Hybrid eVTOL Power System Redundancy via Multi-Functional Battery
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Solution Overview
Problem
Current power systems for hybrid VTOL UAVs lack reliability and redundancy, leading to potential system failures during missions, which can impact both vertical lift capacity and operational range due to added weight from backup batteries.
Innovation Solution
A redundant hybrid power architecture utilizing multiple channels of high voltage AC power generated by liquid fueled turbine engines, with high voltage domain modules and power distribution units that redirect power to ensure continuous operation even if one primary power source fails, eliminating single points of failure and maintaining operational capacity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If backup batteries are added to provide redundancy, then reliability is improved, but weight increases
Solution Approach 1:
The patent makes the primary battery pack serve dual functions: as the main power source during normal operation and as a backup power source when a turbine fails. The battery pack is designed to automatically engage with the power distribution system upon turbine failure, eliminating the need for separate backup batteries while maintaining redundancy. This multi-functionality approach resolves the contradiction by providing reliability without additional weight.
Solution Approach 2:
The system implements self-service redundancy where the existing battery pack automatically transitions from primary power support to backup power source when a turbine fails. The power distribution system automatically detects the failure and redirects power flow without requiring additional backup components. This self-service mechanism provides reliability while avoiding the weight penalty of dedicated backup batteries.
2Reliability
If redundant power systems are added, then reliability is improved, but device complexity increases
Solution Approach 1:
The patent employs the existing battery pack and power distribution system to serve multiple functions: normal power supplementation, backup power source, and automatic failure response. By making these existing components multi-functional rather than adding dedicated redundant systems, the patent achieves reliability improvement without proportionally increasing device complexity.
Solution Approach 2:
The power distribution system automatically detects turbine failures and redirects power flow without requiring complex manual intervention or additional control systems. This self-service capability provides redundancy while keeping the control architecture relatively simple, as the existing system intelligently adapts to failure conditions rather than requiring dedicated backup control pathways.
3Reliability
If backup power sources are added, then reliability is improved, but loss of substance increases
Solution Approach 1:
The patent makes the existing battery pack multi-functional, serving both as primary power supplementation and as backup power source. This eliminates the need for additional backup batteries that would increase weight and reduce lift capacity. The same substance (battery energy) serves multiple purposes, providing reliability without the penalty of lost lift capacity.
4Reliability
If additional batteries are added for redundancy, then reliability is improved, but range of operations decreases
Solution Approach 1:
The patent employs the existing battery pack for multiple functions including normal operation support and backup power. By avoiding additional backup batteries, the total energy capacity of the system is preserved, maintaining the original range of operations while providing redundancy through the multi-functional use of existing components.
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 solution provides a reliable and lightweight power system that maintains UAV operational capabilities without the need for additional backup power sources, ensuring continued flight and mission completion even if one power source fails, while optimizing battery usage for weight savings and extended range.
Implementation Method 1
liquid fueled turbine engines
Implementation Method 2
high voltage AC power generated from at least one generator, the generator coupled to one or more liquid fueled turbine engines
Implementation Method 3
Two or more high voltage domain modules, one for each channel, receive the high voltage AC power and, using a rectifier change it to high voltage DC power
Data Source
AI summary
A reliable and redundant hybrid VTOL UAV power architecture includes two or more channels of high voltage AC power generated from at least one generator, the generator coupled to one or more liquid fueled turbine engines. Two or more high voltage domain modules, one for each channel, receive the high voltage AC power and, using a rectifier change it to high voltage DC power. A power distribution unit accepts the newly converted channel of high voltage DC power and thereafter bidirectionally provides it to a domain battery and to a primary set of motors. Two or more high voltage busses, each coupled separately to one of the two or more high voltage domain modules, each redundantly transport converted channel of high voltage DC power to, in one embodiment, primary sets of motors forming a primary high power domain bus for these select motors.