PSPL_Rocket_A_Sizing/inputs.py at main · Purdue-Space-Program/PSPL_Rocket_A_Sizing · GitHub

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import coding_utils.constants as c
import numpy as np

step_size = 20 # number of values to use for each variable input
# DONT GOT OVER 30 FOR 3D GRAPHS ITS SLOW ASF, 20 IS A GOOD NUMBER

# A dictionary used to define the possible definitions where each key is an input (constant or variable)
# and each value is either the constant value or a range of values

# rocket_definition_inputs_scope = {

variable_inputs = {
    # "FUEL_NAME":                  ["Ethanol", "Kerosene"],

    "OF_RATIO":                   np.linspace(0.2, 3, step_size), # [dimensionless] ratio of oxygen to fuel by mass
    # "CHAMBER_PRESSURE":           np.linspace(80, 500, step_size) * c.PSI2PA, # [pa] pressure in the chamber during combustion


    # "FUEL_TANK_LENGTH":   np.linspace(6 * c.IN2M, 3 * c.FT2M, step_size), # [meters] speedy metals pipe lengths: https://www.speedymetals.com/pc-4648-8371-6-od-x-0125-wall-tube-6061-t6-aluminum.aspx
    "CONTRACTION_RATIO":          np.linspace(3, 8, step_size), # [dimensionless] area ratio of chamber to throat (3 to 6 recommended by textbook)

    # "OXIDIZER_ON_TOP_FUEL_ON_BOTTOM": [True, False], # [boolean (true or false)] whether the oxidizer tank is above the fuel tank or not

    # "a":   np.linspace(6 * c.IN2M, 288 * c.IN2M, step_size), # stress testing
    # "b":   np.linspace(6 * c.IN2M, 288 * c.IN2M, step_size), # stress testing
    # "c":   np.linspace(6 * c.IN2M, 288 * c.IN2M, step_size), # stress testing
    # "d":   np.linspace(6 * c.IN2M, 288 * c.IN2M, step_size), # stress testing
    # "e":   np.linspace(6 * c.IN2M, 288 * c.IN2M, step_size), # stress testing
    # "f":   np.linspace(6 * c.IN2M, 288 * c.IN2M, step_size), # stress testing
    # "g":   np.linspace(6 * c.IN2M, 288 * c.IN2M, step_size), # stress testing
}

constant_inputs = {
    "CHAMBER_PRESSURE":                         100 * c.PSI2PA, # [psi] pressure in the chamber during combustion
    # "OF_RATIO":                                 1.5, # [dimensionless] ratio of oxygen to fuel by mass

    "FUEL_TANK_LENGTH":                         4 * c.FT2M, # [meters] speedy metals pipe lengths: https://www.speedymetals.com/pc-4648-8371-6-od-x-0125-wall-tube-6061-t6-aluminum.aspx
    # "CONTRACTION_RATIO":                        2.5, # [dimensionless] area ratio of chamber to throat (3 to 6 recommended by textbook)

    "FUEL_NAME":                                "IPA",
    # "FUEL_NAME":                                "Ethanol",

    "OXIDIZER_NAME":                            "Liquid Oxygen",

    "PROPELLANT_TANK_OUTER_DIAMETER":           6.0 * c.IN2M, # [meters] from speedy metals pipe (link above)
    "PROPELLANT_TANK_THICKNESS":                0.125 * c.IN2M,   # [meters] from speedy metals pipe (link above)

    # "ALUMINUM_ENGINE_COVER_OUTER_DIAMETER":   4.5   * c.IN2M, # [meters] from speedy metals pipe (link above)
    # "ALUMINUM_ENGINE_COVER_INNER_DIAMETER":   4.25  * c.IN2M, # [meters] from speedy metals pipe (link above)
    # "ALUMINUM_ENGINE_COVER_THICKNESS":        0.125 * c.IN2M, # [meters] from speedy metals pipe (link above)
    # "GRAPHITE_CHAMBER_OUTER_DIAMETER":        4.25  * c.IN2M, # [meters] the same diameter as "ALUMINUM_ENGINE_COVER_INNER_DIAMETER" since they're touching
    # "GRAPHITE_CHAMBER_INNER_DIAMETER":        4.00  * c.IN2M, # [meters] this will be the diameter of the volume where combustion occurs
    # "GRAPHITE_CHAMBER_THICKNESS":             0.125 * c.IN2M, # [meters]
}

constant_inputs["PROPELLANT_TANK_INNER_DIAMETER"] = constant_inputs["PROPELLANT_TANK_OUTER_DIAMETER"] - (2 * constant_inputs["PROPELLANT_TANK_THICKNESS"])


if __name__ == "__main__":
    import main # dumbahh