Hybrid Multirotor Propulsion Power Splitting and Aggregation
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Solution Overview
Problem
Existing hybrid multirotor propulsion systems face efficiency losses due to power conversion in indirect systems and increased costs and weight distribution issues in direct systems.
Innovation Solution
A hybrid multirotor propulsion system that splits total mechanical power into direct and indirect components, using a mechanical power source, a distributor gearbox, electric machines, and power management units to optimize power transmission and control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If indirect hybrid propulsion system is used to convert mechanical power to electric power, then flight autonomy can be extended, but total power efficiency drastically declines due to multiple power conversion steps
Solution Approach 1:
The propulsion system is segmented into multiple independent propulsion units, each with its own electromotor and propeller. This allows the mechanical power from the internal combustion engine to be distributed to multiple propellers simultaneously, reducing the need for repeated power conversion steps while maintaining extended flight autonomy through efficient power distribution.
Solution Approach 2:
A mechanical power transmission system with distributor gearbox acts as an intermediary between the internal combustion engine and multiple electromotors. This intermediary mechanism enables direct mechanical power distribution to multiple propulsion units, avoiding the efficiency losses associated with converting mechanical power to electric power and back to mechanical power in traditional indirect hybrid systems.
2Loss of energy
If direct hybrid propulsion system is used to directly transmit mechanical power to propeller, then power efficiency is maintained, but manufacturing and maintenance costs increase due to multiple internal combustion engines
Solution Approach 1:
The system merges the advantages of direct and indirect hybrid propulsion by combining a single internal combustion engine with multiple electromotors in a hybrid configuration. This unified approach maintains power efficiency through direct mechanical power transmission while avoiding the high costs associated with multiple internal combustion engines, as the single engine shares its output across multiple propulsion units.
Solution Approach 2:
The mechanical power transmission system with distributor gearbox serves multiple functions: it distributes power to multiple electromotors, enables direct mechanical power transmission to maintain efficiency, and reduces the need for multiple internal combustion engines. This multi-functional component achieves both efficiency and cost-effectiveness simultaneously.
3Loss of energy
If multiple internal combustion engines are used in direct hybrid system, then mechanical power can be directly transmitted to propellers, but weight distribution becomes problematic and flight operations become more difficult
Solution Approach 1:
The system merges multiple power sources into a single internal combustion engine that serves all propulsion units through a distributor gearbox. This consolidation concentrates the weight of the mechanical power source in one location, improving weight distribution and flight stability compared to having multiple分散 internal combustion engines throughout the aircraft structure.
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
Achieves high efficiency with reduced manufacturing and maintenance costs by minimizing power conversion and concentrating weight near the center of gravity, improving flight operations and energy consumption.
Implementation Method 1
an electric machine; to cause the electric machine to convert a second mechanical power component into electric power
Implementation Method 2
an electromotor; to cause each electromotor to convert electric propeller power into an indirect mechanical propeller power
Implementation Method 3
an internal combustion engine as well as an electromotor for outputting mechanical power
Data Source
AI summary
A hybrid multirotor propulsion system for an aircraft includes a plurality of propulsion units, each propulsion unit having a propeller, an electromotor and a peripheral differential gearbox; a plurality of driving elements, each of which is coupled to a respective one of the plurality of propulsion units; a mechanical power source; a main distributor gearbox; at least one electric machine; and a power management unit. The power management unit is configured according to a predetermined operating mode, which causes the mechanical power source to output first and second mechanical power components; and distributing the first mechanical power component to provide each driving element with a direct mechanical propeller power; and causes the electric machine to convert the second mechanical power component into electric power, part of which provides each electromotor with an electric propeller power. The direct mechanical propeller power causes each electromotor to convert the electric propeller power into an indirect mechanical propeller power, outputted to the peripheral differential gearbox; and causes the peripheral differential gearbox of each propulsion unit to aggregate the direct mechanical propeller power and the indirect mechanical propeller power to a total mechanical propeller power which drives the propeller of each propulsion unit.