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US 2014/0110528 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.
Claims27
An apparatus, comprising:
- 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 aft of the first section and to extend to at least a trailing edge of a horizontal stabilizer of the tail assembly, 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.
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 second section to extend to at least a trailing edge of a horizontal stabilizer of the tail assembly, the third section aft of the second section and having third lateral surfaces converging inboard.
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;
- and
- 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 oriented ten degrees or less from being parallel to the longitudinal axis of the fuselage, the second section to extend to at least a trailing edge of a horizontal stabilizer.
A method, 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;
- and
- directing second lateral surfaces of a second section of the fuselage to be substantially parallel, the second lateral surfaces to be aft of the first section and to extend to at least a trailing edge of a horizontal stabilizer.
Dependencies are inferred from the claim text.