Torque balancing for hybrid electric propulsion systems and aircraft utilizing hybrid electric propulsion systems
A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system. The ECU can be configured to receive a torque command and split output power between the electric motor system and the heat engine system. Additionally and/or alternatively, the ECU can be configured to balance a total torque against a second total torque of a second aircraft powerplant.
1. A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system, the heat engine system and the electric motor system drivingly engaged to a first air mover, the ECU being configured to:
receive a torque command and split output power between the electric motor system and the heat engine system;
the ECU further comprising a torque splitting module configured to:
receive a total torque value;
receive a second total torque value, the second total torque value generated by a second aircraft powerplant driving a second air mover different than the first air mover, the first air mover being disengaged from the second aircraft powerplant, the second air mover being disengaged from the hybrid electric aircraft powerplant, the first air mover having a thrust requirement corresponding to that of the second air mover, the first air mover engaged solely by the hybrid electric aircraft powerplant, the second air mover engaged solely by the second aircraft powerplant;
determine a torque split of the total torque value between the electric motor system and the heat engine system, including varying both of a first torque generated by the heat engine system and a second torque generated by the electric motor system to achieve the torque split and to output the total torque value; and
control the electric motor system and the heat engine system to produce the total torque value in accordance with the determined torque split to match or approximate the second total torque value generated by the second aircraft powerplant.
2. The ECU of claim 1 , further comprising a total torque module configured to:
receive one or more input values including at least a power lever setting;
determine the total torque value as a function of the one or more input values; and
output the total torque value to the torque splitting module.
3. The ECU of claim 2 , wherein the one or more input values further include at least one of an altitude, a total temperature, a condition lever setting, and/or the second total torque of the second aircraft powerplant.
4. The ECU of claim 2 , wherein the total torque module is configured to determine the total torque value using a locally stored torque map to match or approximate the second total torque of the second aircraft powerplant at a same power lever setting.
5. The ECU of claim 2 , further comprising a torque rate limit module configured to match or approximate a rate of torque change to the second aircraft powerplant to match or approximate dynamic response of the second aircraft powerplant.
6. The ECU of claim 1 , comprising a fuel flow control module configured to control fuel flow in the heat engine system to control torque output of the heat engine system as a function of a heat engine torque value (Qh) output by the torque splitting module.
7. The ECU of claim 6 , wherein the torque splitting module is configured to output an electric motor torque value (Qe) to a motor control module (MC) of the electric motor system, wherein the MC is configured to control an electric motor of the electric motor system as a function of the Qe.
8. A hybrid electric aircraft powerplant system, comprising:
a heat engine system configured to provide a first torque to a first air mover;
an electric motor system configured to provide a second torque to the first air mover in addition to and/or independently of the heat engine system; and
a hybrid electric engine control module (ECU) operatively connected to the heat engine system and the electric motor system to control a torque output from each of the heat engine system and the electric motor system, wherein the ECU is configured to receive a torque command and split output power between the electric motor system and the heat engine system, wherein the ECU includes a torque splitting module configured to:
receive a total torque value;
receive a second total torque value, the second total torque value generated by a second aircraft engine driving a second air mover different than the first air mover, the first air mover being disengaged from the second aircraft engine, the second air mover being disengaged from the hybrid electric aircraft powerplant system, the first air mover having a thrust requirement corresponding to that of the second air mover, the first air mover engaged solely by the hybrid electric aircraft powerplant, the second air mover engaged solely by the second aircraft engine; and
determine a torque split of the total torque value between the electric motor system and the heat engine system, including varying both of the first torque generated by the heat engine system and the second torque generated by the electric motor system to achieve the torque split and to output the total torque value; and
control the electric motor system and the heat engine system to produce the total torque value in accordance with the determined torque split to match or approximate the second total torque value generated by the second aircraft engine.
9. The hybrid electric aircraft powerplant system of claim 8 , wherein the ECU further comprises a total torque module configured to:
receive one or more input values including at least a power lever setting;
determine the total torque value as a function of the one or more input values; and
output the total torque value to the torque splitting module.
10. The hybrid electric aircraft powerplant system of claim 9 , wherein the one or more input values further include at least one of an altitude, a total temperature, a condition lever setting, and/or the second total torque of the second aircraft powerplant.
11. The hybrid electric aircraft powerplant system of claim 9 , wherein the total torque module is configured to determine the total torque value using a locally stored torque map to match or approximate the second total torque of the second aircraft powerplant at a same power lever setting.
12. The hybrid electric aircraft powerplant system of claim 9 , wherein the ECU further comprises a torque rate limit module configured to match or approximate a rate of torque change to the second aircraft powerplant to match or approximate dynamic response of the second aircraft powerplant.
13. The hybrid electric aircraft powerplant system of claim 8 , further comprising a fuel flow control module configured to receive a heat engine torque value (Qh) output by the torque splitting module and to control fuel flow in the heat engine system to control torque output of the heat engine system as a function of the Qh output by the torque splitting module.
14. The hybrid electric aircraft powerplant system of claim 13 , wherein the torque splitting module is configured to output an electric motor torque value (Qc) to a motor control module (MC) of the electric motor system, wherein the MC is configured to control an electric motor of the electric motor system as a function of the Qe.
15. A computer implemented hybrid electric aircraft powerplant control method for a hybrid electric aircraft powerplant drivingly engaged to a first air mover, the method comprising:
receiving one or more power input values including at least a power lever command;
determining a total torque demand based on the one or more power input values to create a total torque value and receiving a second total torque value generated by a second aircraft powerplant drivingly engaging a second air mover different than the first air mover, the first air mover being disengaged from the second aircraft powerplant, the second air mover being disengaged from the hybrid electric aircraft powerplant, the first air mover having a thrust requirement corresponding to that of the second air mover, the first air mover engaged solely by the hybrid electric aircraft powerplant, the second air mover engaged solely by the second aircraft powerplant;
splitting the total torque value into an electric motor torque value and a heat engine torque value, including varying both of an electric motor torque and a heat engine torque to achieve a desired torque split and to output the total torque; and
controlling an electric motor system as a function of the electric motor torque value and controlling a heat engine system as a function of the heat engine torque value to cause the powerplant to meet the total torque demand, wherein the one or more power input values includes at least a second total torque of the second aircraft powerplant.
16. The method of claim 15 , further comprising matching or approximating the total torque value to the second total torque of the second aircraft powerplant at a same power setting.
17. The method of claim 15 , further comprising controlling a torque change rate to match or approximate a second torque change rate of the second aircraft powerplant.
18. The method of claim 15 , wherein the one or more power input values further include at least one of an altitude, a total temperature, and/or a condition lever setting.
19. The method of claim 15 , comprising controlling fuel flow in the heat engine system to control torque output of the heat engine system as a function of the heat engine torque value (Qh) output by a torque splitting module, wherein the torque splitting module is configured to output the electric motor torque value (Qe) to a motor control module (MC) of the electric motor system, wherein the MC is configured to control an electric motor of the electric motor system as a function of the Qe.