Hybrid VTOL Powertrain Control for Battery SOC Stability
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Solution Overview
Problem
Vertical take-off and landing aerial vehicles with electromotive powertrains face challenges in maintaining battery state of charge (SOC) at a predetermined level, particularly during landing steps, leading to insufficient motor output and affecting flight control, which can be addressed by increasing battery capacity but results in increased weight and costs.
Innovation Solution
A hybrid powertrain control system where the rotor driving motor is connected to a rotor, a battery is connected to the motor, and an engine and generator are connected to the battery to charge and discharge it, with a control device managing engine and generator operation based on motor power requirements and battery SOC across flight steps to maintain the battery at a predetermined level.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If battery capacity is increased to maintain SOC at predetermined level, then battery SOC is maintained, but weight and costs are increased
Solution Approach 1:
The patent combines the battery with an engine-generator system to form a hybrid powertrain. The engine-generator acts as a mobile charging station that can recharge the battery during flight operations, eliminating the need for excessive battery capacity while maintaining SOC reliability.
Solution Approach 2:
The engine-generator serves as an intermediary energy source between external power and the battery. It converts mechanical energy from the engine to electrical energy for battery charging, enabling SOC maintenance without requiring large battery capacity.
2Reliability
If battery capacity is increased to maintain SOC at predetermined level, then battery SOC is maintained, but costs are increased
Solution Approach 1:
The patent merges the battery system with an engine-generator system, allowing the use of a smaller, less expensive battery while the engine-generator provides supplemental charging capacity to maintain SOC during flight operations.
Solution Approach 2:
The system changes the energy supply parameters by introducing an engine-generator that can dynamically adjust power output based on flight phase and battery SOC levels, replacing the need for high-capacity battery specifications.
3Reliability
If engine and generator are controlled based on motor power requirements and battery SOC, then battery SOC is maintained at predetermined level, but device complexity is increased
Solution Approach 1:
The control system implements feedback mechanisms that continuously monitor motor power requirements and battery SOC levels, automatically adjusting engine and generator operation to maintain SOC within predetermined ranges without requiring complex manual intervention.
Solution Approach 2:
The engine-generator system performs multiple functions: it can operate independently to provide power, charge the battery during flight, and serve as a backup power source. This multi-functionality reduces the need for separate dedicated systems.
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 stable flight by maintaining battery SOC at a predetermined level, reduces the need for large battery capacity, decreases weight and costs, and allows for catalyst heating and engine self-diagnosis, enhancing overall flight performance and reducing exhaust gas.
Implementation Method 1
a battery connected to the rotor driving motor to supply power to the motor
Implementation Method 2
a generator connected to the battery to charge and discharge the battery
Data Source
AI summary
A powertrain control system is provided for a vertical take-off and landing aerial vehicle for urban air mobility. A powertrain of the vertical take-off and landing aerial vehicle is a hybrid type powertrain, in which the output shaft of a rotor driving motor is directly connected to a rotor, a battery is connected to the rotor driving motor to supply power thereto, and an engine and a generator are connected to a battery to charge and discharge the battery. The driving of the engine and the generator is controlled based on required power of the motor and the SOC of the battery in each flight step of the vertical take-off and landing aerial vehicle, and the SOC of the battery is constantly maintained at a predetermined level or higher.