Ion Propulsion Propellant Transfer Estimation
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Solution Overview
Problem
Existing ion propulsion systems inaccurately estimate propellant transfer between tanks due to lack of real-time updates in pressure and temperature profiles during the transfer process, leading to inaccuracies in flow rate and mass calculations.
Innovation Solution
A method and system that continuously calculate and update the flow rate of propellant through a latch valve based on initial and intermediate pressure and temperature readings, using a computing device to implement a flow equation and polytropic processes to determine mass transfer and pressure equalization, with built-in xenon properties tables for accurate real-time estimation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If propellant transfer estimation is performed using initial pressure and temperature readings only, then the calculation process is simple and fast, but the measurement precision deteriorates due to temperature and pressure changes during transfer
Solution Approach 1:
The system transitions from static initial readings to dynamic continuous monitoring of pressure and temperature during the entire propellant transfer process. Sensors continuously capture state changes, and the calculation system dynamically updates flow rate and mass estimates in real-time, ensuring accuracy despite changing conditions.
Solution Approach 2:
The system implements feedback by continuously monitoring pressure and temperature during transfer and using these updated readings to recalculate propellant mass and flow rate. This closed-loop approach allows the system to adjust estimates based on actual state changes, significantly improving measurement precision.
2Measurement precision
If real-time updates of pressure and temperature profiles are implemented during propellant transfer, then measurement precision improves, but the loss of time increases due to continuous calculations
Solution Approach 1:
The system maintains continuous monitoring and calculation throughout the propellant transfer process without interruption. Pressure and temperature sensors continuously capture data, and the calculation system continuously updates estimates, ensuring that useful measurement action occurs throughout the entire transfer duration rather than only at discrete points.
Solution Approach 2:
The system performs calculations at periodic intervals during the transfer process, updating pressure and temperature readings at regular time steps. This periodic approach balances the need for accurate real-time estimation with computational efficiency, preventing excessive time loss while maintaining precision.
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 accurate, real-time estimation of propellant transfer, preventing phase transition and ensuring accurate measurement by maintaining propellant in a gaseous state, thus extending operational life and precision in ion propulsion systems.
Implementation Method 1
The flow rate is calculated based on an initial pressure and an initial temperature of each of the first tank and the second tank for a beginning of the transfer event and on a determined intermediate pressure for each of the first tank and the second tank for an intermediate time before an end of the transfer event
Implementation Method 2
using a computing device to implement a flow equation and polytropic processes to determine mass transfer and pressure equalization
Data Source
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AI summary
Methods and systems for estimating propellant transfer in an ion propulsion system (200) are disclosed. One example is a method for estimating transfer of a propellant between a first tank (208) and a second tank (210) in an ion propulsion system during a transfer event. The first tank and the second tank are separated by a valve (216). A flow rate of the propellant through the valve is calculated based on an initial pressure and an initial temperature of each of the first tank and the second tank for a beginning of the transfer event, calculating, based at least in part on the flow rate, a mass of propellant transferred through the latch over a period of time ending at an intermediate time before an end of the transfer event, and determining an intermediate pressure and temperature for each of the first tank and the second tank for the intermediate time.