Parallel control loops for hybrid electric aircraft

Patent metadata

Field	Value
Publication number	US-12252264-B2
Application number	US-202318370151-A
Country	US
Kind code	B2
Filing date	Sep 19, 2023
Priority date	May 15, 2020
Publication date	Mar 18, 2025
Grant date	Mar 18, 2025

Abstract

A method of controlling a hybrid-electric aircraft powerplant includes running a first control loop for command of a thermal engine based on error between total response commanded for a hybrid-electric powerplant and total response from the hybrid-electric powerplant. A second control loop runs in parallel with the first control loop for commanding the thermal engine based on error between maximum thermal engine output and total response commanded. A third control loop runs in parallel with the first and second control loops for commanding engine/propeller speed, wherein the third control loop outputs a speed control enable or disable status. A fourth control loop runs in parallel with the first, second, and third control loops for commanding the electric motor with non-zero demand when the second control loop is above control to add response from the electric motor to response from the thermal engine to achieve the response commanded.

First claim

What is claimed is:

1. A system comprising:
a hybrid-electric powerplant for an aircraft, the hybrid-electric powerplant including a thermal engine and an electric motor each operatively connected together in parallel to a combining gear box to provide torque to drive an air mover for thrust, the combining gear box being connected to the air mover via a reduction gear box;
a first control loop connected for commanding the thermal engine based on an error between a total response commanded for the hybrid-electric powerplant and a total response output from the hybrid-electric powerplant;
a second control loop connected in parallel with the first control loop for commanding the thermal engine based on an error between a maximum thermal engine output and the total response commanded for the hybrid-electric powerplant, sensory feedback from the reduction gear box being combined with sensory feedback from the electric motor to determine a torque feedback from the thermal engine, commanding the thermal engine including controlling fuel flow to the thermal engine;
a low selector connected between the first control loop and the second control loop to command the thermal engine for the lower of responses commanded from the first and second control loops;
a third control loop connected in parallel with the first and second control loops for commanding engine/air mover speed, wherein the third control loop outputs a speed control enable or disable status;
a high selector connected between output of the third control loop and the low selector; and
a fourth control loop connected in parallel with the first, second, and third control loops for commanding the electric motor with a non-zero demand when the second control loop is in control to add a response from the electric motor to a response from the thermal engine to achieve the total response commanded for the hybrid-electric powerplant,
wherein:
each of the first, second, third and fourth control loops is configured to run while not actively commanding;
the first control loop includes a first integrator configured to be reset while the first control loop is running and not actively commanding;
the second control loop includes a second integrator configured to be reset while the second control loop is running and not actively commanding;
the third control loop includes a third integrator configured to be reset while the third control loop is running and not actively commanding; and
the fourth control loop includes a fourth integrator configured to be reset while the fourth control loop is running and not actively commanding.

2. The system as recited in claim 1 , wherein the air mover is a propeller.

3. The system as recited in claim 1 , wherein the first integrator is configured to be reset by one of the second control loop, the third control loop or the fourth control loop that is actively commanding.

4. The system as recited in claim 1 , wherein the second integrator is configured to be reset by one of the first control loop, the third control loop or the fourth control loop that is actively commanding.

5. The system as recited in claim 1 , wherein the third integrator is configured to be reset by one of the first control loop, the second control loop or the fourth control loop that is actively commanding.

6. The system as recited in claim 1 , wherein the fourth integrator is configured to be reset by one of the first control loop, the second control loop or the third control loop that is actively commanding.

Assignees

• Pratt & Whitney Canada

Inventors

• Guerchkovitch Leonid
• Dhingra Manuj
• Karpman Boris
• Kaufman Aaron J

Classifications

• B64D35/025

  of parallel type · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D31/06 Primary

  actuated automatically · CPC title

• B64D31/18 Primary

  for hybrid-electric power plants · CPC title

• B64D27/026

  comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33) · CPC title