Structural Hydrogen Tank for Load-Bearing UAV Airframes
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Solution Overview
Problem
Unmanned aerial vehicles (UAVs) are limited in range and flight time due to battery power, and existing hydrogen fuel cell systems are complex and difficult to repair, especially in remote or congested areas where traditional aircraft may not operate.
Innovation Solution
A structural gas tank integrated into the airframe of a UAV, capable of storing high-pressure hydrogen or other gases, combined with fuel cell powered line-replaceable thrust modules that include a nacelle with a rapid connection interface for easy replacement, allowing for efficient hydrogen supply to a fuel cell system and enabling rapid maintenance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If hydrogen fuel tanks are externally coupled or housed internally within a nacelle, then the UAV can operate with extended range and flight time, but the system becomes complex and difficult to repair at an operating location
Solution Approach 1:
The hydrogen storage system is divided into multiple separate tanks (first hydrogen tank and second hydrogen tank) that can be independently mounted to different components of the UAV. This segmentation allows the system to provide extended flight time while maintaining repairability, as individual tanks can be replaced without affecting the entire fuel cell system.
2Duration of action of moving object
If hydrogen fuel tanks are externally coupled or housed internally within a nacelle, then the UAV can operate with extended range and flight time, but the system becomes difficult to repair at an operating location
Solution Approach 1:
By segmenting the hydrogen storage into separate tanks that can be independently mounted and removed, the system enables easy replacement of individual tanks at operating locations without requiring complex disassembly or specialized repair facilities.
3Productivity
If a structural gas tank is integrated into the airframe, then the UAV achieves efficient hydrogen supply to fuel cell, but the tank must withstand high pressure and structural loads simultaneously
Solution Approach 1:
The hydrogen tank is designed to serve multiple functions simultaneously: it acts as both a high-pressure gas storage container and a structural component of the UAV airframe. The tank is mounted to withstand structural loads while maintaining its pressure containment function, thereby integrating fuel storage with the load-bearing structure.
Solution Approach 2:
The hydrogen tank is integrated within or as part of the UAV's structural components (such as the pylon or fuselage), allowing the tank to be nested within the airframe structure. This nesting arrangement enables the tank to benefit from the surrounding structural support while maintaining efficient hydrogen supply to the fuel cell.
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 extends the range and flight time of UAVs by providing a reliable and maintainable hydrogen fuel system, enabling efficient operation in various environments and allowing for rapid replacement of components, thus enhancing operational flexibility and safety.
Implementation Method 1
Fuel cells operate by allowing an electrochemical reaction between hydrogen and oxygen, which produces electrical energy and water
Data Source
AI summary
A tank has a body defining a chamber therein, the chamber is configured to store a gas at a pressure greater than atmospheric pressure, a first mounting element extending from the body, and a second mounting element extending from the body. The first mounting element and the second mounting element are configured for coupling to a first component of a vehicle and a second component of the vehicle, respectively, and the body is configured to carry a structural load between the first component and the second component when the first mounting element and the second mounting element are coupled thereto. The first component carries a propulsion device and the second component comprises at least one of a wing and a landing element. The tank further includes a stem having an orifice and the stem is configured for delivering the gas to the propulsion device through the orifice.