mirror of
https://gitlab.com/lander-team/air-prop-simulation.git
synced 2025-07-23 22:51:35 +00:00
60 lines
1.4 KiB
Julia
60 lines
1.4 KiB
Julia
using Unitful
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using DataFrames
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using Plots
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using UnitfulRecipes
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using Roots
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using CSV
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# Tank https://www.amazon.com/Empire-Paintball-BASICS-Pressure-Compressed/dp/B07B6M48SR/
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V = 90u"inch^3"
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P0 = 4500.0u"psi"
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Wtank = 2.3u"lb"
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Pmax = 100u"psi"
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Wsolenoid = 1.5u"kg"
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# Params
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d_nozzle = (1 // 16) * u"inch"
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a_nozzle = (pi / 4) * d_nozzle^2
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Poutmax = 800u"psi"
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# Universal Stuff
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P_amb = 1u"atm"
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γ = 1.4
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R = 287.05u"J/(kg * K)"
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T = 300u"K"
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# Setting up while loop
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t = 1.0u"s"
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P = P0 |> u"Pa"
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M = V * (P / (R * T)) |> u"kg"
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df = DataFrame(Thrust = 0.0u"N", Pressure = P, Time = t, Mass = M)
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ts = 0.001u"s"
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while M > 0.01u"kg"
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# while t < 30u"s"
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# Calculate what is leaving tank
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P = minimum([P, Pmax])
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ve = sqrt((2 * γ / (γ - 1)) * R * T * (1 - P_amb / P)^((γ - 1) / γ)) |> u"m/s"
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ρ = P / (R * T) |> u"kg/m^3"
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ṁ = ρ * a_nozzle * ve |> u"kg/s"
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Thrust = ṁ * ve + a_nozzle * (P - P_amb) |> u"N"
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# Calculate what is still in the tank
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M = M - ṁ * ts |> u"kg"
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P = (M * R * T) / V |> u"Pa"
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t = t + ts
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df_step = DataFrame(Thrust = Thrust, Pressure = P, Time = t, Mass = M)
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append!(df, df_step)
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end
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println("---------------------------\n\n\n\n")
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println("Total Impulse: ", sum(df.Thrust) * ts)
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println("Burn Time: ", t)
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println("Mass Total: ", Wtank + Wsolenoid + maximum(df.Mass))
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print(describe(df))
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plot(df.Time, df.Thrust, title = "Thrust Over Time")
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CSV.write("thrustdata.csv", df .|> ustrip)
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