Electric power system architecture and fault tolerant VTOL aircraft using same
A power system with a reliability enhancing battery architecture for electric motors adapted for use in an aerial vehicle. Individual batteries may be used to power a subset two or more motors in systems with six or more motors, for example. Each motor may be powered may be powered by two or more subsets of batteries, allowing accommodation for motor failure. With a failed motor in a vertical take-off or landing mode, power may be diverted to other motors to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.
1. An electrically powered vertical take-off and landing aircraft, said aircraft comprising:
a left inboard propulsion assembly and a left outboard propulsion assembly. each of the left inboard and left outboard propulsion assemblies comprising an electric motor;
a right inboard propulsion assembly and a right outboard propulsion assembly,. each of the right inboard and right outboard propulsion assemblies comprising an electric motor;
a plurality of batteries, each of said plurality of batteries coupled to two or more of said electric motors; and
a flight control system adapted to:
operate the propulsion assemblies in a vertical thrust generating mode;
detect failure of a particular propulsion assembly;
reduce power to a corresponding propulsion assembly, the corresponding propulsion assembly being symmetrically located on an opposite side of a longitudinal centerline of said aircraft relative to the particular propulsion assembly; and
increase the power delivered to some or all of the remaining propulsion assemblies in order to maintain necessary thrust.
2. The aircraft of claim 1 further comprising a plurality of inverters, wherein each of said batteries is coupled to each of said electric motors through an inverter.
3. The aircraft of claim 1 wherein the left inboard propulsion assembly is offset from the left outboard propulsion assembly along the direction of the longitudinal centerline of said aircraft and the right inboard propulsion assembly is offset from the right outboard propulsion assembly along the direction of the longitudinal centerline of said aircraft.
4. The aircraft of claim 2 wherein the flight control system is adapted to autonomously adjust the power delivered by said batteries to said electric motors in the event of a motor failure to maintain a desired aircraft attitude.
5. The aircraft of claim 1 wherein the flight control system is adapted to autonomously adjust the power delivered by said batteries to said electric motors in the event of a battery failure to maintain a desired aircraft attitude.
6. The aircraft of claim 2 wherein the flight control system is adapted to autonomously adjust the power delivered by said batteries to said electric motors in the event of a battery failure to maintain a desired aircraft attitude.
7. The aircraft of claim 1 wherein each of said electric motors comprises a plurality of motor winding circuits, and wherein each of said winding circuits in said plurality of motor winding circuits in a motor are coupled to a different battery.
8. The aircraft of claim 2 wherein each of said electric motors comprises a plurality of motor winding circuits, and wherein each of said winding circuits in said plurality of motor winding circuits in a motor are coupled to a different battery.
9. The aircraft of claim 4 wherein each of said electric motors comprises a plurality of motor winding circuits, and wherein each of said winding circuits in said plurality of motor winding circuits in a motor are coupled to a different battery.
10. The aircraft of claim 6 wherein each of said electric motors comprises a plurality of motor winding circuits, and wherein each of said winding circuits in said plurality of motor winding circuits in a motor are coupled to a different battery.
11. The aircraft of claim 1 wherein the particular propulsion assembly is coupled to a first battery on a same side of the longitudinal centerline of the aircraft as the particular propulsion assembly and is coupled to a second battery on the opposite side of the longitudinal centerline of the aircraft from the particular propulsion assembly. and the flight control system is adapted to divert power from the first battery and the second battery from the particular propulsion assembly to some or all of the remaining propulsion assemblies.
12. The aircraft of claim 2 wherein the particular propulsion assembly is coupled to a first battery on a same side of the longitudinal centerline of the aircraft as the particular propulsion assembly and is coupled to a second battery on the opposite side of the longitudinal centerline of the aircraft from the particular propulsion assembly and the flight control system is adapted to divert power from the first battery and the second battery from the particular propulsion assembly to some or all of the remaining propulsion assemblies.
13. The aircraft of claim 7 wherein the particular propulsion assembly is coupled to a first battery on a same side of the longitudinal centerline of the aircraft as the particular propulsion assembly and is coupled to a second battery on the opposite side of the longitudinal centerline of the aircraft from the particular propulsion assembly, and the flight control system is adapted to divert power from the first battery and the second battery from the particular propulsion assembly to some or all of the remaining propulsion assemblies.
14. The aircraft of claim 1 wherein the flight control system is adapted to detect failure of a particular propulsion assembly by:
detecting that the electric motor in the particular propulsion assembly has stopped drawing current.
15. The aircraft of claim 1 wherein the flight control system is adapted to reduce power to the corresponding propulsion assembly by:
reducing power to be within a range of 0-20% of nominal power.
16. An electrically powered vertical take-off and landing aircraft, said aircraft comprising:
a left inboard propulsion assembly and a left outboard propulsion assembly, the left inboard propulsion assembly being offset from the left outboard propulsion assembly along the direction of a longitudinal centerline of said aircraft, each of the left inboard and left outboard propulsion assemblies comprising an electric motor;
a right inboard propulsion assembly and a right outboard propulsion assembly, the right inboard propulsion assembly being offset from the right outboard propulsion assembly along the direction of the longitudinal centerline of said aircraft, each of the right inboard and right outboard. propulsion assemblies comprising an electric motor;
a plurality of batteries, each of said plurality of batteries coupled to two or more of said electric motors; and
a flight control system adapted to:
operate the propulsion assemblies in a vertical thrust generating mode;
detect failure of a particular propulsion assembly of the left and right inboard and outboard propulsion assemblies;
reduce power to a corresponding propulsion assembly, the corresponding propulsion assembly being symmetrically located on an opposite side of the longitudinal centerline of said aircraft relative to the particular propulsion assembly; and
increase the power delivered to some or all of the remaining propulsion assemblies in order to maintain necessary thrust.
17. The aircraft of claim 16 further comprising a plurality of inverters, wherein each of said batteries is coupled to each of said electric motors through an inverter.
18. The aircraft of claim 16 further wherein the flight control system is further adapted to autonomously adjust the power delivered by said batteries to said electric motors in the event of a battery failure to maintain a desired aircraft attitude.
19. The aircraft of claim 16 wherein the particular propulsion assembly is coupled to a first battery on a same side of the longitudinal centerline of the aircraft as the particular propulsion assembly and is coupled to a second battery on the opposite side of the longitudinal centerline of the aircraft from the particular propulsion assembly, and the flight control system is adapted to divert power from the first battery and the second battery from the particular propulsion assembly to some or all of the remaining propulsion assemblies.
20. The aircraft of claim 16 wherein the flight control system is adapted to reduce power to the corresponding propulsion assembly by reducing power to he within a range of 0-20% of nominal power.