VTOL Power Architecture for Battery and Motor Fault Tolerance
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Solution Overview
Problem
Existing electric-powered aerial vehicles face reliability issues during vertical take-off and landing (VTOL) and forward flight due to motor and battery failures, which can disrupt attitude control and thrust, leading to potential crashes.
Innovation Solution
A power system architecture with multiple batteries powering subsets of electric motors, each with dual windings, allows for automatic rerouting of power in case of motor or battery failures, ensuring continued attitude control and thrust by redistributing power among remaining motors and batteries.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single battery powers each motor in a multi-motor electric-powered aerial vehicle, then the power system is simple and lightweight, but the system reliability deteriorates when a battery or motor fails
Solution Approach 1:
The power system is segmented into multiple independent battery modules, where each battery can independently power one or more motors. This segmentation allows the system to continue operating with reduced functionality when individual batteries or motors fail, thereby improving reliability without requiring a completely redundant system.
Solution Approach 2:
The power distribution architecture enables dynamic reconfiguration of power flow paths. When a battery or motor fails, the system dynamically reroutes power from remaining functional batteries to remaining functional motors, allowing the vehicle to adapt its operating configuration and maintain flight capability.
2Reliability
If multiple batteries power each motor with dual windings, then fault tolerance improves, but the power system complexity and weight increase
Solution Approach 1:
The system implements local quality by providing enhanced redundancy (multiple batteries powering each motor with dual windings) at critical components while maintaining overall system efficiency. This localized approach to redundancy improves fault tolerance at the motor level without requiring complete duplication of the entire power system.
Solution Approach 2:
The patent applies partial redundancy by having multiple batteries capable of powering each motor, but not requiring all batteries to simultaneously power all motors at full capacity. The dual winding configuration provides excessive action in terms of redundancy, ensuring that even if one battery or winding fails, the motor can still operate.
3Reliability
If power is automatically rerouted upon motor or battery failure, then flight safety improves, but the control system complexity increases
Solution Approach 1:
The power distribution system incorporates self-service capabilities through automatic detection and rerouting functions. When a battery or motor failure is detected, the system automatically reconfigures power flow without requiring manual intervention or complex external control, thereby improving flight safety while limiting the increase in control system complexity.
Solution Approach 2:
The system employs feedback mechanisms to monitor the operational status of batteries and motors in real-time. This feedback enables the control system to detect failures and automatically initiate power rerouting procedures, ensuring flight safety through continuous monitoring and adaptive response.
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 maintains stable flight operations even with motor or battery failures by automatically adjusting power distribution, enhancing reliability and fault tolerance, thereby preventing accidents and ensuring safe landing.
Implementation Method 1
electric motors used on aerial vehicles
Implementation Method 2
Individual batteries may be used to power a subset of two or more motors
Data Source
AI summary
A power system with a reliability enhancing battery architecture for electric motors adapted for use in an aerial vehicle. Individual batteries may be used to power a subset two or more motors in systems with six or more motors, for example. Each motor may be powered by two or more subsets of batteries, allowing accommodation for motor failure. With a failed motor in a vertical take-off or landing mode, power may be diverted to other motors to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.