Plasmonic Evaporation Chamber Thruster for Higher Thrust

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Solution Overview

Problem

Existing Hall-effect thrusters suffer from limited thrust due to power, efficiency, and specific impulse limitations, necessitating an improvement in thruster design using surface plasmonic resonance (SPR) and photothermal absorption (PA) mechanisms.

Innovation Solution

A propulsion system utilizing an SPR/PA evaporation chamber with nanostructures on a transparent substrate, which excites conduction electrons with light to heat propellant, expelling it through nozzles for thrust, integrated with propellant storage and delivery systems, and optionally using fiber optics or opaque covers for light control.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Force

If Hall-effect thrusters are used to ionize and accelerate propellant, then thrust is produced, but the thrust is very small due to power, efficiency, and specific impulse limitations

Engineering Contradiction:

ImprovethrustVSAvoidpower efficiency

Core Design Contradiction:

ForceVSUse of energy by moving object

Solution Approach 1:

The patent replaces the electrical ionization and acceleration mechanism of Hall-effect thrusters with a photothermal mechanism. Light energy is absorbed by the propellant in the evaporation chamber, converting electromagnetic energy directly to thermal energy, which then produces thrust through thermal expansion and expulsion. This substitution eliminates the need for complex electrical fields and ionization processes, achieving higher efficiency and thrust.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

2Force

If conventional thruster designs are used, then propulsion is achieved, but propellant costs are high and system weight is excessive

Engineering Contradiction:

Improvepropulsion capabilityVSAvoidsystem weight

Core Design Contradiction:

ForceVSWeight of moving object

Solution Approach 1:

The patent extracts and eliminates unnecessary components from conventional thruster systems. By using a simple evaporation chamber with transparent walls to allow light penetration, the design removes complex ionization chambers, electromagnetic field generation systems, and associated control mechanisms. This extraction of essential functions to minimal components reduces system weight while maintaining propulsion capability.

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The patent changes the fundamental operating parameters from electrical-based propulsion to light-based thermal propulsion. By using photothermal absorption to heat propellant directly with light energy, the system achieves higher specific impulse and reduced propellant consumption, thereby lowering both propellant costs and system weight requirements.

Inventive Principle:

Principle #35Parameter changes

3Loss of energy

If light energy is used to heat propellant through SPR/PA mechanisms, then radiative-to-thermal energy transfer efficiency reaches 60-80%, but requires precise control of light delivery

Engineering Contradiction:

Improveenergy transfer efficiencyVSAvoidlight control system

Core Design Contradiction:

Loss of energyVSDevice complexity

Solution Approach 1:

The transparent evaporation chamber serves multiple functions simultaneously: it allows light penetration for photothermal heating, contains the propellant, and acts as the propulsion chamber itself. This multi-functionality eliminates the need for separate light delivery systems, insulation layers, and control mechanisms, achieving high energy efficiency without increasing device complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

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 achieves highly efficient (60-80%) radiative-to-thermal energy transfer, potentially outperforming Hall effect thrusters in thrust and specific impulse while reducing propellant costs and system weight, suitable for asteroid missions and other space applications.

Implementation Method 1

Surface plasmonic resonance (SPR) is a well-known phenomenon in which the conduction electrons at a metal-dielectric interface are locked in a resonant oscillation with an external electromagnetic wave

Methodology Applied

Scientific EffectSurface plasmonic resonance: Resonance

Implementation Method 2

Photothermal absorption (PA) is a more general term for radiative absorption that re-releases the energy as heat concerning processes in both insulators and conductors

Methodology Applied

Scientific EffectPhotothermal absorption: Absorption (EM radiation)

Implementation Method 3

The plurality of nanostructures configured to heat the propellant

Methodology Applied

Scientific EffectThermal conduction: Conduction (thermal)

Data Source

PatentUS12545437B2Mass propelled device

Publication Date: 2026.02.10 SCHIFFBAUER TECH LTD

AI summary

A mass propelled device includes an evaporation chamber and at least one nozzle. The evaporation chamber includes (i) at least one transparent substrate and (ii) a plurality of nanostructures disposed on a second surface opposite a first surface. The evaporation chamber receives light on the first surface and the plurality of nanostructures excites conduction electrons in response to the received light. The evaporation chamber heats propellent therein using the conduction electrons thereby generating heated propellant. The at least one nozzle produces thrust by exhausting the heated propellent from the evaporation chamber.