[
  {
    "path": "posts/2021-04-01-air-propulsion-simulation/",
    "title": "Air Propulsion Simulation",
    "description": "Simulating the performace of an air propulsion system as an alternative to solid rocket motors.",
    "author": [
      {
        "name": "Anson Biggs",
        "url": "https://ansonbiggs.com"
      }
    ],
    "date": "2021-04-01",
    "categories": [
      "Julia",
      "Capstone"
    ],
    "contents": "\nBoilerplate intro about why all of this was done\n\n\nShow code\nusing Plots\nplotly()\ntheme(:ggplot2); # In true R spirit\n\nusing Unitful\nusing DataFrames\nusing Measurements\nusing Measurements: value, uncertainty\n\nThis code is just the setup, using values scraped from various parts of the world wide web.\n\n# Tank https://www.amazon.com/Empire-Paintball-BASICS-Pressure-Compressed/dp/B07B6M48SR/\nV = (85 ± 5)u\"inch^3\"\nP0 = (4200.0 ± 300)u\"psi\"\nWtank = (2.3 ± 0.2)u\"lb\"\nPmax = (250 ± 50)u\"psi\" # Max Pressure that can come out the nozzle\n\nWsolenoid = 1.5u\"kg\"\n\n# Params\nd_nozzle = ((1 // 18) ± 0.001)u\"inch\"\na_nozzle = (pi / 4) * d_nozzle^2\n\n# Universal Stuff\nP_amb = (1 ± 0.2)u\"atm\"\nγ = 1.4 ± 0.05\nR = 287.05u\"J/(kg * K)\"\nT = (300 ± 20)u\"K\"\n\nThis is the actual simulation. Maybe throw some references in and explain some equations.\nThe rocket equation is pretty sick:\n\\[T = \\dot{m} \\cdot v_\\text{Exit} + A_\\text{Nozzle} \\cdot (P - P_\\text{Ambient}) \\] And thats about all you need to get to the moon(Curtis 2020).\n\nlet\nt = 0.0u\"s\"\nP = P0 |> u\"Pa\"\nM = V * (P / (R * T)) |> u\"kg\"\nts = 1u\"ms\"\nglobal df = DataFrame(Thrust=(0 ± 0)u\"N\", Pressure=P0, Time=0.0u\"s\", Mass=M)\n  while M > 0.005u\"kg\"\n      # while t < 30u\"s\"\n      # Calculate what is leaving tank\n      P = minimum([P, Pmax])\n      ve = sqrt((2 * γ / (γ - 1)) * R * T * (1 - P_amb / P)^((γ - 1) / γ)) |> u\"m/s\"\n      ρ = P / (R * T) |> u\"kg/m^3\"\n      ṁ = ρ * a_nozzle * ve |> u\"kg/s\"\n  \n      Thrust = ṁ * ve + a_nozzle * (P - P_amb) |> u\"N\"\n  \n      # Calculate what is still in the tank\n      M = M - ṁ * ts |> u\"kg\"\n      P = (M * R * T) / V |> u\"Pa\"\n      t = t + ts\n  \n      df_step = DataFrame(Thrust=Thrust, Pressure=P, Time=t, Mass=M)\n      append!(df, df_step)\n  end\nend\n\nHeres the results plotted. Notice the massive error once the tank starts running low.\n\n\n\nBig conclusion about things.\n\n\n\nCurtis, Howard D. 2020. Orbital Mechanics for Engineering Students. Fourth edition. Butterworth-Heinemann Publications.\n\n\n\n\n",
    "preview": "posts/2021-04-01-air-propulsion-simulation/air-propulsion-simulation_files/figure-html5/unnamed-chunk-4-J1.png",
    "last_modified": "2021-04-01T23:23:11-07:00",
    "input_file": {}
  },
  {
    "path": "posts/welcome/",
    "title": "Welcome to Anson's Projects",
    "description": "Welcome to our new blog, Anson's Projects. We hope you enjoy \nreading what we have to say!",
    "author": [
      {
        "name": "Nora Jones",
        "url": "https://example.com/norajones"
      }
    ],
    "date": "2021-04-01",
    "categories": [],
    "contents": "\n\n\n\n",
    "preview": {},
    "last_modified": "2021-04-01T20:38:44-07:00",
    "input_file": {}
  }
]