In-Space Fusion Reactor Cooling via Structural Integration
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Solution Overview
Problem
Current fusion reactor cooling systems for spacecraft require complex and resource-intensive methods, such as injecting large amounts of gas or frozen solids, to maintain supercooled temperatures for magnetic components, which can be inefficient and cumbersome.
Innovation Solution
The system utilizes the ambient temperatures in space to cool high-powered magnets and other components by integrating them with the spacecraft's outer structure, employing thermal interfacing materials and adjustable louvers to optimize heat dissipation and manage temperatures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If quenching is utilized to cool the components of the fusion reactors, then the high-powered magnets can be cooled, but large amounts of gas or frozen solids are required which makes the system complex and resource-intensive
Solution Approach 1:
The fusion reactor components are directly exposed to the space environment to utilize ambient space temperatures for cooling, eliminating the need for separate cooling apparatus. The spacecraft structure itself serves as the cooling mechanism by conducting heat from the magnets to the external space environment.
Solution Approach 2:
The cooling function is extracted from the internal system by exposing the shaping coils and magnets directly to the external space environment through protrusions or openings in the spacecraft structure, removing the need for complex internal cooling loops and quenching systems.
2Temperature
If a separate cooling apparatus is built for the fusion reactor, then cooling can be provided, but the system becomes more complex and requires additional resources
Solution Approach 1:
The fusion reactor components utilize the ambient space environment as their cooling medium, eliminating the need for separate coolant systems. The spacecraft structure and space itself provide the cooling function without requiring additional substances or resources.
Solution Approach 2:
The spacecraft structure serves dual functions: providing structural support and serving as a heat dissipation pathway to space. The same structure that protects the spacecraft also acts as the cooling system by conducting heat from internal components to the external space environment.
3Temperature
If thermal interfacing material is used at contact points, then heat dissipation is optimized, but the manufacturing process becomes more complex
Solution Approach 1:
Thermal interfacing material is introduced at the contact points between the shaping coils and spacecraft structure to enhance heat transfer efficiency. This intermediary material ensures optimal thermal contact while accommodating manufacturing tolerances and assembly variations.
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 approach eliminates the need for separate cooling apparatuses, simplifies the cooling process, and effectively maintains the necessary supercooled temperatures for fusion reactors, enabling efficient operation and extended mission durations.
Implementation Method 1
The shaping coils can contact the outer structure of the spacecraft at a plurality of contact points to dissipate heat from the shaping coils to the outer structure. Thermal interfacing material can be disposed at the contact points to optimize the heat dissipation between the shaping coils and the outer structure.
Implementation Method 2
The outer structure of the spacecraft can include a plurality of louvers adapted for exposing components of the fusion reactor to space for cooling. The louvers can be positioned over the shaping coils for cooling the shaping coils.
Data Source
AI summary
A fusion reactor for a spacecraft adapted to be cooled by the resident temperatures in space. The fusion reactor includes a core containing fusion plasma and fuel, and a plurality of shaping coils adapted to contain and shape the fusion plasma and fuel. The fusion reactor including the core and the plurality of shaping coils are disposed within an outer structure of the spacecraft, and the shaping coils are adapted to be cooled by the resident temperatures in space.