Abstract: A system for increasing the thrust and power capabilities of a side-by-side vertical takeoff and landing vehicle to optimize the coaxial rotor performance. The system includes a first coaxial rotor spaced from an aircraft body and a second coaxial rotor spaced from the aircraft body and opposite the first coaxial rotor. The first coaxial rotor has a first top propeller aligned with a first bottom propeller along a first rotational axis. The second coaxial rotor having a second top propeller aligned with a second bottom propeller along a second rotational axis. A gyroscopic moment to maintain pitch stability is controlled by modulating the first and second top propellers, which have a different angular speed or different torque from the first and second bottom propellers, and tilting the first and second coaxial rotors towards the central axis with a common tilt angle and a common tilt rate.

Abstract: A system and method to control the stability and direction of a quad tilt vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) by manipulating the rotational speed of propellers at each rotor while simultaneously tilting the rotors in a 45 degree configuration related to a central axis for directional control. Each rotor is attached to a tilting mechanism configured to be symmetrically aligned at a 45 degree angle from a central axis to manipulate a directional angle of each rotor along a first and second axis. The first and fourth rotors are aligned on the first axis while the second and third rotors are aligned on the second axis. A controller includes a first control loop for manipulating the rotational speed of the propellers to control the aircraft balance and a second control loop for controlling lateral movement by tilting the rotors along the first and second axis.

Abstract: A system for increasing the thrust and power capabilities of a side by side vertical takeoff and landing vehicle and to optimize the coaxial rotor performance. The system including a first coaxial rotor spaced from an aircraft body and a second coaxial rotor spaced from the aircraft body and opposite the first coaxial rotor. The first coaxial rotor having a first top propeller aligned with a first bottom propeller along a first rotational axis. The second coaxial rotor having a second top propeller aligned with a second bottom propeller along a second rotational axis. A gyroscopic moment to maintain pitch stability is controlled by modulating the first and second top propellers having a different angular speed or different torque from the first and second bottom propellers and tilting the first and second coaxial rotors towards the central axis with a common tilt angle and a common tilt rate.