Solar Thermal Thruster Cooling Geometry for Multi-Propellant Heat Control

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Solution Overview

Problem

Existing rocket propulsion systems face inefficiencies in thermal energy conversion and propellant flexibility, particularly in smaller thrusters, leading to increased heat loss and potential structural damage due to thermal stress and unsteady phase changes.

Innovation Solution

The use of a solar thermal rocket engine with regenerative cooling channels and adjustable geometry to optimize propellant vaporization and heat transfer, incorporating a multi-surface light trapping solar absorber and variable energy input mechanisms to enhance thermal efficiency and adapt to various propellants.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Power

If solar thermal rocket engines are used to heat propellants, then thrust is generated, but heat loss increases and structural damage occurs due to thermal stress

Engineering Contradiction:

ImprovethrustVSAvoidheat loss

Core Design Contradiction:

PowerVSLoss of energy

Solution Approach 1:

The solar absorber is divided into multiple segments or zones with different geometric configurations, allowing different portions to handle different thermal loads and propellant flow rates, thereby reducing overall heat loss while maintaining thrust generation

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The solar absorber geometry is made adjustable or variable, allowing the system to optimize its thermal characteristics dynamically based on operating conditions, reducing heat loss when full thrust is not required while maintaining operational flexibility

Inventive Principle:

Principle #15Dynamics

2Power

If high temperature solar heating is applied to propellants, then vaporization and thrust are enhanced, but structural stress and potential damage increase

Engineering Contradiction:

Improvethrust enhancementVSAvoidthermal stress

Core Design Contradiction:

PowerVSStress or pressure

Solution Approach 1:

Different regions of the solar absorber are designed with different geometric properties and thermal characteristics, allowing localized heat distribution that matches the propellant flow pattern, reducing thermal stress concentrations while maintaining effective vaporization where needed

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The geometric parameters of the solar absorber (such as surface area, depth, and configuration) are optimized to control the temperature distribution and heat transfer rates, preventing excessive thermal stress while ensuring sufficient heating for propellant vaporization

Inventive Principle:

Principle #35Parameter changes

3Ease of manufacture

If fixed geometry solar absorbers are used, then manufacturing is simplified, but adaptability to different propellants and conditions is reduced

Engineering Contradiction:

Improvemanufacturing simplicityVSAvoidpropellant flexibility

Core Design Contradiction:

Ease of manufactureVSAdaptability or versatility

Solution Approach 1:

The solar absorber is designed with geometric features that can effectively heat multiple types of propellants under various operating conditions, making a single device suitable for diverse applications without requiring complex reconfiguration mechanisms

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

Adjustable geometric parameters allow the solar absorber to adapt its thermal characteristics to match different propellant properties and operating conditions, providing versatility while maintaining manufacturing feasibility through standardized adjustment mechanisms

Inventive Principle:

Principle #15Dynamics

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 design improves thermal efficiency, reduces structural stress, and enhances operational flexibility by minimizing heat loss and adapting to different propellants, thereby increasing thrust and durability.

Implementation Method 1

a multi-surface light trapping solar absorber

Methodology Applied

Scientific EffectSolar energy absorption: Absorption (EM radiation)

Implementation Method 2

regenerative cooling channels and adjustable geometry to optimize propellant vaporization and heat transfer

Methodology Applied

Scientific EffectHeat transfer: Convection

Implementation Method 3

optimize propellant vaporization

Methodology Applied

Scientific EffectVaporization: Evaporation

Data Source

PatentEP4143427B1Omnivorous solar thermal thruster, cooling systems, and thermal energy transfer in rockets

Publication Date: 2026.03.25 TRANS ASTRONAUTICA CORP

Figure 1
Figure 2A
Figure 2B~2C

AI summary

Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.