Aircraft Fuel Cell Layout With Airflow Control and CG Balance
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Solution Overview
Problem
The integration of a fuel cell system into an aircraft poses challenges due to weight and center of gravity issues, as well as the need for efficient air flow management, which affects fuel consumption and energy conversion efficiency.
Innovation Solution
A fuel cell system layout is optimized within the aircraft fuselage, incorporating an inlet portion for outside air, a blower, air recirculation loop, hydrogen storage tank, and a controller to manage air flow rates based on external conditions, ensuring efficient energy generation and propulsion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If a fuel cell system is integrated into the aircraft, then fuel consumption is reduced and energy conversion efficiency is improved, but the weight of the aircraft increases due to carrying the fuel cell stack, hydrogen storage tank, and associated equipment
Solution Approach 1:
The patent combines multiple equipment components (fuel cell stack, hydrogen storage tank, air supply device, motor, and battery) into an integrated fuel cell system that is collectively installed in the aircraft. This merging approach optimizes the overall weight by sharing common structures and systems rather than carrying separate independent equipment, thereby reducing the total weight increase while maintaining improved fuel efficiency.
2Use of energy by moving object
If the fuel cell system is installed in the aircraft, then energy efficiency is improved, but the center of gravity changes due to the positional relation of the hydrogen storage tank and equipment layout
Solution Approach 1:
The patent strategically locates the fuel cell system and its components (hydrogen storage tank, fuel cell stack, air supply device, and motor) at specific positions within the aircraft fuselage to optimize the center of gravity. By carefully selecting the local installation positions of each component, the system achieves balanced weight distribution that maintains aircraft stability while maximizing energy conversion efficiency.
3Power
If the air flow rate to the fuel cell stack is increased, then energy generation is improved, but the aerodynamic impact and drag increase
Solution Approach 1:
The patent introduces an air supply device as an intermediary component that mediates between the external air flow and the fuel cell stack. This device controls and regulates the air flow rate entering the fuel cell stack, allowing optimization of energy generation while minimizing the direct aerodynamic impact on the aircraft. The air supply device acts as a buffer that decouples the relationship between aircraft motion and fuel cell air intake.
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 configuration enhances stability, reduces fuel consumption, and improves energy efficiency by optimizing the placement of the fuel cell system and managing air flow according to external conditions, thereby minimizing weight and aerodynamic impact.
Implementation Method 1
Electricity may be generated through a chemical reaction (e.g., a redox reaction) between hydrogen and oxygen, or another oxidizing agent.
Data Source
AI summary
The present disclosure relates to a fuel cell system and an aircraft equipped with a fuel cell system. The aircraft may have a fuselage elongated in a front-rear direction, a front horizontal stabilizer towards a front of the fuselage, main wings extending to opposite sides of the fuselage, a rear horizontal stabilizer towards a rear of the fuselage, the fuel cell system rear to the main wings and a controller. The fuel cell system may be configured to provide electrical energy for driving a motor on each of the main wings. The controller may be configured to cause transmission of electrical energy from the fuel cell system to the motor. A center of gravity of the aircraft may be near front edges of the main wings. A flow rate of air into the fuel cell system may be controlled in response to an outside air condition.