Modular Fuel Cell Propulsion System for Aircraft
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Solution Overview
Problem
Current aircraft propulsion systems rely on heat engines using kerosene, which necessitates the development of an alternative solution that utilizes electric motors for more efficient and adaptable propulsion.
Innovation Solution
An autonomous propeller propulsion system comprising a fuel cell, electric motor, propshaft, propeller, and controller, with a chassis and attachment systems allowing for easy detachment and reattachment, along with a hydrogen tank and cooling system, enabling flexible adaptation to aircraft requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a heat engine using kerosene is used to move the propeller, then the aircraft can be propelled, but the system lacks adaptability and efficiency compared to electric motors
Solution Approach 1:
The propulsion system is divided into separate modular components: fuel cell module, electric motor module, propeller module, and control module. Each can be independently selected, replaced, or adjusted to optimize performance for different aircraft requirements while maintaining high energy efficiency through specialized design of each segment.
Solution Approach 2:
The system incorporates variable speed control of the electric motor through the controller, allowing dynamic adjustment of propulsion output to match changing flight conditions. This dynamic adaptability enables optimal energy efficiency across different operating regimes, unlike fixed-characteristic heat engines.
2Adaptability or versatility
If an autonomous propulsion system with fuel cells is designed, then energy efficiency and adaptability are improved, but the device complexity increases
Solution Approach 1:
The controller serves multiple functions: converting electric current from fuel cells, controlling motor speed, monitoring system status, and coordinating between different modules. This multi-functionality reduces the number of separate components needed, managing system complexity while maintaining high adaptability.
Solution Approach 2:
The chassis integrates multiple support functions: structural support for all components, mounting for attachment systems, and housing for electrical connections. This consolidation reduces the number of separate structural elements, managing complexity while enabling the adaptable configuration of advanced propulsion components.
3Ease of operation
If the propulsion system is designed for easy detachment and reattachment, then ease of operation and maintenance are improved, but the attachment systems add device complexity
Solution Approach 1:
The attachment system is segmented into standardized first attachment systems on the propulsion unit and corresponding second attachment systems on the aircraft structure. This segmentation allows the complex attachment mechanism to be pre-assembled and tested as a complete module, simplifying the field operation of attaching or replacing the entire propulsion system without handling individual complex components.
4Power
If parallel electric motors are used with a gearbox, then propulsion power and adaptability are improved, but the device complexity and mechanical coupling requirements increase
Solution Approach 1:
The gearbox acts as an intermediary mechanical coupling device that receives power from multiple electric motor output shafts and combines it into a single propshaft. This intermediary component manages the complexity of synchronizing and combining multiple power sources, enabling high propulsion power while maintaining a manageable mechanical architecture.
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
This solution allows for efficient and adaptable propulsion by converting hydrogen fuel into electric power, facilitating easy replacement and maintenance, thereby enhancing aircraft performance and reducing operational disruptions.
Implementation Method 1
an autonomous propeller propulsion system for an aircraft comprising a wing with a structure (103, 404) having a second attachment systems (108, 408) and a second connection means (220), an autonomous propeller propulsion system comprising: a chassis (152, 452) having first attachment systems (106, 406), which are intended to engage with the second attachment systems (108, 408) to ensure detachable attachment of the autonomous system on the structure (103, 404); at least one fuel cell (202) attached to the chassis (152, 452)
Implementation Method 2
a controller (208) converting an electric current delivered by the fuel cells (202) into an electric current delivered to the electric motor (204)
Implementation Method 3
an electric motor (204) attached to the chassis (152, 452) and having an output shaft
Implementation Method 4
a cooling system with a heat exchanger, the heat exchanger is fed with fresh air from the at least one scoop (211), the heat exchanger expels hot air and the hot air is discharged through the exhaust pipe
Data Source
AI summary
An autonomous propeller propulsion system for an aircraft. The autonomous system comprises a chassis with first attachment systems which engage with second attachment systems of the wing to ensure detachable attachment of the autonomous system, a fuel cell attached to the chassis, an electric motor attached to the chassis and having an output shaft, a propshaft rotated by the output shaft, a propeller attached to the propshaft, a controller converting an electric current delivered by the fuel cells into an electric current delivered to the electric motor, a hydrogen feed duct and an air feed duct, a set of auxiliary equipment, and a first connection arrangement, which connects with a second connection arrangement of the aircraft.