Lightweight vertical take-off and landing aircraft and flight control paradigm using thrust differentials
An aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in at least two dimensions relative to the horizontal during takeoff, and which may also control regular flight in some aspects by the use of differential thrust of the engines.
1. An aerial vehicle adapted for vertical takeoff and horizontal flight, said aerial vehicle comprising:
a main vehicle body;
one or more electric batteries;
a two dimensional array of three or more rotors pivotally connected to said main vehicle body, wherein each of said rotors comprise an electric motor;
a flight control system, said flight control system adapted control the attitude of said aerial vehicle while taking off vertically by varying the thrust of the three or more thrust producing elements, said flight control system adapted to control the attitude of said aerial vehicle while in horizontal flight by varying the thrust of the three or more thrust producing elements;
a first right side wing, wherein a first rotor is attached to said first right side wing above said first right side wing, and wherein a second rotor is attached to said first right side wing below said first right side wing, and wherein said first right side wing is pivotally attached to said main vehicle body; and
a second left side wing, wherein a third rotor is attached to said second left side wing above said second left side wing, and wherein a fourth rotor is attached to said second left side wing below said second left side wing, and wherein said second left side wing is pivotally attached to said main vehicle body.
2. The aerial vehicle of claim 1 wherein said first right side wing and said second left side wing are adapted to rotate from a first position adapted to vertical take-off and landing to a second position adapted for regular flight.
3. The aerial vehicle of claim 1 wherein said first right side wing is adapted to rotate around a first pivot axis, and wherein said second left side wing is adapted to rotate around a second pivot axis.
4. The aerial vehicle of claim 3 wherein said first pivot axis and said second pivot axis are parallel.
5. The aerial vehicle of claim 3 wherein said first pivot axis and said second pivot axis are coaxial.
6. The aerial vehicle of claim 2 further comprising a control system, said control system adapted to control the attitude of said aerial vehicle during take-off and landing around a first control axis parallel to the ground and a second control axis parallel to the ground by altering the power output of the electric motors of the rotors, wherein said first control axis and said second control axis are perpendicular to each other.
7. The aerial vehicle of claim 6 wherein said control system comprises attitude sensors adapted to sense the attitude of said aerial vehicle.
8. The aerial vehicle of claim 7 wherein said control system is adapted to alter the thrust produced by each rotor in response to attitude sensor data.