Electric Propulsion Thruster Using Dual Metallic and Non-Metallic Propellants
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Solution Overview
Problem
Spacecraft require multiple thruster systems for metallic and non-metallic propellants due to contamination issues and thrust efficiency, leading to increased volume, mass, complexity, and cost.
Innovation Solution
A propulsion system with electric thrusters that can selectively use either metallic or non-metallic propellants, stored at appropriate densities and pressures, and a control system to manage propellant supply based on operational needs, including a metallic propellant storage tank with a heater and pressurant system and a non-metallic propellant storage tank capable of holding gas or supercritical fluid.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a metallic propellant is used in a thruster system, then high thrust levels are achieved, but propellant contamination occurs on surfaces and sensitive instruments
Solution Approach 1:
The patent applies multi-functionality by enabling a single electric propulsion thruster to operate with both metallic and non-metallic propellants. The thruster system is designed with universal compatibility to accept different propellant types based on mission requirements, allowing high-thrust metallic propellant operations when contamination is not an issue, and clean non-metallic propellant operations when instruments are deployed, all through one integrated system rather than requiring separate dedicated thrusters for each propellant type
2Object-affected harmful factors
If a non-metallic gas is used as a propellant, then contamination issues are avoided, but thrust levels are reduced and storage volume increases
Solution Approach 1:
The electric propulsion thruster is designed with universal compatibility to accept both metallic and non-metallic propellants, allowing the system to switch between propellant types based on mission requirements. This enables the use of non-metallic propellants for contamination-sensitive operations while maintaining the capability to use metallic propellants for high-thrust requirements, all through one integrated thruster system
3Object-affected harmful factors
If multiple separate thruster systems are included for metallic and non-metallic propellants, then both high thrust and contamination-free operation are achieved, but spacecraft volume, mass, complexity, and cost increase
Solution Approach 1:
The patent implements a single electric propulsion thruster that can operate with both metallic and non-metallic propellants, replacing the need for multiple separate thruster systems. This universal thruster design reduces spacecraft volume, mass, and complexity while maintaining the capability to achieve both high-thrust metallic propellant operations and contamination-free non-metallic propellant operations based on mission requirements
Solution Approach 2:
The patent merges the functionality of separate metallic and non-metallic propellant thruster systems into a single integrated electric propulsion thruster. By combining these previously separate systems into one unit that can accept both propellant types, the patent reduces the number of components, simplifies the overall system architecture, and decreases spacecraft volume and mass while maintaining all required operational capabilities
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
Enables efficient and flexible propulsion with reduced contamination risks and mass, while maintaining high thrust levels, by allowing the electric thruster to switch between propellants based on mission requirements, thereby simplifying spacecraft design and operation.
Implementation Method 1
The metallic propellant storage tank can include or be associated with a heater and/or a pressurant system for dispensing the metallic propellant
Implementation Method 2
The metallic propellant storage tank can include or be associated with a heater and/or a pressurant system for dispensing the metallic propellant
Data Source
AI summary
Spacecraft propulsion systems and methods featuring a first storage tank containing a metallic propellant and a second storage tank containing a non-metallic propellant are provided. A selected one of the metallic propellant and the non-metallic propellant is supplied to an electric propulsion thruster, depending on an operational mode of the spacecraft. The metallic propellant is stored at a relatively high density, while the non-metallic propellant is stored at a lower density than the metallic propellant. Moreover, the non-metallic propellant is preferably utilized to produce thrust through the electric propulsion thruster during operational maneuvers, while the metallic propellant is reserved for producing thrust through the electric propulsion thruster during end-of-life, such as deorbiting, maneuvers.