Hybrid Rotor Power Unit for Rapid Thrust and Flight Endurance
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Solution Overview
Problem
Current aircraft power systems face challenges in achieving rapid thrust control and efficient energy management, particularly in multi-rotor aerial vehicles, where internal-combustion engines are slow to respond to torque changes and prone to failure, while electric motors offer rapid torque adjustments but are limited by low power density.
Innovation Solution
A hybrid power unit system integrating a primary electric motor and an internal-combustion engine, with a local controller that manages torque output and regenerative braking, and a cooling fan to augment thrust, allowing for rapid rotor speed changes and efficient energy use.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If an internal-combustion engine is used for thrust generation, then extended flight time and high power output are achieved, but rapid torque response and reliability deteriorate
Solution Approach 1:
The power system is segmented into two independent power sources: an internal-combustion engine for sustained high-power operation and extended flight time, and an electric motor for rapid torque response and maneuverability. Each power source operates independently to address different performance requirements without compromising the other.
Solution Approach 2:
The patent combines two different power generation systems (internal-combustion engine and electric motor) into a single hybrid power unit that drives a common rotor. This merging allows the system to leverage the strengths of both power sources simultaneously, achieving both extended flight time and rapid torque response.
2Power
If an internal-combustion engine is used, then high power output is achieved, but system reliability and failure resistance worsen
Solution Approach 1:
The power system is divided into two independent power sources with different reliability characteristics. The electric motor provides a reliable backup that can take over immediately if the internal-combustion engine fails, thereby improving overall system reliability while maintaining high power output capability through the internal-combustion engine.
Solution Approach 2:
The electric motor serves as a pre-configured backup power source that is ready to compensate for potential internal-combustion engine failure. This beforehand cushioning ensures continuous operation and improves reliability by having a fallback option available before any failure occurs.
3Speed
If a primary electric motor is used for rapid torque control, then maneuverability and rapid thrust control are improved, but power density and flight time are limited
Solution Approach 1:
The power system is segmented such that the electric motor handles rapid torque adjustments and maneuverability requirements, while the internal-combustion engine provides sustained power for extended flight time. This segmentation allows each component to specialize in its strength without compromise.
Solution Approach 2:
The electric motor provides more than sufficient torque response capability for maneuverability, potentially exceeding what would be needed alone, while the internal-combustion engine supplements to provide the additional sustained power needed for extended flight time. The combined action exceeds what either system could achieve independently.
4Duration of action of moving object
If battery capacity is increased to extend flight time, then energy storage is improved, but system weight increases
Solution Approach 1:
The patent replaces the purely mechanical/electrical energy storage approach (larger battery) with a hybrid approach that includes an internal-combustion engine as an additional power source. This substitution allows extended flight time to be achieved not by storing more energy in the battery, but by having a secondary power source that can operate in conjunction with or independently of the battery-powered electric motor.
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
Enables rapid thrust control and extended flight times with high maneuverability and payload capacity by leveraging the strengths of both electric and internal-combustion engines, while maintaining a stable battery state and reducing system weight.
Implementation Method 1
a cooling fan configured to displace air through the engine shroud to cool the internal-combustion engine and output a second thrust, from the shroud outlet, to augment the first thrust
Implementation Method 2
a primary electric motor comprising a motor output, a rotor coupled to the motor output and configured to generate a first thrust
Implementation Method 3
an internal-combustion engine coupled to the rotor
Implementation Method 4
a nozzle coupled to the shroud outlet, a nozzle actuator configured to drive the nozzle over a range of orientations
Data Source
AI summary
One variation of a system for generating thrust at an aerial vehicle includes: a primary electric motor; a rotor coupled to the motor; an internal-combustion engine; a clutch interposed between the motor and an output shaft of the internal-combustion engine; an engine shroud defining a shroud inlet between the rotor and the internal-combustion engine, extending over the internal-combustion engine, and defining a shroud outlet opposite the rotor; a cooling fan coupled and configured to displace air through the engine shroud; and a local controller configured to receive a rotor speed command specifying a target rotor speed, adjust a throttle setpoint of the internal-combustion engine according to the target rotor speed and a state of charge of a battery in the aerial vehicle, and drive the primary electric motor to selectively output torque to the rotor and to regeneratively brake the rotor according to the target rotor speed.