Currently working on refactor, much work to do
This commit is contained in:
Connor
@@ -1,50 +0,0 @@
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@testset "Find Closest" begin
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println("Testing NLP solver")
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using NLsolve, PlotlyJS
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# Initial Setup
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sc = Sc("test")
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fresh_sc = copy(sc)
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a = rand(25000:1.:40000)
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e = rand(0.01:0.01:0.05)
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i = rand(0.01:0.01:π/6)
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T = 2π*√(a^3/μs["Earth"])
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prop_time = 5T
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n = 200
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# A simple orbit raising
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start_mass = 10_000.
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start = [ oe_to_xyz([ a, e, i, 0., 0., 0. ], μs["Earth"]); start_mass ]
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Tx, Ty, Tz = conv_T(repeat([0.9], n), repeat([0.], n), repeat([0.], n),
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start,
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sc,
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prop_time,
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μs["Earth"])
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final = prop(hcat(Tx, Ty, Tz), start, copy(sc), μs["Earth"], prop_time)[2]
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new_T = 2π*√(xyz_to_oe(final, μs["Earth"])[1]^3/μs["Earth"])
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# This should be close enough to converge
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Tx, Ty, Tz = conv_T(repeat([0.89], n), repeat([0.], n), repeat([0.], n),
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start,
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sc,
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prop_time,
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μs["Earth"])
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result = nlp_solve(start, final, sc, μs["Earth"], 0.0, prop_time, hcat(Tx, Ty, Tz))
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# Test and plot
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@test result.converged
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path1 = prop(zeros((100,3)), start, sc, μs["Earth"], T)[1]
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path2, calc_final = prop(result.zero, start, sc, μs["Earth"], prop_time)
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path3 = prop(zeros((100,3)), calc_final, sc, μs["Earth"], new_T)[1]
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path4 = prop(zeros((100,3)), final, fresh_sc, μs["Earth"], new_T)[1]
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savefig(plot_orbits([path1, path2, path3, path4],
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labels=["initial", "transit", "after transit", "final"],
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colors=["#FFFFFF","#FF4444","#44FF44","#4444FF"]),
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"../plots/find_closest_test.html")
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if result.converged
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@test norm(calc_final[1:6] - final[1:6]) < 1e-4
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end
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end
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@@ -5,26 +5,29 @@
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using Thesis: laguerre_conway
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# Test that the propagator produces good periodic orbits (forwards and backwards)
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for T in rand(3600*1.5:3600*4, (5))
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start = oe_to_xyz([ (μs["Earth"]*(T/(2π))^2)^(1/3), rand(0.01:0.01:0.5), rand(0.01:0.01:0.45π), 0., 0., 1. ], μs["Earth"])
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μ = Earth.μ
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for T in rand(3600*1.5:3600*4, 5)
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e = rand(0.0:0.01:0.75)
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i = rand(0.0:0.01:0.499π)
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start = [ oe_to_xyz([ (μ*(T/(2π))^2)^(1/3), e, i, 0., 0., 1. ], μ); 12_000. ]
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orbit = start
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for _ in 1:5
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i = 0.
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while i < T
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orbit = laguerre_conway(orbit, μs["Earth"], 1.)
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orbit = laguerre_conway(orbit, 1., Earth)
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i += 1
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end
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@test i ≈ T
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@test norm(orbit - start) < 1e-2
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@test norm(orbit[1:6] - start[1:6]) < 1e-2
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end
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for _ in 1:5
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i = 0.
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while i > -T
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orbit = laguerre_conway(orbit, μs["Earth"], -1.)
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orbit = laguerre_conway(orbit, -1., Earth)
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i -= 1
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end
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@test i ≈ -T
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@test norm(orbit - start) < 1e-2
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@test norm(orbit[1:6] - start[1:6]) < 1e-2
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end
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end
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39
julia/test/inner_loop/phase.jl
Normal file
39
julia/test/inner_loop/phase.jl
Normal file
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@testset "Phase" begin
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println("Testing NLP solver")
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using NLsolve, PlotlyJS
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# Initial Setup
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T = rand( 2hour : second : 12hour)
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revs = 5
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n = 10revs
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start_mass = 12_000.
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# A simple orbit raising
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start = gen_orbit(T, start_mass, Earth)
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thrust = spiral(0.9, n, start, test_sc, revs*T, Earth)
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final = prop(thrust, start, test_sc, revs*T, Earth)[2]
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new_T = 2π * √( xyz_to_oe(final, Earth.μ)[1]^3 / Earth.μ )
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# This should be close enough to converge
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thrust_guess = spiral(0.88, n, start, test_sc, revs*T, Earth)
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result = solve_phase(start, final, test_sc, revs*T, thrust_guess, Earth)
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calc_path, calc_final = prop(result.zero, start, test_sc, revs*T, Earth)
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# Test
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@test converged(result)
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@test norm(calc_final[1:6] - final[1:6]) < 1e-5
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# Plot
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paths = Pathlist()
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push!(paths, prop(start, T, Earth),
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calc_path,
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prop(calc_final, T, Earth),
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prop(final, T, Earth) )
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fig = plot_orbits(paths, Earth,
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labels=["init", "transit", "post-transit", "final"],
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colors=["#FFF","#F44","#4F4","#44F"])
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savefig(fig, "../plots/nlp_test.html")
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end
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@@ -6,26 +6,19 @@
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# Set up
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start_mass = 10_000.
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start = [oe_to_xyz([ (μs["Earth"]*(rand(3600*1.5:0.01:3600*4)/(2π))^2)^(1/3),
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rand(0.01:0.01:0.5),
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rand(0.01:0.01:0.45π),
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0.,
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0.,
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1. ], μs["Earth"]); start_mass]
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stepsize = rand(100.0:0.01:500.0)
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start = gen_orbit(rand(.5year : hour : 2year), start_mass)
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stepsize = rand(hour : second : 6hour)
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# Test that Laguerre-Conway is the default propagator for spacecrafts
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craft = Sc("no_thrust")
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state = prop_one([0., 0., 0.], start, craft, μs["Earth"], stepsize)
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@test laguerre_conway(start, μs["Earth"], stepsize) ≈ state[1:6]
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state = prop_one([0., 0., 0.], start, no_thrust, stepsize)
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@test laguerre_conway(start, stepsize) ≈ state[1:6]
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@test state[7] == start_mass
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# Test that mass is reduced properly
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craft = Sc("test")
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state = prop_one([1., 0., 0.], start, craft, μs["Earth"], stepsize)
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@test state[7] == start_mass - craft.mass_flow_rate*stepsize
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state = prop_one([1., 0., 0.], start, bepi, stepsize)
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@test state[7] == start_mass - bepi.mass_flow_rate*stepsize
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# Test that a bad ΔV throws an error
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@test_throws ErrorException prop_one([1.5, 0., 0.], start, craft, μs["Earth"], stepsize)
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@test_throws Thesis.PropOne_Error prop_one([1.5, 0., 0.], start, bepi, stepsize)
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end
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@@ -4,21 +4,32 @@
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using PlotlyJS
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# First some setup
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sc = Sc("test")
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T = rand(3600*2:0.01:3600*4)
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start = [oe_to_xyz([ (μs["Earth"]*(T/(2π))^2)^(1/3),
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0.1,
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π/4,
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0.,
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0.,
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1. ], μs["Earth"]); 10_000.]
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# Plot an earth plot
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T = rand(2hour : 1 : 4hour)
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revs = 30
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n = revs*100
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ΔVs = repeat([0.9, 0., 0.]', outer=(n,1))
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path = prop(ΔVs, start, copy(sc), μs["Earth"], revs*T)[1]
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p = plot_orbits([path])
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savefig(p,"../plots/plot_test.html")
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start = gen_orbit(T, 12_000., Earth)
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thrust = spiral(0.9, n, start, test_sc, revs*T, Earth)
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path = prop(thrust, start, test_sc, revs*T, Earth)[1]
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p = plot_orbits([path], Earth)
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savefig(p,"../plots/plot_test_earth.html")
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@test typeof(p) == PlotlyJS.SyncPlot
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# Now change a little bit and plot around the Sun
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# This also checks that the spacecraft are configured right:
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# They really shouldn't run out of fuel in 4 years
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T = rand(year : hour : 4year)
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tof = 4year
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start = gen_orbit(T, 12_000.)
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thrust = spiral(0.9, n, start, bepi, tof)
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sun_paths = Vector{Vector{Vector{Float64}}}()
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push!(sun_paths, prop(zeros(100,3), start, bepi, tof)[1])
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push!(sun_paths, prop(thrust, start, bepi, tof)[1])
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p = plot_orbits(sun_paths)
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savefig(p,"../plots/plot_test_sun.html")
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@test typeof(p) == PlotlyJS.SyncPlot
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end
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@@ -4,24 +4,13 @@ using LinearAlgebra
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using SPICE
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using Thesis
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try
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furnsh("../../SPICE/naif0012.tls")
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furnsh("../../SPICE/de430.bsp")
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catch
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furnsh("SPICE/naif0012.tls")
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furnsh("SPICE/de430.bsp")
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end
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# Tests
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@testset "All Tests" begin
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include("spacecraft.jl")
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include("plotting.jl")
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include("inner_loop/laguerre-conway.jl")
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include("inner_loop/propagator.jl")
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include("inner_loop/find_closest.jl")
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include("inner_loop/monotonic_basin_hopping.jl")
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include("inner_loop/inner_loop.jl")
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include("outer_loop.jl")
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include("inner_loop/phase.jl")
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# include("inner_loop/monotonic_basin_hopping.jl")
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end
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print()
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@@ -1,28 +0,0 @@
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@testset "Spacecraft Construction" begin
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println("Testing spacecraft")
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# Test that the standard spacecraft can be created
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craft = Sc("test")
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@test craft.dry_mass == 9000.
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@test craft.mass_flow_rate == craft.max_thrust/(0.00981*2000)
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@test craft.max_thrust == 0.00025
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@test craft.num_thrusters == 50
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@test craft.duty_cycle == 0.9
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craft = Sc("no_thrust")
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@test craft.dry_mass == 9000.
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@test craft.mass_flow_rate == 0.01
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@test craft.max_thrust == 0.
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@test craft.num_thrusters == 0
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@test craft.duty_cycle == 0.
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# Test that the standard spacecraft can be copied
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new_craft = copy(craft)
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@test new_craft.dry_mass == craft.dry_mass
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@test new_craft.mass_flow_rate == craft.mass_flow_rate
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@test new_craft.max_thrust == craft.max_thrust
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@test new_craft.num_thrusters == craft.num_thrusters
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@test new_craft.duty_cycle == craft.duty_cycle
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end
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