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US 2016/0101853 A1Published application
Vertical take off and landing aircraft
OwnerDavid Wayne Toppenberginventor
Life of this patent
Estimating the term…
Abstract
A vertical takeoff and landing aircraft is provided. The aircraft includes a fuselage having a first end, a second end, and a center of gravity in between the first end and the second end. Wings may extend from the side of the fuselage. The wings may include a canard at the first end, and a wing at the second end. The present invention may further include a pair of engines pivotally attached on either side of the fuselage and substantially aligning with the center of gravity.
Claims15
An aircraft comprising:
- a fuselage comprising a first end, a second end, and a center of gravity in between the first end and the second end;
- wings comprising at least a canard wing and a second wing extending from the fuselage;
- and
- a pair of engines attached on either side of the fuselage substantially aligning with the center of gravity,
- wherein the pair of engines are pivotally mounted and comprise a first pivot position in which the pair of engines propel the aircraft in a substantially horizontal direction, and a second pivot position in which the pair of engines propel the aircraft in hover and in a substantially vertical direction.
2 more elements
An aircraft comprising:
- a fuselage comprising a first end, a second end, and a center of gravity in between the first end and the second end;
- a canard wing at the first end of the fuselage;
- a second wing at the second end of the fuselage;
- and
- a pair of engines attached on either side of the fuselage substantially aligning with the center of gravity,
- wherein the pair of engines are pivotally mounted to the second wing and comprise a first pivot position in which the pair of engines propel the aircraft in a substantially horizontal direction, and a second pivot position in which the pair of engines propel the aircraft in a substantially vertical direction.
3 more elements
Dependencies are inferred from the claim text.