Adaptive Cooling System For eVTOL Aircraft With Variable Geometry Inlet
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Solution Overview
Problem
Electric vertical takeoff and landing (eVTOL) aircraft face a tradeoff between drag during cruise flight and thermal management system performance in VTOL mode, with existing cooling systems being insufficiently sized for low-speed flights, leading to reduced efficiency and increased energy consumption.
Innovation Solution
An adaptive cooling system that adjusts airflow volumes and heat exchanger configurations based on flight mode, utilizing multiple closed cooling sub-systems and a thermal management controller to optimize cooling capacity while minimizing drag in both wing-borne and VTOL flight modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If the cooling system is sized for VTOL mode, then cooling capacity is improved, but drag during cruise flight increases
Solution Approach 1:
The patent implements a variable geometry inlet that can dynamically change its cross-sectional area based on flight mode. During VTOL operations, the inlet is enlarged to maximize cooling capacity for the heat exchanger. During cruise flight, the inlet is reduced to minimize drag on the aircraft. This dynamic adjustment resolves the contradiction by allowing the system to have large cooling capacity when needed while maintaining aerodynamic efficiency during cruise.
2Object-generated harmful factors
If the cooling system is sized for nominal cruise flight, then drag is reduced, but cooling capacity becomes insufficient for low-speed VTOL flight
Solution Approach 1:
The variable geometry inlet allows the cooling system to be compact during cruise (reducing drag) while expanding during VTOL operations (increasing cooling capacity). The inlet area is dynamically adjusted based on flight conditions, enabling the same physical infrastructure to serve both cruise and VTOL cooling needs effectively.
3Temperature
If a larger air inlet is used, then cooling capacity is improved, but aircraft efficiency decreases due to increased drag
Solution Approach 1:
The variable geometry inlet dynamically adjusts its size based on flight mode, being large during VTOL operations when cooling capacity is critical and small during cruise flight when aerodynamic efficiency is paramount. This resolves the contradiction by ensuring the inlet is only large when actually needed for cooling, rather than being permanently large and continuously penalizing aircraft efficiency.
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 adaptive cooling system enhances cooling efficiency and reduces energy consumption by providing increased airflow and cooling capacity during VTOL flights while minimizing drag in wing-borne flights, thereby improving overall aircraft performance and range.
Implementation Method 1
The cooling system may include a heat exchanger configured to receive a fluid from which heat is transferable to air
Implementation Method 2
The cooling system may include a fan configured to direct air across a heat exchanger
Data Source
AI summary
An aircraft nacelle has a first and second heat exchanger section to cool aircraft during different modes. Additionally, a fan and other components are configured to maximize efficiency and cooling capacity during a plurality of operating conditions.