Merge branch 'monte-carlo' into 'master'

Uncertainty to Calculations

See merge request lander-team/air-prop-simulation!1

calcs.jl

@@ -1,124 +0,0 @@
-### A Pluto.jl notebook ###
-# v0.12.20
-
-using Markdown
-using InteractiveUtils
-
-# This Pluto notebook uses @bind for interactivity. When running this notebook outside of Pluto, the following 'mock version' of @bind gives bound variables a default value (instead of an error).
-macro bind(def, element)
-    quote
-        local el = $(esc(element))
-        global $(esc(def)) = Core.applicable(Base.get, el) ? Base.get(el) : missing
-        el
-    end
-end
-
-# ╔═╡ 7d1e8730-81f7-11eb-0b4d-d7c878032280
-begin
-	using Unitful
-	using Roots
-	using PlutoUI
-end
-
-# ╔═╡ d8461f50-833d-11eb-04f2-f9e262a97ba5
-md"## Air Compressor Thrust Calcs"
-
-# ╔═╡ 2a976cf0-833e-11eb-3892-03869a9b0acc
-html"<button onclick='present()'>present</button>"
-
-# ╔═╡ b0efd6c2-81f9-11eb-2aad-efc9bdd8c220
-@bind diam Slider(0.1:.1:6.5, default=.5)
-
-# ╔═╡ bc06c722-81fa-11eb-05ac-e38ac21ce27e
-@bind p Slider(15:6000, default=126)
-
-# ╔═╡ 99835750-81fe-11eb-3a7e-1132eb3cdd90
-@bind w Slider(.5:.25:20, default=5)
-
-# ╔═╡ a9f59000-81f7-11eb-15c0-4520acb6543f
-begin
-	M = w*u"kg"
-	
-	P_amb = 1u"atm"
-	P_c = p*u"psi"
-	
-	d_nozzle = diam*u"mm"
-	a_nozzle = (pi/4)*d_nozzle^2
-	
-	γ = 1.4
-	R = 287.05u"J/(kg * K)"
-	T = 300u"K"
-	
-	burn_time = 5u"s"
-	
-	V = 68u"inch^3"
-end;
-
-# ╔═╡ 764dcf30-81fa-11eb-3155-559823202b8f
-md"Area of Nozzle: $(a_nozzle) | $(round(u\"inch^2\",a_nozzle, digits = 4))"
-
-# ╔═╡ b4a957a0-833e-11eb-1ca9-0d87d162790f
-md"Diameter of Nozzle: $(d_nozzle) | $(round(u\"inch\",d_nozzle, digits = 4))"
-
-# ╔═╡ a7bef990-81fa-11eb-3976-817c3e383e64
-md"Pressure of system: $(P_c)"
-
-# ╔═╡ b113c030-81fe-11eb-2042-776472e720ac
-md"Mass of Lander: $(M) | $(round(u\"lb\",M, digits = 2))"
-
-# ╔═╡ a9317cb0-81f7-11eb-26e5-95719252409b
-begin 
-	ve = sqrt((2 * γ / (γ - 1)) * R * T * (1 - P_amb / P_c)^((γ - 1) / γ)) |> u"m/s"
-	
-	ρ = P_c / (R * T) |> u"kg/m^3"
-	ṁ = ρ * a_nozzle * ve |> u"kg/s"
-end;
-
-# ╔═╡ cf5b7030-846d-11eb-2f23-290624c7d684
-M_air = ρ*V |> u"kg"
-
-# ╔═╡ 2149b640-846e-11eb-262b-299ded0c61c5
-M_air / ṁ
-
-# ╔═╡ c57fe2d0-81f7-11eb-27d7-4b5c0520998d
-Thrust = ṁ * ve + a_nozzle * (P_c - P_amb) |> u"N"
-
-# ╔═╡ 213ef2c0-81fb-11eb-1425-15bfcf1dc14c
-volume_air = ṁ * burn_time / ρ |> u"inch^3";
-
-# ╔═╡ 9388c570-833d-11eb-3baa-758b5cb19065
-md"Air Needed: $(round(ustrip(volume_air/burn_time)*.004329,digits=3)) Gallon/s"
-
-# ╔═╡ e85b0e90-81fe-11eb-0dd5-0b3df376a4f7
-begin
-	W_earth = 9.81u"m/s^2" * M |> u"N"
-	W_moon = 1.623u"m/s^2" * M |> u"N"
-end;
-
-# ╔═╡ 57844480-833a-11eb-3a57-bf00cecde849
-md"Thrust to Weight Ratio Earth: $(Thrust/W_earth)"
-
-# ╔═╡ a5c735d0-833a-11eb-2bae-71ba4af6b3a1
-md"Thrust to Weight Ratio Moon: $(Thrust/W_moon)"
-
-# ╔═╡ Cell order:
-# ╟─d8461f50-833d-11eb-04f2-f9e262a97ba5
-# ╟─2a976cf0-833e-11eb-3892-03869a9b0acc
-# ╟─7d1e8730-81f7-11eb-0b4d-d7c878032280
-# ╟─764dcf30-81fa-11eb-3155-559823202b8f
-# ╟─b4a957a0-833e-11eb-1ca9-0d87d162790f
-# ╟─b0efd6c2-81f9-11eb-2aad-efc9bdd8c220
-# ╟─a7bef990-81fa-11eb-3976-817c3e383e64
-# ╠═bc06c722-81fa-11eb-05ac-e38ac21ce27e
-# ╟─b113c030-81fe-11eb-2042-776472e720ac
-# ╠═99835750-81fe-11eb-3a7e-1132eb3cdd90
-# ╠═a9f59000-81f7-11eb-15c0-4520acb6543f
-# ╠═a9317cb0-81f7-11eb-26e5-95719252409b
-# ╠═2149b640-846e-11eb-262b-299ded0c61c5
-# ╠═cf5b7030-846d-11eb-2f23-290624c7d684
-# ╠═c57fe2d0-81f7-11eb-27d7-4b5c0520998d
-# ╟─213ef2c0-81fb-11eb-1425-15bfcf1dc14c
-# ╠═9388c570-833d-11eb-3baa-758b5cb19065
-# ╟─e85b0e90-81fe-11eb-0dd5-0b3df376a4f7
-# ╟─57844480-833a-11eb-3a57-bf00cecde849
-# ╟─a5c735d0-833a-11eb-2bae-71ba4af6b3a1

readme.md

@@ -0,0 +1,8 @@
+# Air Prop Thrust 
+Total Impulse: 405.0 ± 39.0 N s
+
+![Thrust Over Time](ThrustCurve.png)
+
+More Data:
+
+<table class="data-frame"><thead><tr><th></th><th>variable</th><th>mean</th><th>min</th><th>median</th><th>max</th><th>nmissing</th><th>eltype</th></tr><tr><th></th><th>Symbol</th><th>Quantity</th><th>Quantity</th><th>Quantity</th><th>Quantity</th><th>Int64</th><th>DataType</th></tr></thead><tbody><p>4 rows × 7 columns</p><tr><th>1</th><td>Thrust</td><td>69.0±6.7 N</td><td>0.0±0.0 N</td><td>86.7±9.2 N</td><td>86.7±9.2 N</td><td>0</td><td>Quantity{Measurement{Float64}, 𝐋 𝐌 𝐓^-2, FreeUnits{(N,), 𝐋 𝐌 𝐓^-2, nothing}}</td></tr><tr><th>2</th><td>Pressure</td><td>1.21e7±2.0e6 Pa</td><td>620000.0±440000.0 Pa</td><td>1.12e7±2.8e6 Pa</td><td>2.9e7±2.1e6 Pa</td><td>0</td><td>Quantity{Measurement{Float64}, 𝐌 𝐋^-1 𝐓^-2, FreeUnits{(Pa,), 𝐌 𝐋^-1 𝐓^-2, nothing}}</td></tr><tr><th>3</th><td>Time</td><td>2.9325 s</td><td>0.0 s</td><td>2.9325 s</td><td>5.865 s</td><td>0</td><td>Quantity{Float64, 𝐓, FreeUnits{(s,), 𝐓, nothing}}</td></tr><tr><th>4</th><td>Mass</td><td>0.196±0.043 kg</td><td>0.01±0.0077 kg</td><td>0.181±0.054 kg</td><td>0.468±0.053 kg</td><td>0</td><td>Quantity{Measurement{Float64}, 𝐌, FreeUnits{(kg,), 𝐌, nothing}}</td></tr></tbody></table>

thrust.jl

@@ -4,33 +4,36 @@ using Plots
 using UnitfulRecipes
 using Roots
 using CSV
+using Measurements
+using Printf
 
 
 # Tank https://www.amazon.com/Empire-Paintball-BASICS-Pressure-Compressed/dp/B07B6M48SR/
-V = 90u"inch^3"
-P0 = 4500.0u"psi"
-Wtank = 2.3u"lb"
-Pmax = 100u"psi"
+V = (85 ± 5)u"inch^3"
+P0 = (4200.0 ± 300)u"psi"
+Wtank = (2.3 ± 0.2)u"lb"
+Pmax = (800 ± 50)u"psi"
 
 Wsolenoid = 1.5u"kg"
 
 # Params
-d_nozzle = (1 // 16) * u"inch"
+d_nozzle = ((1 // 16) ± 0.001)u"inch"
 a_nozzle = (pi / 4) * d_nozzle^2
-Poutmax = 800u"psi"
+Poutmax = (800 ± 50)u"psi"
 
 # Universal Stuff
-P_amb = 1u"atm"
-γ = 1.4
+P_amb = (1 ± 0.2)u"atm"
+γ = 1.4 ± 0.05
 R = 287.05u"J/(kg * K)"
-T = 300u"K"
+T = (300 ± 20)u"K"
 
 # Setting up while loop
-t = 1.0u"s"
+t = 0.0u"s"
 P = P0 |> u"Pa"
 M = V * (P / (R * T)) |> u"kg"
-df = DataFrame(Thrust = 0.0u"N", Pressure = P, Time = t, Mass = M)
-ts = 0.001u"s"
+ts = 1u"ms"
+df = DataFrame(Thrust = (0 ± 0)u"N", Pressure = P, Time = t, Mass = M)
+
 while M > 0.01u"kg"
     # while t < 30u"s"
     # Calculate what is leaving tank
@@ -49,11 +52,38 @@ while M > 0.01u"kg"
     df_step = DataFrame(Thrust = Thrust, Pressure = P, Time = t, Mass = M)
     append!(df, df_step)
 end
+
+impulse = sum(df.Thrust) * ts |> u"N*s"
 println("---------------------------\n\n\n\n")
-println("Total Impulse: ", sum(df.Thrust) * ts)
+println("Total Impulse: ", impulse)
 println("Burn Time: ", t)
+
 println("Mass Total: ", Wtank + Wsolenoid + maximum(df.Mass))
 
+
 print(describe(df))
-plot(df.Time, df.Thrust, title = "Thrust Over Time")
-CSV.write("thrustdata.csv", df .|> ustrip)
+
+plot(df.Time[1:150:end], df.Thrust[1:150:end], title = "Thrust Over Time")
+
+### Save data to readme.md
+
+savefig("ThrustCurve.png")
+
+b = IOBuffer();
+t = TextDisplay(b);
+display(t, "text/html", describe(df));
+table = String(take!(b)); # https://stackoverflow.com/a/60443621/8774114
+
+
+readme = Printf.@sprintf """
+# Air Prop Thrust 
+Total Impulse: %s
+
+![Thrust Over Time](ThrustCurve.png)
+
+More Data:
+
+%s
+""" impulse table
+
+write("readme.md", readme)