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more work on orbits example
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index.jl
107
index.jl
@ -378,8 +378,24 @@ md"""
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# ╔═╡ f6d87354-ac46-4202-92f8-b39a0db13327
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# ╔═╡ f6d87354-ac46-4202-92f8-b39a0db13327
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μ = 3.986004418e14u"m^3/s^2" # Standard Gravitational Parameter for Earth
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μ = 3.986004418e14u"m^3/s^2" # Standard Gravitational Parameter for Earth
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# ╔═╡ f8039870-2570-47d0-8d46-30922415ec9d
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earth_radius = 6378u"km"
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# ╔═╡ 863cd607-a459-49ae-9049-983f3374f523
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abstract type Orbit end
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# ╔═╡ 44daff45-f608-47e3-ad6e-fca43532f322
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# ╔═╡ 44daff45-f608-47e3-ad6e-fca43532f322
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struct Elliptic_Orbit
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struct Circular_Orbit <: Orbit
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"""Simple 2d circular orbit"""
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r::typeof(.1u"km") # altitude
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end
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# ╔═╡ efb58b79-24e4-45c6-ad45-aeaa339d82fd
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ISS = Circular_Orbit(420u"km")
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# ╔═╡ ad3a2b19-5639-4d11-8d89-bc54772d639b
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struct Elliptic_Orbit <: Orbit
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"""Simple 2d elliptic orbit"""
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"""Simple 2d elliptic orbit"""
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r::typeof(.1u"km") # altitude
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r::typeof(.1u"km") # altitude
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a::typeof(.1u"km") # semimajor axis
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a::typeof(.1u"km") # semimajor axis
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@ -387,48 +403,70 @@ struct Elliptic_Orbit
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function Elliptic_Orbit(r, a, e)
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function Elliptic_Orbit(r, a, e)
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@assert e < 1 "Eccentricity must be less than 1!"
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@assert e < 1 "Eccentricity must be less than 1!"
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@assert 0 < e "Eccentricity must be greater than 0!"
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new(r, a, e)
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new(r, a, e)
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end
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end
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function Elliptic_Orbit(r)
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new(r,r,0) # we'll pretend circular orbits count for this example
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function Elliptic_Orbit(perigee, apogee)
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a = (perigee + apogee) / 2
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e = 1 - (perigee/a)
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r = a*((1-e^2)/(1+e)) # Assume θ is 0 since we aren't keeping track of it
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Elliptic_Orbit(r,a,e)
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end
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end
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end
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end
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# ╔═╡ b4e08868-d48a-4f66-9d20-f45ea4d83f00
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# ╔═╡ efb58b79-24e4-45c6-ad45-aeaa339d82fd
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sat = Elliptic_Orbit(earth_radius+537.0u"km", earth_radius+9040.9u"km")
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ISS = Elliptic_Orbit(420u"km")
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# ╔═╡ 3efd8a29-6a56-4f5c-9cab-0f08875b2064
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# ╔═╡ 3efd8a29-6a56-4f5c-9cab-0f08875b2064
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function get_velocity(o::Circular_Orbit)
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v = sqrt(μ/o.r)
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return v |> u"km/s"
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end
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# ╔═╡ 59207a25-fa6d-4369-979d-cd9cc2f094cf
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function get_velocity(o::Elliptic_Orbit)
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function get_velocity(o::Elliptic_Orbit)
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v = sqrt(μ*(2/o.r - 1/o.a))
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v = sqrt(μ*(2/o.r - 1/o.a))
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return v |> u"km/s"
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return v |> u"km/s"
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end
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end
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# ╔═╡ 59207a25-fa6d-4369-979d-cd9cc2f094cf
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# ╔═╡ 11fb3a28-edf3-46ff-8c4a-5286793b6e43
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function get_period(o::Elliptic_Orbit)
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T = 2*π*sqrt(o.a^3/μ)
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return T |> u"s"
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end
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# ╔═╡ 5a4b673b-babb-4e11-a292-d71087fa32bc
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# ╔═╡ a6c72acc-39fc-4dfc-8126-64c6b35145d1
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get_period(ISS)
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# ╔═╡ d79a6752-77ba-496f-96c3-d9904db0a46b
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get_velocity(ISS)
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get_velocity(ISS)
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# ╔═╡ 026321df-6991-4b59-aaba-c467b267a477
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# ╔═╡ 79a9ab94-06a8-4613-8f60-358e08f0f32e
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whatsit(u"m")
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get_velocity(sat)
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# ╔═╡ 3955b9d6-7514-4712-ba22-929afda3c77c
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typeof(1.1u"km")
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# ╔═╡ a7bacb81-0f19-4d2d-9588-61e912689001
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Elliptic_Orbit(1,2,.9)
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# ╔═╡ c3d943b4-809d-4a96-a99d-be7653ba2c8b
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# ╔═╡ c3d943b4-809d-4a96-a99d-be7653ba2c8b
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begin
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function Plots.plot(orbit::Elliptic_Orbit)
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a = orbit.a |> u"km" |> ustrip
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b = orbit.a*sqrt(1-orbit.e^2) |> u"km" |> ustrip
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t = 0:.01:2π
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x_orbit(t) = a*cos(t)
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y_orbit(t) = b*sin(t)
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plot(x_orbit, y_orbit, t)
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x_earth(t) = ustrip(earth_radius)*cos(t) + a*orbit.e
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y_earth(t) = ustrip(earth_radius)*sin(t)
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plot!(x_earth,y_earth, t, c=:gray,fill=(0,:blue), legend=false,aspect_ratio=:equal)
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title!("Satellite Orbiting Earth")
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end
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plot(sat)
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end
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# ╔═╡ 01ba1742-d26e-4271-ab62-0bd9ce5e291d
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function get_ΔV(start::Orbit, final::Orbit)
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get_velocity(start) - get_velocity(final)
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end
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# ╔═╡ ad4d24a8-f601-4522-a3eb-c01f6fd68aec
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get_ΔV(ISS,sat)
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# ╔═╡ 2d0de5db-5558-41e0-96d5-a3317d151aff
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# ╔═╡ 8924673f-e99c-44b3-be6d-2abf0b2f5e23
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# ╔═╡ 8924673f-e99c-44b3-be6d-2abf0b2f5e23
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@ -1401,17 +1439,20 @@ version = "0.9.1+5"
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# ╠═9ea4584c-8177-4f69-9739-b2faa93281a8
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# ╠═9ea4584c-8177-4f69-9739-b2faa93281a8
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# ╠═f43812d2-9f87-489a-9317-e7aa19ffd3bc
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# ╠═f43812d2-9f87-489a-9317-e7aa19ffd3bc
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# ╠═f6d87354-ac46-4202-92f8-b39a0db13327
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# ╠═f6d87354-ac46-4202-92f8-b39a0db13327
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# ╠═f8039870-2570-47d0-8d46-30922415ec9d
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# ╠═863cd607-a459-49ae-9049-983f3374f523
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# ╠═44daff45-f608-47e3-ad6e-fca43532f322
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# ╠═44daff45-f608-47e3-ad6e-fca43532f322
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# ╠═efb58b79-24e4-45c6-ad45-aeaa339d82fd
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# ╠═efb58b79-24e4-45c6-ad45-aeaa339d82fd
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# ╠═ad3a2b19-5639-4d11-8d89-bc54772d639b
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# ╠═b4e08868-d48a-4f66-9d20-f45ea4d83f00
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# ╠═3efd8a29-6a56-4f5c-9cab-0f08875b2064
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# ╠═3efd8a29-6a56-4f5c-9cab-0f08875b2064
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# ╠═59207a25-fa6d-4369-979d-cd9cc2f094cf
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# ╠═59207a25-fa6d-4369-979d-cd9cc2f094cf
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# ╠═5a4b673b-babb-4e11-a292-d71087fa32bc
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# ╠═11fb3a28-edf3-46ff-8c4a-5286793b6e43
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# ╠═a6c72acc-39fc-4dfc-8126-64c6b35145d1
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# ╠═79a9ab94-06a8-4613-8f60-358e08f0f32e
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# ╠═d79a6752-77ba-496f-96c3-d9904db0a46b
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# ╠═026321df-6991-4b59-aaba-c467b267a477
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# ╠═3955b9d6-7514-4712-ba22-929afda3c77c
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# ╠═a7bacb81-0f19-4d2d-9588-61e912689001
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# ╠═c3d943b4-809d-4a96-a99d-be7653ba2c8b
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# ╠═c3d943b4-809d-4a96-a99d-be7653ba2c8b
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# ╠═01ba1742-d26e-4271-ab62-0bd9ce5e291d
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# ╠═ad4d24a8-f601-4522-a3eb-c01f6fd68aec
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# ╠═2d0de5db-5558-41e0-96d5-a3317d151aff
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# ╠═8924673f-e99c-44b3-be6d-2abf0b2f5e23
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# ╠═8924673f-e99c-44b3-be6d-2abf0b2f5e23
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# ╠═3f7ae2df-9d4d-46d3-b12e-22107a560b66
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# ╠═3f7ae2df-9d4d-46d3-b12e-22107a560b66
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# ╠═fbc06121-d53a-4a64-9497-63d7f3583fbb
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# ╠═fbc06121-d53a-4a64-9497-63d7f3583fbb
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