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US 2003/0197091 A1Published application
Aircraft fuselage lift arrangement
AssigneeNone recorded
InventorManuel Munoz Saiz
Life of this patent
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AssigneeNone recorded
InventorManuel Munoz Saiz
Estimating the term…
The present invention is direct to an aircraft fuselage lift arrangement which includes an elongated vertically flattened oval cross section fuselage having a longitudinal axis; an upper longitudinal axis along the upper most portion of the fuselage and parallel to the longitudinal axis, a lower longitudinal axis parallel to the longitudinal axis and along the length of the bottom of the fuselage. The fuselage having a conical nose portion at one end and a conical tail portion at its opposite end. The nose portion of the fuselage having an upwardly inclined front wall extending upwardly from the bottom of the fuselage to at least the upper longitudinal axis of the fuselage. The tail portion of the fuselage having a downwardly declining rear wall extending from the upper longitudinal axis to the bottom of the fuselage. The fuselage also having a main landing gear.
An aircraft fuselage lift arrangement comprising:
An aircraft fuselage lift arrangement comprising:
Dependencies are inferred from the claim text.
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From the US filing history. Foreign family members aren’t listed.
Backward citations are indexed for grants only.
Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like: aerodynamic aspects
Aircraft not otherwise provided for: all-wing aircraft
Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like: fuselages characterised by special shapes
All-wing aircraft: of blended wing body type
Term end not estimated
1. Field of the Invention
On aircraft fuselages.
2. State of the Prior Art
FIG. 1 shows a side schematic view of the fuselage of the invention.
FIG. 2 shows schematic cross section view of a fuselage with the lift arrangement of the invention.
FIG. 3 shows schematic cross section view of a fuselage with the lift arrangement of the invention.
FIG. 1 shows the central fuselage (1), the conical nose (2), the conical tail (3) and the cross-sections of the same (A-A).
FIG. 2 shows the cross-section (A-A) which produces high lift in the nose.
FIG. 3 shows the cross-section (A-A) in the nose or in the tail, which is oval and vertically flattened, which produces more lift than the circular type.