Superconducting Inductive Element for Aircraft Power-to-Weight Limits
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Solution Overview
Problem
Conventional aircraft power systems have an unsatisfactory weight/electrical power ratio, necessitating the optimization of power components to reduce energy consumption and carbon emissions.
Innovation Solution
A lightweight inductive element comprising a stack of magnetic and superconducting material strips, surrounded by an electrically insulating and thermally conductive layer, configured to form loops or solenoids, and operable in a cryogenic fluid environment to enhance inductance per unit weight and length.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If conventional power components are used in aircraft, then the system is simple and easy to manufacture, but the weight/electrical power ratio is unsatisfactory
Solution Approach 1:
The patent changes the physical state and material properties by using superconducting materials that operate at cryogenic temperatures. This parameter change (temperature) enables the system to achieve much higher electrical power density while reducing the weight of inductive components, directly resolving the contradiction between power and weight.
Solution Approach 2:
The invention employs composite structures combining superconducting materials with magnetic materials and electrically insulating layers. This composite approach creates a lightweight inductive component that maintains high electrical power capability while minimizing weight, addressing the power-to-weight ratio issue.
2Weight of moving object
If superconducting materials are used to reduce weight, then the weight/electrical power ratio improves, but the device complexity and cooling requirements increase
Solution Approach 1:
The patent merges the cooling function with the liquid hydrogen fuel storage system already present in the aircraft. The cryogenic fluid serves dual purposes: as fuel and as the cooling medium for superconducting components. This eliminates the need for separate cooling systems, reducing device complexity despite using superconducting materials.
Solution Approach 2:
The liquid hydrogen serves multiple functions simultaneously: it is the energy source for propulsion and also the cryogenic coolant for the superconducting inductive components. This multi-functionality reduces overall system complexity and eliminates redundant cooling infrastructure.
3Device complexity
If conventional inductive components are used, then the cooling system is simple, but the inductance per unit weight and length is insufficient
Solution Approach 1:
By changing the operating temperature parameter to cryogenic levels, the inductive components achieve dramatically higher inductance per unit weight and length. The superconducting state enables magnetic fields to be maintained with minimal energy loss, allowing for more compact and efficient inductive components.
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 solution provides a higher weight/electrical power ratio, reducing energy requirements for aircraft flight by offering high inductance per unit weight and length, and simplifying cooling systems by utilizing liquid hydrogen as a cold source.
Implementation Method 1
at least one second strip of superconducting material
Implementation Method 2
at least one first strip of magnetic material, at least one third strip of magnetic material
Implementation Method 3
each first and second strip of magnetic material is surrounded by an electrically insulating and thermally conductive layer
Implementation Method 4
arranged in a cryogenic fluid volume
Data Source
Figure 1~2
Figure 3
AI summary
The invention relates to an inductive element (100) characterized in that it comprises a stack of at least one first strip (107a) of magnetic material, at least one second strip (105) of superconducting material, and at least one third strip (107b) of magnetic material. It is thus advantageously possible to obtain an increased ratio between the weight of an aircraft comprising inductive elements such said inductive element (100) and the electrical power available on board for the aircraft systems.