# Ion-Propulsion-system-comparison-tool The python code has the following dependencies - 1) tkinter 2) pandas 3) matplotlib Note: Make sure you have the Engine list in the same folder as the code. The Log and the graphs would be saved in the same folder. The "Ion Propulsion system comparison tool" takes in the following user inputs - 1) Base Mass ( = Structure+Payload i.e. everything besides the power and the propulsion subsystem (= Propellant mass + Tank mass) 2) Delta-V 3) Specific power of RTG (Radioisotope thermoelectric generator) in W/kg 4) List of Engines in .xlsx format (Sample included (sourced from manufacturer websites) in the repository) Engine List should have the following information (in the same order as in the sample) 4.1) Engine Name 4.2) Engine Mass 4.2) ISP 4.3) Thrust 4.4) Power Requirement 5) Operating Temperature of propellant 6) Tank Material Density 7) Yield Strength of tank material 8) Critical Pressure of gas 9) Critical Temperature of gas 10) Molecular mass of gas 11) Factor of safety (tank) Note: The code does not take voltage and current into account And then calculates - 1) Total Mass of spacecraft 2) Propellant Volume 3) Propellant Density 4) Tank wall thickness 5) Tank Pressure Apart from display in the UI (made using Tkinter) a 'Log' is also generated Sample 'Log' output - Engine:............|Qinetiq T6 (1kw) ISP:...............|4500.0s Thrust:............|0.039N Total Mass:........|1482.206kg --Base Mass:.......|450kg --Propellant Mass:.|623.906kg --Power Mass:......|400.0kg --Tank Mass:.......|476.423kg Propellant Volume:.|0.465m^3 Propellant Density:|1342.098kg/m^3 Power Requirement:.|1000.0W Tank Thickness:....|35.093mm Tank Pressure:.....|8.179MPa
anant347/Ion-Propulsion-system-comparison-tool
A python GUI app that helps a user to compare various ion engines by plotting a 'Total spacecraft mass by thrust' graph and generating a log that includes various calculated parameters.
PythonMIT