Hybrid Aircraft Propulsion With Split Motor Redundancy Control
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Solution Overview
Problem
Vertical Take-Off and Landing (VTOL) aircraft with hybrid propulsion systems face limitations due to battery range and power density issues, requiring efficient control and redundancy in electric motor systems to ensure reliable operation and detect anomalies.
Innovation Solution
The aircraft propulsion system incorporates a turbomachine, dual half-motors with separate stators and a common rotor, an active rectifier, and distinct command and monitoring modules to control and synchronize motor speeds, detect anomalies, and adapt voltage levels, utilizing different electronic technologies to reduce failure risks and eliminate the need for additional converters.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single command module is used to control both half-motors, then device complexity is reduced, but reliability decreases due to potential single points of failure
Solution Approach 1:
The command module is divided into two separate command modules, each independently controlling one half-motor. This segmentation eliminates single points of failure, as each module can operate independently if the other fails, thereby improving system reliability without significantly increasing overall complexity.
2Adaptability or versatility
If the battery is connected directly to the motor power supply bus, then device complexity is reduced, but adaptability decreases due to voltage variations affecting motor operation
Solution Approach 1:
An active rectifier is introduced as an intermediary component between the battery and the motor power supply bus. This active rectifier regulates voltage variations and adapts the battery output to suitable levels for motor operation, improving voltage adaptability while maintaining a relatively simple power supply architecture through intelligent power management.
3Reliability
If separate monitoring module is added to detect anomalies, then reliability is improved through anomaly detection, but device complexity increases
Solution Approach 1:
The monitoring module is designed with multi-functionality, integrating anomaly detection, diagnostic capabilities, and communication functions into a single unit. This universal approach improves reliability through comprehensive monitoring while minimizing the increase in device complexity by consolidating multiple functions into one module rather than adding separate components for each function.
4Adaptability or versatility
If active rectifier is used to control generator voltage, then adaptability is improved for charge/discharge modes, but device complexity increases
Solution Approach 1:
The active rectifier implements dynamic voltage control, continuously adapting the generator output voltage based on real-time operating conditions and battery charge state. This dynamic adaptability allows the system to efficiently manage charge and discharge modes across varying operational requirements, while the electronic control approach maintains relatively low complexity compared to mechanical or electrochemical alternatives.
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 configuration enhances operational safety, reduces mass, and maintains stable power supply by enabling efficient control and redundancy, allowing for reliable operation across varying charge modes and detecting anomalies, thus extending the range and reliability of VTOL aircraft.
Implementation Method 1
an active rectifier configured to transform the AC voltage into a DC voltage, the value of which is piloted by the active rectifier
Implementation Method 2
at least one electric generator driven by the turbomachine and configured to generate an AC voltage
Data Source
AI summary
An aircraft propulsion system includes a turbomachine andat least one electric motor. The motor includes a first half-motor and a second half-motor that include, respectively, a first stator and a second stator cooperating with a common rotor of the motor.The propulsion system further includes at least one first energy source (B) capable of delivering a DC voltage andat least one electric generator (PMG) driven by the turbomachine. The electric generator generates an AC voltage to form a second energy source and is associated with an active rectifier that transforms the AC voltage into a DC voltage. The value of the DC voltage is controlled by the active rectifier, the output of which is connected to the first energy source.