Patent ID: 11964759
Assignee: nan
Field: Transport (Mechanical engineering)
Classification: CPC B | IPC B

Claim 0:
1. A convertiplane comprising:
a fuselage comprising a front horizontal wing and a tail unit;
a control system;
airfoil sections with aerodynamic control surfaces;
a front horizontal wing with aerodynamic control surfaces;
tail fins; and
motor propeller groups comprising propellers, the motor propellor groups being located such that the propellers are configured to rotate at tips of the front horizontal wing and on the tail unit,
wherein a center of aerodynamic pressure and a resulting thrust vector of the convertiplane are coincident and are mutually dynamically and statically scalarly controllable through the operation of the aerodynamic control surfaces and through control of the thrust vector of each of the motor propeller groups,
wherein the motor propeller groups located on the tips of the front horizontal front wing are configured to counter-rotate the propellers and to provide dynamic shifting of the center of pressure,
wherein the motor propeller groups comprise an axial degree of freedom and are configured such that a thrust vector, a rotation speed, and a blade pitch angle of each motor propeller group is independently controllable relative to the other motor propeller groups.