Battery and engine architecture for VTOL aircraft
Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.
1 . An electric powered VTOL aircraft capable of carrying a payload of at least 500 pounds, comprising:
a fuselage;
at least one wing mechanically coupled to the fuselage;
a first nacelle mechanically coupled to the at least one wing on a first side of the fuselage and having a first static portion that is fixed with respect to the at least one wing and a first tilting portion that is tiltable with respect to the at least one wing;
first and second electric motors mechanically coupled to the first tilting portion and configured to tilt with the first tilting portion;
a first rotor mechanically coupled to the first tilting portion and configured to tilt with the first tilting portion, wherein the first and second electric motors are configured to rotate the first rotor;
a first battery configured to power the first electric motor; and
a second battery configured to power the second electric motor;
wherein the first battery is located in one of the first nacelle or the at least one wing.
2 . The electric powered VTOL aircraft of claim 1 , wherein the second battery is located in the other of the first nacelle or the at least one wing.
3 . The electric powered VTOL aircraft of claim 1 , wherein the first battery is located in the at least one wing.
4 . The electric powered VTOL aircraft of claim 3 , wherein the first battery is longer in a direction perpendicular to the fuselage than in a direction parallel to the fuselage.
5 . The electric powered VTOL aircraft of claim 1 , wherein the first battery is located in the first nacelle.
6 . The electric powered VTOL aircraft of claim 5 , wherein the first battery is longer in a direction parallel to the fuselage than in a direction perpendicular to the fuselage.
7 . The electric powered VTOL aircraft of claim 1 , wherein the first rotor is configured to tilt with respect to the first static portion of the first nacelle by at least 70°.
8 . The electric powered VTOL aircraft of claim 1 , further comprising:
a second rotor, a third rotor, and a fourth rotor.
9 . The electric powered VTOL aircraft of claim 8 , wherein three of the first rotor, the second rotor, the third rotor, and the fourth rotor are capable of providing at least 70% of a lifting force required to lift the electric powered VTOL aircraft carrying the payload of at least 500 pounds.
10 . The electric powered VTOL aircraft of claim 8 , further comprising:
a tail mechanically coupled to the fuselage, wherein
the second rotor is mechanically coupled to the at least one wing on a second side of the fuselage;
the third rotor is mechanically coupled to the tail on the first side of the fuselage; and
the fourth rotor is mechanically coupled to the tail on the second side of the fuselage.
11 . The electric powered VTOL aircraft of claim 10 , wherein:
the third rotor is mechanically coupled to a first end of the tail on the first side of the fuselage; and
the fourth rotor is mechanically coupled to a second end of the tail on the second side of the fuselage.
12 . The electric powered VTOL aircraft of claim 10 , wherein
the second rotor is tiltable with respect to the at least one wing;
the third rotor is tiltable with respect to the tail; and
the fourth rotor is tiltable with respect to the tail.
13 . The electric powered VTOL aircraft of claim 11 , further comprising:
a second nacelle mechanically coupled to the at least one wing on a second side of the fuselage and having a second static portion that is fixed with respect to the at least one wing and a second tilting portion that is tiltable with respect to the at least one wing;
third and fourth electric motors mechanically coupled to the second tilting portion and configured to tilt with the second tilting portion;
a second rotor mechanically coupled to the second tilting portion and configured to tilt with the second tilting portion, wherein the third and fourth electric motors are configured to rotate the second rotor;
a third battery configured to power the third electric motor; and
a fourth battery configured to power the fourth electric motor;
wherein the third battery is located in one of the second nacelle or the at least one wing.
14 . The electric powered VTOL aircraft of claim 13 , wherein the fourth battery is located in the other of the second nacelle or the at least one wing.
15 . The electric powered VTOL aircraft of claim 11 , wherein the first battery comprises one of a Li-ion battery, Li-Polymer battery, or Li-chemical battery.
16 . The electric powered VTOL aircraft of claim 11 , wherein the first battery comprises a specific energy density of about 100 kWh/lb.
17 . A method of operating an electric powered VTOL aircraft capable of carrying a payload of at least 500 pounds, the electric powered VTOL aircraft having a fuselage, at least one wing mechanically coupled to the fuselage, a first nacelle mechanically coupled to the at least one wing on a first side of the fuselage and having a first static portion that is fixed with respect to the at least one wing and a first tilting portion that is tiltable with respect to the at least one wing, first and second electric motors mechanically coupled to the first tilting portion and configured to tilt with the first tilting portion, a first rotor mechanically coupled to the first tilting portion and configured to tilt with the first tilting portion, a first battery located in one of the first nacelle or the at least one wing and configured to power the first electric motor, a second battery configured to power the second electric motor, wherein the first and second electric motors are configured to rotate the first rotor, the method comprising:
in flight, rotating the first rotor by the first electric motor and the second electric motor,
powering the first electric motor by the first battery; and
powering the second electric motor by the second battery.
18 . The method of claim 17 , wherein the second battery is located in the other of the first nacelle or the at least one wing.
19 . The method of claim 17 , wherein the first battery is located in the at least one wing.
20 . The method of claim 19 , wherein the first battery is longer in a direction perpendicular to the fuselage than in a direction parallel to the fuselage.
21 . The method of claim 17 , wherein the first battery is located in the first nacelle.
22 . The method of claim 21 , wherein the first battery is longer in a direction parallel to the fuselage than in a direction perpendicular to the fuselage.
23 . The method of claim 17 , further comprising tilting the first rotor with respect to the first static portion of the first nacelle by at least 70°.
24 . The method of claim 17 , wherein the electric powered VTOL aircraft further comprises:
a second rotor, a third rotor, and a fourth rotor.
25 . The method of claim 24 , wherein three of the first rotor, the second rotor, the third rotor, and the fourth rotor are capable of providing at least 70% of a lifting force required to lift the electric powered VTOL aircraft carrying the payload of at least 500 pounds.
26 . The method of claim 24 , wherein the electric powered VTOL aircraft further comprises:
a tail mechanically coupled to the fuselage, wherein
the second rotor is mechanically coupled to the at least one wing on a second side of the fuselage;
the third rotor is mechanically coupled to the tail on the first side of the fuselage; and
the fourth rotor is mechanically coupled to the tail on the second side of the fuselage.
27 . The method of claim 26 , wherein:
the third rotor is mechanically coupled to a first end of the tail on the first side of the fuselage; and
the fourth rotor is mechanically coupled to a second end of the tail on the second side of the fuselage.
28 . The method of claim 26 , wherein
the second rotor is tiltable with respect to the at least one wing;
the third rotor is tiltable with respect to the tail; and
the fourth rotor is tiltable with respect to the tail.
29 . The method of claim 27 , wherein the electric powered VTOL aircraft further comprises:
a second nacelle mechanically coupled to the at least one wing on a second side of the fuselage and having a second static portion that is fixed with respect to the at least one wing and a second tilting portion that is tiltable with respect to the at least one wing;
third and fourth electric motors mechanically coupled to the second tilting portion and configured to tilt with the second tilting portion;
a second rotor mechanically coupled to the second tilting portion and configured to tilt with the second tilting portion, wherein the third and fourth electric motors are configured to rotate the second rotor;
a third battery located in one of the second nacelle or the at least one wing and configured to power the third electric motor; and
a fourth battery configured to power the fourth electric motor;
the method further comprising:
in flight, rotating the second rotor by the third electric motor and the fourth electric motor,
powering the third electric motor by the third battery; and
powering the fourth electric motor by the fourth battery.
30 . The method of claim 29 , wherein the fourth battery is located in the other of the second nacelle or the at least one wing.