Microfabricated Multiemitter Electrospray Thrusters for SmallSat Propulsion

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Solution Overview

Problem

Small satellites lack efficient propulsion systems that are compact, low in mass and power requirements, and high in efficiency, limiting their capabilities for space exploration and long-life commercial applications.

Innovation Solution

The development of microfabricated multiemitter electrospray thrusters, which utilize micromachining techniques to create compact, low-mass thruster heads that efficiently convert electric power into jet kinetic power, operating at low power levels with high efficiency and scalability for various satellite sizes.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Quantity of substance

If traditional chemical propulsion systems are used, then thrust capability is achieved, but propellant mass and system volume increase significantly

Engineering Contradiction:

Improvepropellant massVSAvoidthrust capability

Core Design Contradiction:

Quantity of substanceVSProductivity

Solution Approach 1:

The patent replaces chemical propulsion systems with electrospray propulsion systems that use electrical fields to accelerate propellant ions, eliminating the need for chemical combustion and significantly reducing propellant mass requirements while maintaining thrust capability

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent changes the operating parameters from chemical combustion to electrical field acceleration, operating at low power levels (1-100 W) with high specific impulse (1000-10,000 seconds) to achieve efficient propellant usage and reduced mass

Inventive Principle:

Principle #35Parameter changes

2Adaptability or versatility

If propulsion systems are integrated into SmallSats, then mission capabilities are extended, but system mass and volume increase

Engineering Contradiction:

Improvemission capabilitiesVSAvoidsystem mass

Core Design Contradiction:

Adaptability or versatilityVSWeight of moving object

Solution Approach 1:

The patent divides the propulsion system into multiple independent electrospray emitters (arrays of 1-1000+ emitters) that can be independently controlled, allowing the system to be scaled to different mass levels while maintaining overall system functionality and reducing individual component mass

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent designs a universal propulsion system that can perform multiple functions including attitude control, orbit transfer, and debris avoidance using the same electrospray emitter arrays, eliminating the need for separate specialized systems

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Loss of energy

If electrospray thrusters operate at low power levels, then efficiency is improved, but thrust output is reduced

Engineering Contradiction:

Improvepropulsion efficiencyVSAvoidthrust output

Core Design Contradiction:

Loss of energyVSForce

Solution Approach 1:

The patent uses arrays of multiple electrospray emitters where each emitter operates at low power with high efficiency, but the collective thrust of all emitters in the array provides sufficient total thrust output for SmallSat missions

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent changes the operating parameters to optimize the balance between efficiency and thrust by adjusting emitter voltage, propellant flow rate, and emitter geometry to achieve high specific impulse while maintaining adequate thrust through multi-emitter arrays

Inventive Principle:

Principle #35Parameter changes

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 electrospray thrusters provide efficient propulsion with high scalability, reduced propellant mass, and extended mission capabilities, enabling precise attitude control, debris avoidance, and orbit transfers, while being cost-effective and safe for use in small satellites.

Implementation Method 1

electrospray propulsion is based on the electrostatic acceleration of charged droplets and ions produced by the electrospraying of a liquid propellant

Methodology Applied

Scientific EffectElectrostatic acceleration: Electrostatics

Implementation Method 2

electrospray propulsion is based on the electrostatic acceleration of charged droplets and ions produced by the electrospraying of a liquid propellant

Methodology Applied

Scientific EffectElectrospraying: Electrohydrodynamics

Data Source

PatentUS20240392735A1Microfabricated Multiemitter Electrospray Thrusters

Publication Date: 2024.11.28 RGT UNIV OF CALIFORNIA

AI summary

Microfabricated multiemitter electrospray thrusters in accordance with embodiments of the invention are disclosed. In one embodiment, an electrospray thruster for electrospraying at least one liquid propellant is provided, the electrospray thruster comprising: an emitter electrode comprising a backside comprising at least one microfluidic channel, wherein the at least one microfluidic channel provides hydraulic impedance to flow of the at least one liquid propellant, and a front side comprising an emitter array comprising at least one emitter, wherein the at least one emitter comprises an inner channel and an emitter tip: wherein the at least one liquid propellant reaches the emitter tip through the inner channel; and wherein each channel of the at least one microfluidic channel feeds the at least one liquid propellant to the at least one emitter via a hole connecting the at least one microfluidic channel with the inner channel of the at least one emitter.