Sided performance coaxial vertical takeoff and landing (VTOL) UAV and pitch stability technique using oblique active tilting (OAT)

A side-by-side vertical takeoff and landing device comprising:

• a first coaxial rotor attached to a first articulating member extending from a first arm and having a first top propeller and a first bottom propeller with fixed pitch blades that are configured to rotate along a first rotational axis, the first arm is rotatably connected to a vehicle body along a longitudinal axis, the vehicle body including at least one wing;
• a second coaxial rotor attached to a second articulating member extending from a second arm and having a second top propeller and a second bottom propeller with fixed pitch blades that are configured to rotate along a second rotational axis, the second arm is rotatably connected to the vehicle body along the longitudinal axis, wherein the first and second to propellers have a first length and the first and second bottom propellers have a second length such that the first length is greater than the second length;
• and
• a controller for modulating the rotational speed and torque of the top and bottom propellers to control a pitch stability of the device, wherein during use a gyroscopic moment from the coaxial rotors is controlled to maintain pitch stability by modulating the first and second top propellers to have a different rotational speed from the first and second bottom propellers and tilting the first and second coaxial rotors towards a central axis along a length of the vehicle body with a common tilt angle and a common tilt rate, wherein the first and second coaxial rotors are controlled to rotate the first and second top propellers with common rotational torque and the first and second bottom propellers with common rotational torque.

A method of stabilizing a side-by-side vertical take off and landing vehicle comprising:

• providing a first coaxial rotor spaced from a vehicle body and a second coaxial rotor spaced from the vehicle body and opposite the first coaxial rotor along a common axis, the vehicle body extends along a longitudinal axis and includes at least one rear wing;
• rotating a first top propeller at the same angular speed and torque as a second top propeller, wherein the first and second to propellers have a first length and the first and second bottom propellers have a second length such that the first length is greater than the second length;
• rotating a first bottom propeller at the same angular speed and torque as a second bottom propeller;
• and
• controlling a gyroscopic moment from the coaxial rotors of the vehicle by a controller to maintain pitch stability by modulating the first and second top propellers to have a different rotational speed from the first and second bottom propellers and tilting the first and second coaxial rotor towards a central axis along a length of the vehicle body with a common tilt angle and a common tilt rate during use to improve the pitch stability and increase thrust and power capabilities of the vehicle,
• wherein the first top propeller and the second top propeller rotate with a common rotational speed and the first bottom propeller and the second bottom propeller rotate with a common rotational speed.