Hybrid power systems for different modes of flight

Patent metadata

Field	Value
Publication number	US-11097839-B2
Application number	US-202017066050-A
Country	US
Kind code	B2
Filing date	Oct 8, 2020
Priority date	Oct 9, 2019
Publication date	Aug 24, 2021
Grant date	Aug 24, 2021

Abstract

A first power source, a second power source, and a power controller are provided, where a vehicle that includes the first power source, the second power source, and the power controller is capable of flying in a transitional mode between a hovering mode and a forward flight mode. The power controller selects one or more of the first power source and the second power source to power a rotor included in the vehicle during the transitional mode.

First claim

What is claimed is:

1. A hybrid power system, comprising:
a first power source that includes a high discharge rate battery;
a second power source that includes a high energy battery; and
a power controller, wherein:
the hybrid power system is included in a vehicle that flies in a transitional mode between a hovering mode and a forward flight mode; and
the power controller selects one or more of the first power source and the second power source to power a rotor included in the vehicle during the transitional mode, including by:
during a takeoff, the power controller determines when to switch from the first power source that includes the high discharge rate battery to the second power source that includes the high energy battery based at least in part on a measured current; and
during a landing, the power controller determines when to switch from the second power source that includes the high energy battery to the first power source that includes the high discharge rate battery based at least in part on a transition between flight state variables and independent of the measured current.

2. The hybrid power system recited in claim 1 , wherein the vehicle includes a vertical takeoff and landing (VTOL) vehicle that further includes:
a forward swept and tapered wing having a trailing edge; and
a tilt rotor that is attached to the trailing edge of the forward swept and tapered wing.

3. The hybrid power system recited in claim 1 , wherein:
the high discharge rate battery included in the first power source has an energy density less than or equal to 190 Wh/kg;
the high energy battery included in the second power source has an energy density greater than or equal to 235 Wh/kg; and
during the transitional mode, the power controller selects both the high discharge rate battery and the high energy battery to power the rotor.

4. The hybrid power system recited in claim 1 , wherein:
the high discharge rate battery included in the first power source has (1) a weight and (2) an energy density less than or equal to 190 Wh/kg;
the high energy battery included in the second power source has an energy density greater than or equal to 235 Wh/kg; and
the weight of the high discharge rate battery is less than or equal to 20% of a total battery weight.

5. The hybrid power system recited in claim 1 , wherein:
the hybrid power system further includes an internal combustion engine;
during the transitional mode, the power controller selects the internal combustion engine to power the rotor and de-selects the high discharge rate battery so that the high discharge rate battery does not power the rotor; and
during the hover mode, the power controller selects the internal combustion engine to power the rotor and selects the high discharge rate battery to power the rotor.

6. The hybrid power system recited in claim 1 , wherein:
the hybrid power system further includes an internal combustion engine;
during the transitional mode, the power controller selects the internal combustion engine to power the rotor and de-selects the high discharge rate battery so that the high discharge rate battery does not power the rotor;
during the hover mode, the power controller selects the internal combustion engine to power the rotor and selects the high discharge rate battery to power the rotor; and
the internal combustion engine is used to recharge the high discharge rate battery at least some of the time when the high discharge rate battery is de-selected and not powering the rotor.

7. The hybrid power system recited in claim 1 , wherein:
the hybrid power system further includes an internal combustion engine;
during the transitional mode, the power controller selects the internal combustion engine to power the rotor and de-selects the high discharge rate battery so that the high discharge rate battery does not power the rotor;
during the hover mode, the power controller selects the internal combustion engine to power the rotor and selects the high discharge rate battery to power the rotor; and
the high discharge rate battery has an energy density less than or equal to 190 Wh/kg.

8. The hybrid power system recited in claim 1 , wherein:
the hybrid power system further includes an internal combustion engine;
the rotor included in the vehicle includes a tilt rotor;
the vehicle further includes a cruise-only rotor;
during the forward flight mode, the power controller selects the internal combustion engine to power the cruise-only rotor; and
during hover mode and the transitional mode, the power controller de-selects the internal combustion engine so that the internal combustion engine does not power the cruise-only rotor.

9. The hybrid power system recited in claim 1 , wherein:
the hybrid power system further includes an internal combustion engine;
the rotor included in the vehicle includes a tilt rotor;
the vehicle further includes a cruise-only, pusher rotor that is located behind a tail in the vehicle;
during the forward flight mode, the power controller selects the internal combustion engine to power the cruise-only rotor; and
during the hover mode and the transitional mode, the power controller de-selects the internal combustion engine so that the internal combustion engine does not power the cruise-only rotor.

10. The hybrid power system recited in claim 1 , wherein:
the hybrid power system further includes an internal combustion engine;
the high discharge rate battery has an energy density less than or equal to 190 Wh/kg;
the high energy battery has an energy density greater than or equal to 235 Wh/kg;
the rotor included in the vehicle includes a tilt rotor;
the vehicle further includes a cruise-only rotor; and
during the forward flight mode, the power controller selects the internal combustion engine to power the cruise-only rotor; and
during the hover mode and the transitional mode, the power controller de-selects the internal combustion engine so that the internal combustion engine does not power the cruise-only rotor.

11. The hybrid power system recited in claim 1 , wherein:
the hybrid power system further includes an internal combustion engine;
the rotor included in the vehicle includes a tilt rotor;
the vehicle further includes a cruise-only rotor;
during the forward flight mode, the power controller selects the internal combustion engine to power the cruise-only rotor, wherein none of the high discharge rate battery, the high energy battery, nor the internal combustion engine powers the tilt rotor during the forward flight mode; and
during the hover mode and the transitional mode, the power controller de-selects the internal combustion engine so that the internal combustion engine does not power the cruise-only rotor.

12. A method for using a hybrid power system that includes a first power source, a second power source, and a power controller, comprising:
providing the first power source, the second power source, and the power controller, wherein the hybrid power system is included in a vehicle that flies in a transitional mode between a hovering mode and a forward flight mode; and
using the power controller to select one or more of the first power source and the second power source to power a rotor included in the vehicle during the transitional mode, including by;
during a takeoff, the power controller determines when to switch from the first power source that includes the high discharge rate battery to the second power source that includes the high energy battery based at least in part on a measured current; and
during a landing, the power controller determines when to switch from the second power source that includes the high ener

Assignees

• Kitty Hawk Corp

Inventors

• Sinha Pranay
• Vander Lind Damon

Classifications

• B64D27/357

  using batteries · CPC title

• B64C27/26

  characterised by provision of fixed wings · CPC title

• B64C29/00

  Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft (rotorcraft B64C27/00) · CPC title

• B64D27/33 Primary

  Hybrid electric aircraft · CPC title

• B64D27/34

  All-electric aircraft · CPC title