Parallel Hybrid-Electric Aircraft Engine Power Management
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Solution Overview
Problem
Aircraft engines face inefficiencies due to the need for a large powerplant capable of both takeoff and climb, which results in excessive weight and limited fuel economy, and existing serial hybrid-electric engines are prone to failures if the generator, battery, or motor malfunctions.
Innovation Solution
A parallel hybrid-electric aircraft engine that combines the output power of an electric motor with an internal combustion engine during takeoff and climb, then converts the electric motor to a generator for reduced power during cruise flight, utilizing a sprag clutch and flexible belt to manage power transitions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a large powerplant is used to provide enough horsepower for takeoff and climb, then the aircraft can accelerate and lift to altitude, but the engine weight increases and fuel economy deteriorates during cruise flight
Solution Approach 1:
The patent applies dynamics by making the engine configuration changeable during flight. The parallel hybrid-electric system dynamically switches between different power delivery modes: using both ICE and electric motor during takeoff/climb, then transitioning to ICE-only mode during cruise. This dynamic adaptation allows the engine to be lightweight yet powerful when needed, resolving the contradiction between engine weight and power availability.
2Power
If a large powerplant is used to provide enough horsepower for takeoff and climb, then the aircraft can accelerate and lift to altitude, but fuel economy worsens when the engine operates at reduced power for cruise flight
Solution Approach 1:
The patent segments the power delivery function into two independent sources: the internal combustion engine and the electric motor. During takeoff and climb, both sources operate simultaneously to provide maximum power. During cruise flight, only the ICE operates at its optimal efficient point, while the electric motor is shut off. This segmentation allows the system to achieve high power when needed while maintaining excellent fuel economy during cruise, resolving the contradiction between power availability and fuel efficiency.
Solution Approach 2:
The parallel hybrid-electric system provides multi-functionality by serving different flight phases with appropriate power sources. The electric motor supplements the ICE during high-power demands (takeoff, climb) and can also serve as a backup power source. The system universally handles various flight conditions optimally, improving overall fuel economy while maintaining the capability for high-power operations.
3Power
If serial hybrid-electric aircraft engines use a generator and battery system, then power can be delivered via wires to an electric motor, but the system fails if the generator, battery, or motor malfunctions
Solution Approach 1:
The patent merges the electric motor and internal combustion engine into a parallel hybrid system where both power sources are directly connected to the propeller through mechanical coupling. This merging eliminates the need for generators and batteries, as the electric motor receives power directly from the ICE via a belt-driven alternator integrated into the mechanical powertrain. The direct mechanical connection and redundant power sources improve reliability, as the system can continue operating if one power source fails.
Solution Approach 2:
The parallel hybrid-electric system provides beforehand cushioning against failure by incorporating redundant power sources. The electric motor serves as a backup to the ICE, and the ICE serves as a backup to the electric motor. This redundancy cushions against the failure of either power source, ensuring continuous operation and improving overall system reliability during critical flight phases.
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 enables a lightweight yet powerful engine that efficiently manages power requirements across flight phases, providing a backup power source and improving fuel economy by optimizing power settings and reducing the risk of engine failures.
Implementation Method 1
utilizing a sprag clutch and flexible belt to manage power transitions
Implementation Method 2
utilizing a sprag clutch and flexible belt to manage power transitions
Implementation Method 3
combines the output power of an electric motor with an internal combustion engine
Implementation Method 4
converts the electric motor to a generator once the additional power of the electric motor is no longer needed
Data Source
AI summary
A parallel hybrid-electric aircraft engine that provides power for takeoff and climb by combining the output power of an electric motor with that an internal combustion engine and then converting the electric motor to a generator once the additional power of the electric motor is no longer needed.