BATTERY AND ENGINE ARCHITECTURE FOR VTOL AIRCRAFT
Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft engineered to carry safely carry at least 500 pounds (approx. 227 kg). The aircraft may include a fuselage, at least one wing, one or more wing tips, a v-tail, one or more control surfaces, and a nacelle assembly comprising a static portion and a tilting portion. The tilting portion supports a rotor, all configured to tilt together for transition between flight modes. Control surfaces are positioned on the wing and tail and configured to be actuated between one or more deflection angle positions.
1 - 57 . (canceled)
58 . An electric powered vertical takeoff and landing (VTOL) aircraft, comprising:
a fuselage;
at least one wing mechanically coupled to the fuselage,
a first wing tip of the at least one wing on a first side of the fuselage,
a second wing tip of the at least one wing on a second side of the fuselage,
a v-tail;
at least first, second, third, and fourth tilt rotors configured to provide lift for the fuselage;
at least a first, second and third pair of control surfaces,
wherein:
the aircraft is configured to be operated by an onboard pilot,
the aircraft is capable of carrying a payload of at least 500 pounds,
the first and second pairs of control surfaces extend from an aft portion of the at least one wing,
the third pair of control surfaces extend from an aft portion of the v-tail,
the first tilt rotor is tiltably mounted on a first static nacelle, the first static nacelle extending from a front of the at least one wing between the fuselage and the first wing tip,
the second tilt rotor is tiltably mounted on a second static nacelle, the second static nacelle extending from a front of the at least one wing between the fuselage and the second wing tip,
the first pair of control surfaces are oppositely positioned on the first and second sides of the fuselage, wherein a first control surface of the first pair of control surfaces is at least partially located between the fuselage and the first tilt rotor, and a second control surface of the first pair of control surfaces is at least partially located between the fuselage and the second tilt rotor;
the second pair of control surfaces are oppositely positioned on the first and second sides of the fuselage, wherein a third control surface of the second pair of control surfaces is at least partially located between the first tilt rotor and the first wing tip, and a fourth control surface of the second pair of control surfaces is at least partially located between the second tilt rotor and the second wing tip;
the third pair of control surfaces are oppositely positioned on first and second sides of the v-tail, and
the first, second, and third pairs of control surfaces are configured to be actuated between one or more deflection angle positions.
59 . The electric powered VTOL aircraft of claim 58 , wherein a slot is formed between the aft portion of the at least one wing and at least one of the first and second pairs of control surfaces when the at least one of the first and second of control surfaces are actuated between the one or more deflection angle positions.
60 . The electric powered VTOL aircraft of claim 58 , wherein a slot is formed between the aft portion of the v-tail and the third pair of control surfaces when the third pair of control surfaces are actuated between the one or more deflection angle positions.
61 . The electric powered VTOL aircraft of claim 58 , wherein the one or more deflection angle positions range from −8 to +65 degrees.
62 . The electric powered VTOL aircraft of claim 58 , wherein the one or more deflection angle positions are selected from the group consisting of −8, −5, 0, +5, +22, and +65 degrees.
63 . The electric powered VTOL aircraft of claim 62 , further comprising a flexible upper surface seal configured to cover a connection between the at least one wing and at least one pair of the first and second pairs of control surfaces, thereby minimizing drag when the at least one of the first and second pairs of control surfaces has a deflection angle position of 0 degrees.
64 . The electric powered VTOL aircraft of claim 58 , wherein at least one of the first, second, and third pairs of control surfaces are segmented into multiple spanwise sections to reduce stresses induced by wing deformation.
65 . The electric powered VTOL aircraft of claim 58 , wherein at least one of the first, second, and third pairs of control surfaces rotates about a hinge.
66 . The electric powered VTOL aircraft of claim 65 , wherein the hinge is offset from the wing or v-tail surface such that when at least one pair of the first, second, and third pairs of control surfaces is deflected downward, a corresponding slot is formed.
67 . The electric powered VTOL aircraft of claim 66 , wherein at least one of the first, second, and third pairs of control surfaces are configured to form the corresponding slot when deployed to a deflection angle position of +22 degrees to allow airflow from the lower side of the wing or v-tail to pass through the slot and over the at least one of the first, second, and third pairs of control surfaces.
68 . The electric powered VTOL aircraft of claim 66 , wherein at least one of the first, second, and third pairs of control surfaces and the corresponding slot are configured to provide linear lift response to small deflection angles such that the at least one of the first, second, and third pairs of control surfaces function as ailerons for aircraft roll control.
69 . The electric powered VTOL aircraft of claim 58 , wherein the second pair of control surfaces do not form a slot between the aft portion of the at least one wing and the second pair of control surfaces when the second pair of control surfaces is actuated.
70 . The electric powered VTOL aircraft of claim 58 , wherein each of the control surfaces of the at least one of the first, second, and third pairs of control surfaces are independently actuated.
71 . The electric powered VTOL aircraft of claim 58 , wherein at least one of the first, second, and third pairs of control surfaces is configured to provide a sectional stall lift coefficient of at least 2.0.
72 . The electric powered VTOL aircraft of claim 58 , wherein at least one pair of the first, second, and third pairs of control surfaces is configured to deflect at least 5 degrees both up and down to function as an aileron for aircraft roll control.
73 . The electric powered VTOL aircraft of claim 58 , wherein at least one pair of the first, second, and third pairs of control surfaces comprise flaps.
74 . The electric powered VTOL aircraft of claim 58 , wherein the at least one wing comprises an outboard portion configured to fold relative to an inboard portion.
75 . The electric powered VTOL aircraft of claim 74 , wherein the outboard portion is foldable about a hinge line.
76 . The electric powered VTOL aircraft of claim 74 , wherein folding the outboard portion is actuated by an actuator.
77 . The electric powered VTOL aircraft of claim 58 , further comprising landing gear extending from at least one of the fuselage and the at least one wing.
78 . The electric powered VTOL aircraft of claim 58 , wherein pitch control of the aircraft during rotor borne flight is provided by a pitch moment generated by at least one of the first, second, third, and fourth tilt rotors.
79 . The electric powered VTOL aircraft of claim 58 , wherein pitch control of the aircraft during wingborne flight is provided by at least one of the first, second, or third pairs of control surfaces and a pitch moment generated by at least one of the first, second, third, and fourth tilt rotors.
80 . The electric powered VTOL aircraft of claim 58 , wherein the fuselage has a passenger compartment with at least one seat configured to seat a human.
81 . The electric powered VTOL aircraft of claim 58 , wherein the third pair of control surfaces have an area between 10%-100% that of the at least one wing.
82 . The electric powered VTOL aircraft of claim 58 , further comprising at least one canard, wherein the at least one canard includes a canard lifting surface.
83 . The electric powered VTOL aircraft of claim 82 , wherein the canard lifting surface has an area between 10%-100% that of the at least one wing.
84 . The electric powered VTOL aircraft of claim 58 , wherein at least one of the first, second, third, and fourth tilt rotors comprises a variable speed rotor.
85 . The electric powered VTOL aircraft of claim 58 , wherein the at least first, second, third, and fourth tilt rotors are powered by at least one electric motor.
86 . The electric powered VTOL aircraft of claim 258 , wherein the at least one electric motor is powered by at least one battery.
87 . An electric powered vertical takeoff and landing (VTOL) aircraft, comprising:
a fuselage;
at least one wing mechanically coupled to the fuselage,
a first wing tip of the at least one wing on a first side of the fuselage,
a second wing tip of the at least one wing on a second side of the fuselage,
a v-tail;
at least first, second, third, fourth, fifth, and sixth tilt rotors configured to provide lift for the fuselage;
at least a first, second and third pair of control surfaces,
wherein the aircraft is configured to be operated by an onboard pilot,
the aircraft is capable of carrying a payload of at least 500 pounds,
the first and second pairs of control surfaces extend from an aft portion of the at least one wing,
the third pair of control surfaces extend from an aft portion of the v-tail,
the first tilt rotor is tiltably mounted on a first nacelle, the first nacelle extending from a front of the at least one wing between the fuselage and the first wing tip,
the second tilt rotor is tiltably mounted on a second nacelle, the second nacelle extending from a front of the at least one wing between the fuselage and the second wing tip,
the third tilt rotor is tiltably mounted on a third nacelle, the third nacelle located at the first wing tip,
the fourth tilt rotor is tiltably mounted on a fourth nacelle, the fourth nacelle located at the second wing tip,
the fifth tilt rotor is tiltably mounted on a fifth nacelle and the sixth tilt rotor is tiltably mounted on a sixth nacelle, the fifth and sixth nacelles coupled to tips of the v-tail,
the first pair of control surfaces are oppositely positioned on the first and second sides of the fuselage, wherein a first control surface of the first pair of control surfaces is at least partially located between the fuselage and the first tilt rotor, and a second control surface of the first pair of control surfaces is at least partially located between the fuselage and the second tilt rotor,
the second pair of control surfaces are oppositely positioned on the first and second sides of the fuselage, wherein a third control surface of the second pair of control surfaces is at least partially located between the first tilt rotor and the first wing tip, and a fourth control surface of the second pair of control surfaces is at least partially located between the second tilt rotor and the second wing tip,
the third pair of control surfaces are oppositely positioned on first and second sides of the v-tail, and
the first, second, and third pairs of control surfaces are configured to be actuated between one or more deflection angle positions.