Reaction drive helicopter with cyclorotor propulsion and control

A rotary wing aircraft comprising:

• a main rotor system comprising a central hub, a plurality of rotors, and one or more mounting pylons attached thereto;
• the main rotor system configured to rotate about a main rotor spin axis that is substantially vertical;
• the plurality of rotors arrayed radially and symmetrically about the main rotor spin axis wherein each of the attached rotors comprises:
• a rotor blade comprising an airfoil shape in the plane perpendicular to its longest axis;
• one or more aerodynamic-lift-altering control surfaces;
• one or more cycloidal rotor thrust generator (cyclorotor) systems attached to the one or more mounting pylons connected to the central hub, each cyclorotor configured to spin about an axis that is not coincident with, but substantially parallel to the main rotor spin axis;
• at least one motor system configured to rotate one or more individual cyclorotors about their spin axes;
• at least one power system capable of delivering motive power to the one or more motor systems;
• a vehicle systems control computer configured to control the component parts of the rotary wing aircraft in a prescribed manner including the rotational speed, maximum pitch, and phase angle of maximum pitch of the cyclorotors, and the positions of the one or more aerodynamic-lift-altering control surfaces.

A rotary wing aircraft comprising:

• a main rotor system comprising a central hub, a plurality of rotors, and one or more mounting pylons attached thereto;
• the main rotor system configured to rotate about a main rotor spin axis that is substantially vertical;
• the plurality of rotors arrayed radially and symmetrically about the main rotor spin axis wherein each of the attached rotors comprises:
• a rotor blade comprising an airfoil shape in the plane perpendicular to its longest axis;
• one or more aerodynamic-lift-altering control surfaces;
• one or more cycloidal rotor thrust generator (cyclorotor) systems attached to one or more of the main rotors and each of the one or more cyclorotors configured to spin about an axis that is not coincident with, but substantially parallel to the main rotor spin axis;
• one or more cyclorotor systems attached to the one or more mounting pylons connected to the central hub, and each of the one or more cyclorotors configured to spin about an axis that is not coincident with, but substantially parallel to the main rotor spin axis;
• at least one motor system configured to rotate one or more individual cyclorotors about their spin axes;
• at least one power system capable of delivering motive power to the one or more motor systems;
• a vehicle systems control computer configured to control the component parts of the rotary wing aircraft in a prescribed manner including the rotational speed, maximum pitch, and phase angle of maximum pitch of the cyclorotors, and the positions of the one or more aerodynamic-lift-altering control surfaces.