Nuclear Reactor Heat Exchange Matrix for Long-Duration Space Power

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Solution Overview

Problem

Conventional power and heat systems for spacecraft in deep-space and low-earth orbit missions are inadequate for long-term operations, necessitating improved systems for sustained power and heat supply.

Innovation Solution

A nuclear reactor system with fuel rods embedded in a heat exchange matrix, coupled with coolant tubes and a thermoelectric generator, provides a closed-loop system for converting heat into electricity, integrated with thermal insulation and radiation shielding, tailored for long-duration missions.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Duration of action of moving object

If conventional power and heat systems are used for spacecraft, then the system complexity is reduced, but the duration of action and reliability are insufficient for long-term deep space missions

Engineering Contradiction:

Improveduration of power supplyVSAvoidsystem complexity

Core Design Contradiction:

Duration of action of moving objectVSDevice complexity

Solution Approach 1:

The nuclear reactor system is divided into distinct functional modules: fuel rods containing radioactive material, heat exchange matrix for thermal transfer, coolant tubes for fluid circulation, and a thermoelectric generator for power conversion. This segmentation allows each component to be optimized independently while maintaining overall system reliability for long-duration missions.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent implements a nested structure where fuel rods are embedded within the heat exchange matrix, coolant tubes are interspersed among the fuel rods, and the entire assembly is housed within protective shrouds. This nested arrangement maximizes heat transfer efficiency while compactly integrating multiple functions within the reactor structure.

Inventive Principle:

Principle #7Nested doll (Nesting)

2Reliability

If a nuclear reactor with embedded fuel rods and coolant tubes is implemented, then heat and power generation reliability is improved, but the device complexity and manufacturing difficulty increase

Engineering Contradiction:

Improvereliability of heat and power supplyVSAvoidease of manufacturing reactor

Core Design Contradiction:

ReliabilityVSEase of manufacture

Solution Approach 1:

The fuel rods, heat exchange matrix, and coolant tubes are pre-assembled into an integrated reactor core structure before being installed in the spacecraft. This preliminary assembly ensures proper alignment and thermal contact between components, simplifying the overall manufacturing process while maintaining high reliability standards.

Inventive Principle:

Principle #10Preliminary action

Solution Approach 2:

The reactor employs composite material structures, including the heat exchange matrix that combines thermal conductivity with structural integrity, and zirconia-clad fuel rods that provide both radiation shielding and heat transfer capabilities. These composite materials reduce the number of separate components needed and simplify manufacturing.

Inventive Principle:

Principle #40Composite materials

3Temperature

If thermal insulation and radiation shielding are added to the reactor system, then heat retention and protection are improved, but the weight and volume of the spacecraft increase

Engineering Contradiction:

Improveheat retentionVSAvoidweight of spacecraft

Core Design Contradiction:

TemperatureVSWeight of moving object

Solution Approach 1:

The outer shroud and radiation shielding structures serve multiple functions: they provide thermal insulation to retain heat for power generation, shield against radiation from the radioactive fuel, and offer structural support for the entire reactor assembly. This multi-functionality reduces the need for separate dedicated components, thereby minimizing weight and volume additions.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The patent merges the radiation shielding function with the structural support framework and thermal insulation layers. The outer shroud integrates these protective functions into a single unified structure rather than adding separate shielding layers, optimizing the weight-to-protection ratio for the spacecraft.

Inventive Principle:

Principle #5Merging (Combining)

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 system offers reliable long-term heat and electrical power generation for spacecraft, enhancing mission durability and efficiency by integrating a nuclear heat generator with a thermoelectric generator.

Implementation Method 1

The heat exchange matrix is configured to conduct heat from the fuel rods to the coolant tubes

Methodology Applied

Scientific EffectThermal conduction: Conduction (thermal)

Implementation Method 2

The TEG can be configured to convert heat energy from coolant from the reactor into electrical power

Methodology Applied

Scientific EffectSeebeck effect: Seebeck Effect

Implementation Method 3

a nuclear reactor having a plurality of fuel rods of radioactive decay material

Methodology Applied

Scientific EffectRadioactive decay: Radioactive Decay

Data Source

PatentUS12397934B2Nuclear-based heat and power for low-earth orbit (LEO) and deep space missions

Publication Date: 2025.08.26 HAMILTON SUNDSTRAND SPACE SYST INT INC

AI summary

A system includes a nuclear reactor having a plurality of fuel rods of radioactive decay material distributed within and embedded within a heat exchange matrix. A plurality of coolant tubes is distributed within and embedded within the heat exchange matrix, interspersed with the plurality of fuel rods. The heat exchange matrix is configured to conduct heat from the fuel rods to the coolant tubes.