Aircraft Motor Control for Battery SOC Balancing and Thrust Stability
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Solution Overview
Problem
In hybrid propulsion systems for aircraft, when the total required electric power exceeds what can be supplied by the primary power source, there is an imbalance in battery capacities, leading to insufficient power for some electric propulsion systems despite sufficient power being available for others.
Innovation Solution
A control apparatus that includes power generators, batteries, electric motors, and diodes, with an electric motor control section and battery monitoring section to adjust the output power of electric motors based on battery state of charge differences, ensuring equalization of battery states of charge by reducing power consumption from batteries with lower states of charge and increasing power from those with higher states of charge.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If electric power is supplied from multiple second power sources to meet total required power, then sufficient electric power can be supplied to electric propulsion systems, but imbalance in battery capacities causes insufficient power for some systems despite sufficient power for others
Solution Approach 1:
The control apparatus continuously monitors the state of charge of each battery through the state of charge acquisition section. Based on this feedback information, the power supply selection section dynamically determines which power source supplies power to each electric propulsion system, ensuring that batteries with higher state of charge are utilized first, thereby preventing power insufficiency while maintaining reliable power supply.
Solution Approach 2:
The system dynamically adjusts the power supply configuration based on real-time battery states. The power supply selection section changes the power source assignment for each electric propulsion system according to the current state of charge levels, transforming a static power distribution system into a dynamic one that adapts to changing battery conditions, thus resolving the power imbalance issue.
2Reliability
If thrust from first electric motor is decreased to reduce power consumption, then battery state of charge can be equalized, but total thrust generation is reduced
Solution Approach 1:
The system merges the power supply from multiple sources (first power source and second power sources) to drive the electric propulsion systems. By combining power from batteries with different state of charge levels, the system can equalize battery states while maintaining sufficient total thrust generation, as the power deficit from one motor is compensated by power surplus from another motor's battery.
Solution Approach 2:
Each electric propulsion system is designed with the capability to receive power from multiple power sources. The first electric motor and second electric motor can both function to drive the same rotor, allowing flexible power distribution. This multi-functionality enables the system to equalize battery states by routing power through different paths while maintaining required thrust generation.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach ensures that the state of charge of all batteries is made approximately equal, preventing power insufficiencies and maintaining stable aircraft attitude by adjusting thrust generation accordingly.
Implementation Method 1
at least one power generator configured to generate electric power
Implementation Method 2
at least one first battery configured to store electric power; at least one second battery configured to store electric power
Implementation Method 3
at least one first electric motor configured to operate using electric power supplied from the power generator and the first battery; at least one second electric motor configured to operate using electric power supplied from the power generator and the second battery
Implementation Method 4
at least one first diode including an anode connected to a side of the power generator, and a cathode connected to a side of the first battery; at least one second diode including an anode connected to the side of the power generator, and a cathode connected to a side of the second battery
Implementation Method 5
a plurality of rotors configured to generate thrust acting on a fuselage
Data Source
AI summary
When a difference in the SOC among respective batteries is greater than or equal to a first prescribed value, an electric motor control section reduces output power of a cruise electric motor that operates using electric power of a battery with a low SOC and increases output power of a cruise electric motor that operates using electric power of a battery with a high SOC.