Hybrid Electric Propulsion Load Response for Thrust Stability
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Solution Overview
Problem
Hybrid electric propulsion systems for aerial vehicles face issues with rapid electrical load changes, leading to thrust asymmetry and overspeed due to electrical coupling, which existing technologies have not adequately addressed.
Innovation Solution
A hybrid electric propulsion system with onboard sensing devices and controllers that detect electrical load changes and generate control actions, such as reducing fuel flow or using electrical braking, to rapidly adjust engine torque and maintain stable thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a hybrid electric propulsion system is implemented, then additional thrust sources and electrical power generation are achieved, but rapid electrical load changes cause thrust asymmetry and overspeed issues
Solution Approach 1:
The control system continuously monitors electrical load changes through sensing devices and automatically adjusts engine torque in response to detected load variations, creating a closed-loop feedback mechanism that maintains thrust stability despite rapid electrical load changes in the hybrid electric propulsion system
Solution Approach 2:
The control system detects electrical load changes and generates control actions to adjust engine torque before significant thrust asymmetry or overspeed conditions develop, preventing harmful effects before they occur rather than responding after the problem manifests
2Device complexity
If electrical coupling is used to connect power generating and consuming devices, then system integration and power transfer are achieved, but single failures produce severe thrust changes and handling issues
Solution Approach 1:
The control system monitors performance indicators from sensing devices that detect electrical load changes and automatically adjusts engine torque in response to failures or load variations, providing real-time feedback control that compensates for the vulnerability of electrically coupled systems to single failures and maintains safe aircraft handling
Solution Approach 2:
The control system acts as an intermediary between the electrically coupled power generating and consuming devices, mediating the effects of failures by detecting load changes and adjusting engine torque to compensate for imbalances, thereby preventing severe thrust asymmetry from propagating through the system
3Speed
If rapid electrical load changes are allowed, then system responsiveness and power flexibility are improved, but engine overspeed and handling safety are compromised
Solution Approach 1:
The control system detects electrical load changes and generates control actions to adjust engine torque before overspeed conditions can develop, taking preliminary protective action that allows the system to remain responsive to power demands while preventing harmful engine overspeed
Solution Approach 2:
The control system continuously monitors electrical load through sensing devices and provides real-time feedback control by adjusting engine torque in response to detected load changes, enabling the system to respond rapidly to power demands while simultaneously preventing engine overspeed through automatic torque regulation
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
The system effectively mitigates thrust asymmetry and overspeed by automatically responding to rapid electrical load changes, ensuring safer aircraft handling and reducing the risk of engine overspeed.
Implementation Method 1
a first electric machine mechanically coupled with the engine and configured to generate electrical power when driven by the engine
Implementation Method 2
a second electric machine electrically coupled with the first electric machine and configured to receive electrical power from the first electric machine
Data Source
Figure 1
Figure 2
Figure 3
AI summary
Hybrid electric propulsion systems and methods therefore are provided. More particularly, the present disclosure is directed to control systems for hybrid electric propulsion systems for aerial vehicles that are configured for rapidly and automatically taking action in response to rapid electrical load changes on a torque source, such as an engine. Methods for operating hybrid electric propulsion systems for aerial vehicles are also provided.