| 摘要 |
Systems and methods for vertical takeoff and/or landing are disclosed herein. An aerial vehicle may include a first propulsion unit and a second propulsion each rotatably connected to a body. The aerial vehicle may include a first wing and a second wing each rotatably connected to the body. And the aerial vehicle may include a control system configured to: position the first propulsion unit, the second propulsion unit, the first wing, and the second wing; operate the first propulsion unit and the second propulsion unit; and rotate the first propulsion unit, the second propulsion unit, the first wing, and the second wing. |
| 主权项 |
1. An aerial vehicle comprising:
a first propulsion unit and a second propulsion unit each rotatably connected to a body, wherein the first propulsion unit is located on a first side of the body, and wherein the second propulsion unit is located on a second side of the body; a first wing and a second wing each rotatably connected to the body, wherein the first wing is located on the first side of the body, and wherein the second wing is located on the second side of the body; and a control system configured to:
position the first propulsion unit, the second propulsion unit, the first wing, and the second wing, such that when the aerial vehicle is substantially perpendicular to the ground, the first propulsion unit is oriented substantially opposite to the second propulsion unit with respect to a first axis that is substantially perpendicular to a centerline of the aerial vehicle and the first wing is oriented substantially opposite to the second wing with respect to a second axis that is substantially perpendicular to the centerline of the aerial vehicle;operate the first propulsion unit and the second propulsion unit to cause the aerial vehicle to spin around the centerline of the aerial vehicle and thereby vertically lift off the ground; androtate the first propulsion unit about the first axis, the second propulsion unit about the first axis, the first wing about the second axis, and the second wing about the second axis, such that a vertical component of a thrust of the first propulsion unit and the second propulsion unit increases during the rotation, wherein after rotating for a certain period of time, the first propulsion unit is oriented substantially parallel to the second propulsion unit with respect to the first axis, the first wing is oriented substantially parallel to the second wing with respect to the second axis, and the aerial vehicle enters vertical flight, wherein in vertical flight, the thrust of the first propulsion unit and the second propulsion unit is substantially vertical. |
