Hybrid Contingency Power Drive System for Aircraft
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Solution Overview
Problem
Rotary wing aircraft face challenges in providing contingency power during engine failures, as increasing emergency power ratings is difficult, expensive, and not feasible without significant engine redesign, affecting fuel economy and system cost.
Innovation Solution
A hybrid power drive system comprising a main engine and an auxiliary electric power system connected in parallel, which provides additional power to the rotor when the main engine's power is insufficient, using an electric motor and rechargeable electric power sources like batteries or ultra-capacitors to ensure safe flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the turbine engine is run at increased speeds and temperatures during emergency (OEI ratings), then emergency power is improved, but engine reliability deteriorates and operating duration is limited to 30 seconds to 2.5 minutes
Solution Approach 1:
The power delivery system is segmented into two independent subsystems: a conventional turbine engine subsystem and an electric motor subsystem. The turbine engine provides normal operating power while the electric motor subsystem (comprising batteries or ultra-capacitors and an electric motor) provides emergency contingency power. This segmentation allows the turbine engine to operate within safe, reliable parameters while the electric subsystem handles emergency power demands.
Solution Approach 2:
An electric motor acts as an intermediary between the energy storage system (batteries/ultra-capacitors) and the rotor, providing emergency power when the turbine engine cannot meet power demands. This intermediary enables power delivery during emergencies without requiring the turbine engine to operate in unreliable high-stress conditions.
2Duration of action of moving object
If the turbine engine is run at increased speeds and temperatures during emergency, then emergency power duration is extended, but fuel economy deteriorates
Solution Approach 1:
The power system is divided into a fuel-efficient turbine engine for normal operation and an electric motor subsystem for emergency operations. This segmentation allows the turbine to maintain optimal fuel economy during normal flight while the electric subsystem provides extended emergency power duration without additional fuel consumption, as it draws from stored electrical energy in batteries or ultra-capacitors.
Solution Approach 2:
The conventional mechanical approach of extending turbine engine operation at high temperatures and speeds is replaced with an electric motor subsystem powered by batteries or ultra-capacitors. This substitution eliminates the need to burn additional fuel during emergencies, thereby maintaining fuel economy while extending emergency power duration.
3Power
If significant engine redesign is performed to increase emergency power ratings, then emergency power capability is improved, but system cost and manufacturing complexity increase
Solution Approach 1:
The invention merges two distinct power delivery technologies: the conventional turbine engine system and the electric motor system with battery/ultra-capacitor energy storage. This hybrid combination provides enhanced emergency power capability without requiring redesign of the proven turbine engine, thereby avoiding the complexity and costs associated with significant engine modifications.
Solution Approach 2:
The electric motor subsystem serves multiple functions: it provides emergency contingency power, assists during rotor startup, and can operate independently or in conjunction with the turbine engine. This multi-functionality increases emergency power capability without adding dedicated single-purpose components, reducing overall system complexity.
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 hybrid system delivers contingency power to maintain safe flight conditions after an engine failure while minimizing fuel economy and system cost impacts, offering a short-duration power boost and improving overall engine operability and rotor startup characteristics.
Implementation Method 1
an electric motor and rechargeable electric power sources, such as batteries or ultra-capacitors
Data Source
AI summary
A hybrid power drive system for an aircraft comprises a rotor that receives power and a first power drive sub-system including at least one engine in connection with the rotor is configured to provide a first power to the rotor. Further, the hybrid power drive system also includes a second power drive sub-system connected in parallel to the first power drive sub-system. The second power drive sub-system is configured to provide a second power to the rotor a second power drive sub-system connected in parallel to the first power drive sub-system and configured to provide a second power to the rotor when the first power provided by the first power drive sub-system is less than a power demand of the rotor.