Aircraft Power Control for Dual-Generator VTOL Thrust Balancing
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Solution Overview
Problem
Increasing the capacity of batteries in multi-rotor aircraft to extend flight duration leads to increased weight and fuselage weight, compromising efficiency and cost-effectiveness.
Innovation Solution
A control device for an aircraft with dual generators and batteries, where an electric motor control section adjusts power distribution between electric motors to reduce power consumption and maintain thrust, allowing one generator to take over when the other fails, thereby optimizing power usage and reducing weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If the capacity of the battery is increased to extend flight duration after generator failure, then the operation duration of electric motors is improved, but the weight of the battery and fuselage increases
Solution Approach 1:
The control device dynamically changes operational parameters by switching between different power supply modes: normal dual-generator mode, single-generator mode with reduced thrust, and battery-only mode with further reduced thrust. This allows the system to extend flight duration without requiring a larger battery by optimizing power consumption based on available power sources.
Solution Approach 2:
The system implements dynamic thrust adjustment where the thrust generated by rotors is continuously modified based on power availability. When one generator fails, the control device reduces thrust from rotors powered by the remaining generator and increases thrust from rotors powered by the failed generator's motors (now running on battery), creating a balanced power distribution that extends flight duration without requiring increased battery capacity.
2Duration of action of moving object
If the capacity of the battery is increased to extend flight duration, then the operation duration of electric motors is improved, but the weight of the fuselage increases
Solution Approach 1:
The control device modifies operational parameters by adjusting thrust levels dynamically. When operating on battery power after generator failure, the system reduces overall thrust requirements and redistributes power among rotors, allowing extended flight duration without the need for increased fuselage weight or larger battery installation.
3Use of energy by moving object
If power consumption of the first electric motor is reduced by reducing thrust, then power usage is optimized, but the thrust generated by the rotor is reduced
Solution Approach 1:
The control device merges power sources by having multiple generators and batteries supply power to multiple electric motors that drive individual rotors. When one generator fails, the system combines power from the remaining generator and battery to maintain overall thrust while optimizing power consumption of individual motors. The thrust reduction in motors powered by the failed generator is compensated by increased thrust in motors powered by the operational generator.
Solution Approach 2:
The system implements asymmetric power distribution where different rotors operate at different thrust levels based on power availability. Rotors powered by the operational generator maintain higher thrust, while rotors powered by battery (after generator failure) operate at reduced thrust, creating an asymmetric configuration that optimizes overall power usage while maintaining sufficient total thrust for flight.
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 solution extends the operation duration of electric motors and increases flight duration while minimizing weight and manufacturing costs by dynamically adjusting power distribution between electric motors.
Implementation Method 1
at least one first generator configured to generate electric power; at least one second 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 with electric power supplied from the first generator and the first battery; at least one second electric motor configured to operate with electric power supplied from the second generator and the second battery
Implementation Method 4
a plurality of rotors configured to generate thrust acting on a fuselage
Data Source
AI summary
When a first generator is stopped, an electric motor control section reduces the output power of a VTOL electric motor and a cruise electric motor that operate with electric power supplied from the first generator, and increases the output power of a VTOL electric motor and a cruise electric motor that operate with electric power supplied from a second generator.