section aft of the second section;
- and
- coupling a horizontal stabilizer to the second section such that a leading edge of the horizontal stabilizer is at an intersection of the first section and the second section and a trailing edge of the horizontal stabilizer is at an intersection of the second section and the third section.
2 more elements
Dependencies are inferred from the claim text.