Iodine Propellant Delivery for Pressure-Free Electric Thrusters
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Solution Overview
Problem
Existing electric thrusters for aerospace systems face high costs and weight issues due to the use of xenon gas as propellant, which requires pressure tanks and is not suitable for secondary payloads.
Innovation Solution
A propellant delivery system using iodine as an alternative propellant, which can be stored in a solid state and converted to gas using thermal energy from waste heat, eliminating the need for pressure tanks and allowing for a cost-effective, energy-efficient, and lightweight thruster design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If xenon gas is used as propellant, then good discharge properties and relatively high atomic mass are achieved, but high costs and need for pressure tanks occur
Solution Approach 1:
The patent changes the physical state parameter of the propellant from gaseous (xenon requiring pressure tanks) to solid (iodine crystals), eliminating the need for pressure containment systems while maintaining suitable discharge properties through controlled sublimation and vaporization
Solution Approach 2:
The patent uses iodine as a substitute material that copies the essential functional properties of xenon (atomic mass, ionization characteristics) while avoiding its drawbacks (cost, storage requirements), achieving similar thruster performance without pressure tanks
2Weight of moving object
If iodine is used as propellant, then cost and weight are reduced by eliminating pressure tanks, but additional heating devices are required to convert solid iodine to gas
Solution Approach 1:
The patent merges the heating function into the existing thruster structure by using the discharge chamber and anode as heating elements. The electrical discharge that accelerates ions also provides the thermal energy needed to sublime solid iodine and vaporize it, combining two functions into one system component
Solution Approach 2:
The thruster system serves itself by using its own operational energy (electrical discharge) to perform the phase conversion of propellant. The waste heat and electrical field from the thruster operation automatically sublimate the iodine, eliminating the need for separate heating devices
3Use of energy by moving object
If waste heat is used to convert iodine to gas, then energy efficiency is improved, but precise control of propellant flow becomes more difficult
Solution Approach 1:
The patent implements feedback control by monitoring the thruster's operational parameters (current, voltage, temperature) and using this information to regulate the iodine supply rate. The control system adjusts the propellant flow based on the actual thermal and electrical conditions, maintaining precise control while utilizing waste heat efficiently
Solution Approach 2:
The patent employs dynamic adjustment of propellant delivery based on real-time thruster conditions. The system adapts the iodine vaporization rate and flow control according to varying operational demands, allowing precise control despite using thermal energy from dynamic discharge processes
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 efficiently converts iodine into a gaseous state using waste heat, reducing system weight and costs, and allows for precise control of propellant flow, enabling efficient operation of electric thrusters without the need for additional heating devices.
Implementation Method 1
The expansion actuator comprises a material which changes its volume as a result of a change in temperature. For example, the material of the expansion actuator can expand when it is heated.
Implementation Method 2
The heater can be adapted to deliver thermal energy to the pipe and/or to the propellant on and/or in the pipe.
Implementation Method 3
The propellant can thereby be converted into the gaseous state and kept in the gaseous state by the thermal energy delivered by the heater. As a result of being converted into the gaseous state, the propellant expands and is able to flow through the pipe.
Implementation Method 4
The pipe is made of a thermally conducting material, such as, for example, aluminum, steel or aluminum nitride. Owing to the thermal conductivity of the pipe, it is also possible to transmit heat from the heater via the pipe to the expansion actuator
Data Source
AI summary
An electric thruster comprises a propellant delivery system, wherein the propellant delivery system comprises: a pipe for carrying propellant; a valve which is adapted to adjust a volume or mass flow of the propellant in the pipe; and an expansion actuator which is adapted to actuate the valve for adjusting the volume or mass flow of the propellant. The electric thruster further comprises at least one tank which is adapted to receive propellant for the electric thruster; and a discharge chamber. The at least one tank thereby at least partially encloses an end of the discharge chamber and/or an element thermally coupled with the discharge chamber, and the valve of the propellant delivery system is arranged between the tank and the end of the discharge chamber.