Built the population member gen function
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Connor
@@ -5,76 +5,78 @@
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println("Testing Monotonic Basin Hopper")
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# Initial Setup
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sc = Sc("test")
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a = rand(50_000:1.:100_000)
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e = rand(0.01:0.01:0.5)
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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 = 0.5T
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n = 20
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start_mass = 10_000.
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# sc = Sc("test")
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# a = rand(50_000:1.:100_000)
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# e = rand(0.01:0.01:0.5)
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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 = 0.5T
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# n = 20
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# start_mass = 10_000.
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# A simple orbit raising
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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([0.8], 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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nominal_path, final = prop(hcat(Tx, Ty, Tz), start, sc, μs["Earth"], prop_time)
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new_T = 2π*√(xyz_to_oe(final, μs["Earth"])[1]^3/μs["Earth"])
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# # A simple orbit raising
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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([0.8], 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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# nominal_path, final = prop(hcat(Tx, Ty, Tz), start, sc, μs["Earth"], prop_time)
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# new_T = 2π*√(xyz_to_oe(final, μs["Earth"])[1]^3/μs["Earth"])
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# Find the best solution
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best, archive = mbh(start,
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final,
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sc,
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μs["Earth"],
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0.0,
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prop_time,
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n,
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search_patience_lim=25,
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drill_patience_lim=50,
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verbose=true)
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# # Find the best solution
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# best, archive = mbh(start,
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# final,
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# sc,
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# μs["Earth"],
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# 0.0,
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# prop_time,
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# n,
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# search_patience_lim=25,
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# drill_patience_lim=50,
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# verbose=true)
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# Test and plot
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@test best.converged
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transit, calc_final = prop(best.zero, start, sc, μs["Earth"], prop_time)
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initial_path = prop(zeros((100,3)), start, sc, μs["Earth"], T)[1]
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after_transit = prop(zeros((100,3)), calc_final, sc, μs["Earth"], new_T)[1]
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final_path = prop(zeros((100,3)), final, sc, μs["Earth"], new_T)[1]
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savefig(plot_orbits([initial_path, nominal_path, final_path],
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labels=["initial", "nominal transit", "final"],
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colors=["#FF4444","#44FF44","#4444FF"]),
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"../plots/mbh_nominal.html")
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savefig(plot_orbits([initial_path, transit, after_transit, final_path],
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labels=["initial", "transit", "after transit", "final"],
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colors=["#FFFFFF", "#FF4444","#44FF44","#4444FF"]),
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"../plots/mbh_best.html")
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i = 0
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best_mass = calc_final[end]
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nominal_mass = final[end]
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masses = []
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for candidate in archive
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@test candidate.converged
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path2, calc_final = prop(candidate.zero, start, sc, μs["Earth"], prop_time)
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push!(masses, calc_final[end])
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@test norm(calc_final[1:6] - final[1:6]) < 1e-4
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end
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@test best_mass == maximum(masses)
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# # Test and plot
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# @test best.converged
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# transit, calc_final = prop(best.zero, start, sc, μs["Earth"], prop_time)
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# initial_path = prop(zeros((100,3)), start, sc, μs["Earth"], T)[1]
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# after_transit = prop(zeros((100,3)), calc_final, sc, μs["Earth"], new_T)[1]
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# final_path = prop(zeros((100,3)), final, sc, μs["Earth"], new_T)[1]
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# savefig(plot_orbits([initial_path, nominal_path, final_path],
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# labels=["initial", "nominal transit", "final"],
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# colors=["#FF4444","#44FF44","#4444FF"]),
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# "../plots/mbh_nominal.html")
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# savefig(plot_orbits([initial_path, transit, after_transit, final_path],
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# labels=["initial", "transit", "after transit", "final"],
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# colors=["#FFFFFF", "#FF4444","#44FF44","#4444FF"]),
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# "../plots/mbh_best.html")
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# i = 0
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# best_mass = calc_final[end]
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# nominal_mass = final[end]
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# masses = []
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# for candidate in archive
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# @test candidate.converged
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# path2, calc_final = prop(candidate.zero, start, sc, μs["Earth"], prop_time)
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# push!(masses, calc_final[end])
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# @test norm(calc_final[1:6] - final[1:6]) < 1e-4
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# end
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# @test best_mass == maximum(masses)
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# This won't always work since the test is reduced in fidelity,
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# but hopefully will usually work:
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@test (start_mass - best_mass) < 1.1 * (start_mass - nominal_mass)
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# # This won't always work since the test is reduced in fidelity,
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# # but hopefully will usually work:
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# @test (start_mass - best_mass) < 1.1 * (start_mass - nominal_mass)
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# Now let's test a sun case. This should be pretty close to begin with
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start_mass = 10_000.
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launch_date = DateTime(2016,3,28)
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launch_j2000 = utc2et(Dates.format(launch_date,"yyyy-mm-ddTHH:MM:SS"))
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earth_start = [spkssb(ids["Earth"], launch_j2000, "J2000"); 1e5]
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earth_start = [spkssb(ids["Earth"], launch_j2000, "ECLIPJ2000"); start_mass]
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earth_speed = earth_start[4:6]
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v∞ = 3.0*earth_speed/norm(earth_speed)
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start = earth_start + [zeros(3); v∞; 0.0]
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final = [1.62914115303947e8, 1.33709639408102e8, 5.690490452749867e7, -16.298522963602757, 15.193294491415365, 6.154820267250081, 1.0001e8]
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tof = 3600*24*30*10.75
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mars_state = [spkssb(Thesis.ids["Mars"], launch_j2000+tof, "ECLIPJ2000"); start_mass]
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final = mars_state + [ zeros(3); [-1.1, -3., -2.6]; 0.0 ]
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a = xyz_to_oe(final, μs["Sun"])[1]
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T = 2π*√(a^3/μs["Sun"])
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n = 20
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