Parallel hybrid electric vertical takeoff and landing aircraft
A vertical takeoff and landing aircraft, includes a main rotor system, a gearbox mechanically connected to the main rotor system, a first gas turbine engine mechanically connected to the gearbox, a first electrical motor-generator mechanically connected to the first gas turbine engine and mechanically connected to the gearbox, a second electrical motor-generator mechanically connected to the gearbox, a third electrical motor electrically connected to the second electrical motor-generator and mechanically connected to an anti-torque device, the third electrical motor configured to provide mechanical power to the anti-torque device, and a plurality of power-controller interface units. The plurality of power-controller interface units are configured to, during a first phase of flight, control the first gas turbine engine and the first electrical motor-generator to provide mechanical power to the gearbox, and control the second electrical motor-generator to provide electrical power to the third electrical motor.
1 . A vertical takeoff and landing aircraft, comprising:
a main rotor system;
a gearbox mechanically connected to the main rotor system;
a first gas turbine engine mechanically connected to the gearbox;
a first electrical motor-generator mechanically connected to the first gas turbine engine and mechanically connected to the gearbox;
a second electrical motor-generator mechanically connected to the gearbox;
a third electrical motor electrically connected to the second electrical motor-generator and mechanically connected to an anti-torque device, the third electrical motor configured to provide mechanical power to the anti-torque device, wherein the third electrical motor is not mechanically connected to the gearbox; and
a plurality of power-controller interface units, wherein the plurality of power-controller interface units are configured to:
in a first operational mode associated with a first phase of flight, control the first gas turbine engine and the first electrical motor-generator to provide mechanical power to the gearbox, and control the second electrical motor-generator to provide electrical power to the third electrical motor.
2 . The vertical takeoff and landing aircraft of claim 1 , wherein the plurality of power-controller interface units are configured to:
in a second operational mode associated with a second phase of flight, control the first gas turbine engine to provide mechanical power to the gearbox, control the first electrical motor-generator to provide electrical power to a stored energy source, and control the second electrical motor-generator to provide electrical power to the third electrical motor.
3 . The vertical takeoff and landing aircraft of claim 1 , further comprising:
a second gas turbine engine mechanically connected to the gearbox; and
a fourth electrical motor-generator mechanically connected to the second gas turbine engine and mechanically connected to the gearbox.
4 . The vertical takeoff and landing aircraft of claim 3 , wherein the plurality of power-controller interface units are configured to:
in a third operational mode associated with a third phase of flight, control the first gas turbine engine, the second gas turbine engine, and the first electrical motor-generator to provide mechanical power to the gearbox, and control the fourth electrical motor-generator to provide electrical power to the third electrical motor;
wherein the plurality of power-controller interface units are configured to enter the third operational mode in response to detecting a failure at the second electrical motor-generator.
5 . The vertical takeoff and landing aircraft of claim 3 , wherein the plurality of power-controller interface units are configured to:
in a third operational mode associated with a third phase of flight, control the first gas turbine engine, the second gas turbine engine, the first electrical motor-generator, and the second electrical motor-generator to provide mechanical power to the gearbox;
wherein the plurality of power-controller interface units are configured to enter the third operational mode in response to detecting a failure at the fourth electrical motor-generator.
6 . The vertical takeoff and landing aircraft of claim 3 , wherein the plurality of power-controller interface units are configured to:
in a fourth operational mode associated with a fourth phase of flight, control the first gas turbine engine, and the first electrical motor-generator, and the fourth electrical motor-generator to provide mechanical power to the gearbox, and control the second electrical motor-generator to provide electrical power to the third electrical motor.
7 . The vertical takeoff and landing aircraft of claim 6 , wherein the plurality of power-controller interface units are configured to enter the fourth operational mode in response to detecting a failure at the second gas turbine engine.
8 . The vertical takeoff and landing aircraft of claim 7 , wherein the plurality of power-controller interface units are configured to:
operate the first gas turbine engine at a first power rating in the first operational mode; and
operate the first gas turbine engine at a second power rating in the fourth operational mode;
wherein the second power rating is higher than the first power rating.
9 . The vertical takeoff and landing aircraft of claim 7 , wherein the plurality of power-controller interface units are configured to:
operate the first electrical motor-generator at a first current level in the first operational mode; and
operate the first electrical motor-generator at a second current level in the fourth operational mode;
wherein the second current level is greater than the first current level.
10 . The vertical takeoff and landing aircraft of claim 1 , wherein each power-controller interface unit includes a flight control computer and an integrated-converter-controller.
11 . The vertical takeoff and landing aircraft of claim 10 , wherein the flight control computer is configured to send control signals to a respective gas turbine engine to manage a power output of the respective gas turbine engine.
12 . The vertical takeoff and landing aircraft of claim 10 , wherein the flight control computer is configured to send control signals to a respective electrical motor-generator to manage a power output of the respective electrical motor-generator.
13 . The vertical takeoff and landing aircraft of claim 1 , wherein the third electrical motor includes triple-redundant integrated-converter-controllers.
14 . The vertical takeoff and landing aircraft of claim 13 , further comprising a plurality of power management units, each power management unit configured to provide electrical power from a stored energy source to a respective power-interface control unit.
15 . The vertical takeoff and landing aircraft of claim 14 , wherein each power management unit is configured to provide electrical power from a respective power-controller interface unit to the stored energy source.
16 . The vertical takeoff and landing aircraft of claim 15 , wherein each power management unit is configured to provide electrical power from the stored energy source to a respective integrated-converter-controller of the third electrical motor.
17 . The vertical takeoff and landing aircraft of claim 16 , wherein the plurality of power-controller interface units includes triple-redundant power-controller interface units.
18 . The vertical takeoff and landing aircraft of claim 17 , wherein the plurality of power management units includes triple-redundant power management units.
19 . The vertical takeoff and landing aircraft of claim 1 , wherein the first electrical motor-generator includes triple redundant electrical motors and the third electrical motor includes triple redundant electrical motors.
20 . The vertical takeoff and landing aircraft of claim 3 , wherein the first electrical motor-generator includes triple redundant electrical motor-generators and the fourth electrical motor-generator includes triple redundant electrical motor-generators.