Hybrid Distributed Propulsion System for Urban Air Mobility
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Solution Overview
Problem
Current urban air mobility (UAM) solutions face challenges in minimizing noise and pollution during take-off and landing in urban areas, and existing aircraft designs are limited by noise and smoke emissions, requiring innovative propulsion systems for efficient and safe operations within densely populated environments.
Innovation Solution
A hybrid distributed propulsion system combining electric propulsion for low-noise urban operations and internal combustion engine propulsion for increased range, payload, and flight time, utilizing a power generation unit, battery unit, fan modules, and a control unit to selectively power the propulsion system based on flight stage and location.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If electric propulsion is used for urban operations, then noise and pollution are reduced, but flight range and payload capacity are limited
Solution Approach 1:
The propulsion system is segmented into multiple independent fan modules (first fan module, second fan module, third fan module, fourth fan module) distributed across the aerial vehicle. Each module can be independently controlled by separate power sources, allowing selective operation of propulsion units based on flight requirements. This segmentation enables the vehicle to use only necessary propulsion modules during urban operations to minimize noise and pollution while retaining access to full propulsion capacity when extended range is needed.
Solution Approach 2:
The power supply system dynamically switches between battery unit and power generation unit based on flight stage and location. The control unit monitors operational conditions and adjusts power source selection in real-time, enabling the vehicle to operate in low-noise electric mode during urban take-off and landing phases, then transition to high-power combustion mode for cruising or extended-range operations. This dynamic adaptation resolves the contradiction between noise reduction and flight range.
2Duration of action of moving object
If internal combustion engine is used for increased range and payload, then flight time and operational capability are improved, but noise and smoke emissions increase
Solution Approach 1:
The power generation unit acts as an intermediary between the battery unit and the propulsion system. It converts chemical energy from fuel into electrical energy, which then charges the battery or directly powers the fan modules. This intermediary power conversion system enables extended operational capability by providing sustained energy supply for long-duration flights while maintaining the option to switch to pure electric mode when noise and smoke emissions need to be minimized during sensitive operational phases.
Solution Approach 2:
The system changes operational parameters by switching between different power sources and configurations. During urban operations, the vehicle operates with electric propulsion only (parameter: power source = battery), achieving low noise and zero smoke emissions. For extended-range missions, the parameter changes to include power generation unit operation (parameter: power source = battery + fuel-powered generator), thereby increasing flight time and operational capability while accepting higher emissions during non-urban phases.
3Adaptability or versatility
If hybrid distributed propulsion system is implemented, then operational flexibility and safety are enhanced, but system complexity increases
Solution Approach 1:
The battery unit serves multiple functions: it powers the fan modules during electric-only operations, stores energy generated by the power generation unit during hybrid operations, and provides backup power for critical systems. The power generation unit similarly serves dual purposes by generating electricity for propulsion and charging the battery. This multi-functionality reduces the need for separate dedicated systems, thereby managing complexity while enhancing operational flexibility and safety.
Solution Approach 2:
The control unit continuously monitors the operational state of all propulsion modules and power sources, comparing actual performance against desired performance parameters. Based on this feedback, the control unit dynamically adjusts power distribution, fan module operation, and power source selection to optimize system performance. This closed-loop control manages the complexity of the hybrid system by providing automated coordination between multiple components, reducing the burden on operators while enhancing safety through continuous monitoring and adjustment.
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 effectively reduces noise and pollution in urban areas while enhancing operational capabilities outside urban zones, enabling efficient and safe short-distance and long-distance UAM operations.
Implementation Method 1
a battery unit that is charged with power supplied from the power generation unit or supplied with power from the outside
Implementation Method 2
a power generation unit generating electricity by consuming fuel
Implementation Method 3
a plurality of fan modules receiving power from the battery unit or the power generation unit to provide lift to the aerial vehicle
Data Source
AI summary
Disclosed are an aerial vehicle using a hybrid distributed propulsion system and a control method thereof. According to an embodiment of the present specification, an aerial vehicle includes a power generation unit generating electricity by consuming fuel; a battery unit that is charged with power supplied from the power generation unit or supplied with power from the outside; a plurality of fan modules receiving power from the battery unit or the power generation unit to provide lift to the aerial vehicle; a power supply path control unit selecting at least one of the power generation unit and the battery unit to supply power to at least one of the plurality of fan modules; and a route generation unit generating a flight route from a departure point to a destination of the aerial vehicle.