Vertical take-off and landing aircraft and methods of taking-off, landing, and aircraft control

An aircraft comprising:

• a fuselage having a forward and aft direction and including an electrical power system;
• a forward and an aft right wing attached to the fuselage, the aft right wing being attached elevationally above and aft of the forward right wing,
• the forward and aft right wing having wingtips and being physically connect proximate the wingtips by a wingtip longitudinal structure;
• a forward and an aft left wing attached to the fuselage, the aft left wing being attached elevationally above and aft of the forward left wing,
• the forward and aft left wing having wingtips and being physically connect at the wingtips by a wingtip longitudinal structure;
• the forward and aft right wings and the forward and aft left wings including
• a plurality of ducted assemblies, each including a fixedly positioned electrical rotor to draw air from the forward direction through the ducted assembly and propel air out of the ducted assembly in the aft direction when powered by the electrical power system,
• the rotors and power system being sized to enable vertical take-off, forward flight, and vertical landing of the aircraft, and
• a segmented moveable flaperon assembly positioned in the aft direction relative to the rotor to direct propelled air to provide substantially forward thrust and dynamic lift in a first position and substantially vertical thrust and vertical lift in a second position.

A method of controlling an aircraft comprising:

• providing an aircraft having
• a fuselage having a forward and aft direction and including a power system,
• at least a first and second right wing attached to the fuselage,
• the second right wing being attached elevationally above and aft of the first right wing, and
• the first and second right wings each having wingtips and being physically connected proximate the wingtips by at least one wingtip longitudinal structure;
• at least a first and second left wing attached to the fuselage at least substantially symmetrically opposed to the corresponding first and second right wings,
• the second left wing being attached elevationally above and aft of the first left wing
• the first and second left wings each having wingtips and being physically connected proximate the wingtips by at least one wingtip longitudinal structure;
• the first and second right wings and first and second left wings including at least one ducted assembly including a fixedly positioned rotor, and
• a segmented moveable flaperon assembly positioned in the aft direction relative to the rotor;
• and
• powering the rotors via the power system to draw air from the forward direction through the ducted assembly and propel air out of the ducted assembly in the aft direction;
• positioning the moveable flaperon in a first position to direct propelled air from the rotor to provide substantially forward thrust and dynamic lift in a first position and in a second position to provide substantially vertical thrust and vertical lift.