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Connor
2022-02-19 12:30:54 -07:00
parent 5d5c79c909
commit 329a2990c5
16 changed files with 532 additions and 273 deletions
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30
julia/test/missions/nlp_2_phase
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@@ -7,23 +7,23 @@ Spacecraft: bepi
num_thrusters: 2
duty_cycle: 0.9
Launch Mass: 3600.0 kg
Launch Date: 2021-10-31T23:59:59.769
Launch V∞: [1.0462564431708832, -2.520754077506101, -2.301043507881933] km/s
Launch Date: 2021-10-31T22:00:16.400
Launch V∞: [1.0097399011270518, -2.6447886914618515, -2.5394649406128433] km/s
Phase 1:
Planet: Venus
V∞_in: [0.4205842845952983, -3.5241183574614556, 4.879873784266574] km/s
V∞_out: [2.657685712690303, -4.920354075306563, 2.266369032728228] km/s
time of flight: 1.2614399691127092e7 seconds
arrival date: 2022-03-26T23:59:58.769
thrust profile: [0.08791530712557315 -0.009101317973001748 0.010254083007822207; 0.07287521745776969 -0.011381949725375708 0.051332448819202944; 0.04543116258472458 -0.01531732267940295 0.08273458014460809; 0.011034188560216448 -0.020310595889307323 0.10100599446320643; -0.009607377273254756 -0.02382633371411493 0.1081982710061048; -0.028510355701058584 -0.030611944159923403 0.11101434996597628; -0.039048295910837236 -0.03820244320795566 0.11279184708362161; -0.048252651406879885 -0.04651039104792323 0.11301481830933677; -0.05288674350674192 -0.0561882917884983 0.11293454239992265; -0.05458628096513579 -0.06643801004024381 0.11223764822140121; -0.053564283975236535 -0.07751051107973227 0.11061646758637526; -0.049500823222769094 -0.0891415249668692 0.10769319474620971; -0.04185476746663511 -0.10066361474827486 0.10355236756997019; -0.03087924291992901 -0.1112479139000727 0.09781871133696314; -0.015564164113106642 -0.11996802006040436 0.09064682025194883; 0.001781758545597473 -0.12613079909578606 0.0809801955196938; 0.021345925406049154 -0.12876486287710442 0.06930029766487243; 0.041502826765638504 -0.12763804654948588 0.054677487677216745; 0.06024411885991524 -0.12236183464053872 0.038231302757203295; 0.07560839256024353 -0.114157581119008 0.018886579096999003] %
V∞_in: [0.6971321781569763, -3.000415336232889, 5.257930893162622] km/s
V∞_out: [3.155471614002537, -4.846243818499916, 1.9261368837603878] km/s
time of flight: 1.261440000905646e7 seconds
arrival date: 2022-03-26T22:00:16.400
thrust profile: [0.034282174989117516 0.030630284530489906 0.0516767016545959; 0.04055472535721235 0.027376197088858283 0.04809039664320572; 0.043660143604191994 0.03047637966598728 0.04358760046457853; 0.04125099543115894 0.03016179866323979 0.04499932191472562; 0.04495441021193453 0.03348083036100891 0.03861183062100992; 0.04710965203705168 0.02635602095857307 0.04054560175736578; 0.05033947480940243 0.03062684297509654 0.032922298467773295; 0.04663650635412875 0.030369216537824293 0.03703971691255565; 0.048565701285880614 0.029118981813448557 0.034508738912923845; 0.05056448644255328 0.028722504694661054 0.031034420379757226; 0.04932798248085456 0.03007397062288681 0.030824783232637425; 0.047996060872376366 0.028952951818463326 0.032857369566278626; 0.04951821298908887 0.028758116977346378 0.027958339954661; 0.0489313400699588 0.03046347487498191 0.027859841906091212; 0.04520420340375004 0.031670198439770064 0.030514442243397236; 0.04566034232248259 0.034381957552538395 0.024900845759794794; 0.04082535412813151 0.03357236769501879 0.03170011587741194; 0.04621217362755022 0.03182636410505487 0.02410773528455805; 0.045645717216652795 0.032921517920520164 0.02079135127615303; 0.042597542211632096 0.03558968396172082 0.021282994074205266; 0.03731044485129105 0.03994289623933655 0.02130495307758324; 0.04247833588674327 0.03457796735712127 0.01899569141913135; 0.04312850336659755 0.03399248745544899 0.013149159955936978; 0.03754604612989521 0.03763011819702751 0.018318693954420588; 0.03535094668642273 0.036858320028499134 0.02199684830247042; 0.028891076662331875 0.04324155785176078 0.014413619206886816; 0.03267849036426984 0.0401634806637448 0.011840587979407397; 0.024706839495172658 0.043042163807245896 0.01826522977160073; 0.028601237657836467 0.041588848578667854 0.014411946517623132; 0.028228090581187873 0.04015749743865513 0.01508529741887872; 0.024783781293558266 0.04189396738290361 0.014616887877185162; 0.024764235231400287 0.0412235929856152 0.014206631004299218; 0.022700981741250053 0.04285522888573239 0.008652897464076466; 0.023149708367887163 0.04204784290805528 0.011482287191821549; 0.030060665695868752 0.03682561335933804 0.01406740384301527; 0.020327198179371554 0.03967929127546447 0.01907556971774192; 0.01948576963473395 0.04150171458022886 0.01440277138047399; 0.014609183554173198 0.04193091541988154 0.0190142349738259; 0.017338241200120032 0.0405327064144073 0.019397828837718817; 0.013519064235294736 0.043194207588669445 0.012618271521276186; 0.01416527483071525 0.042360112796518024 0.018565046588499192; 0.016192504354863486 0.04321790744316709 0.014857969976184007; 0.005926517746692747 0.04385012579593121 0.01848227965737381; 0.007881472501745706 0.045008039792868576 0.01571801630208125; 0.006544092936553959 0.04561895672702495 0.016342515520064185; 0.0018483989093118227 0.046533973409849064 0.014988164886431584; -0.000568247332158013 0.047073416094890685 0.01286929122897256; -0.008004594524198529 0.046599777614930456 0.013010850227684606; -0.00696671229499173 0.048339673337854945 0.010999881717700421; -0.0070218437672999665 0.04911375570173229 0.010996777473604348] %
Phase 2:
Planet: Mars
V∞_in: [3.866657617879469, -3.8561104436565112, -1.1528388074396114] km/s
V∞_out: [-0.04156826938628659, 0.04537147320396694, 0.010962101613372877] km/s
time of flight: 1.3305600070108933e7 seconds
arrival date: 2022-08-27T23:59:58.769
thrust profile: [0.12294683695617006 -0.14210501591303906 -0.015953927996763824; 0.1346036754636979 -0.11703322342276389 -0.02118233265872474; 0.14035562458965456 -0.09253436643679969 -0.026037109750586127; 0.14159974389839877 -0.07034252588185486 -0.02965559917950358; 0.13983758574258884 -0.0508280123903436 -0.03226072974284784; 0.13628355001371623 -0.03381714643542805 -0.033706183284138075; 0.13174907912062978 -0.01944710462973476 -0.03378159713957984; 0.12690191547644916 -0.006666552590772735 -0.032314321099804075; 0.12190989012800546 0.005350412631176013 -0.02896415432946389; 0.11640547480173373 0.01766009561198736 -0.024295908236754368; 0.11004779022898785 0.029624240108957346 -0.018629744776725948; 0.10255142565747595 0.041391197147168296 -0.011260773047897207; 0.09257939116538691 0.054055648527399226 -0.0018819573006649628; 0.07862129598678515 0.06762185940978795 0.006827208192964654; 0.06184044671572194 0.07873199678299247 0.015671300335402687; 0.04256729407158805 0.08711502955932304 0.023547740065060118; 0.022644089962366266 0.0922573542104121 0.029300773045221138; 0.0012772594401787602 0.09453861142625342 0.0335188440659034; -0.017213511457067864 0.09403439603239908 0.036105272081528195; -0.03466637624188391 0.0910940423628138 0.03867124120601387] %
V∞_in: [3.934071361708631, -4.0556866988998195, -0.9569218994864468] km/s
V∞_out: [2.835079207012675, -3.038506396757051, -0.8239067509398897] km/s
time of flight: 1.3305600002135515e7 seconds
arrival date: 2022-08-27T22:00:16.400
thrust profile: [0.07875872819429838 -0.07602928888291517 -0.002461076427925589; 0.08368497242841927 -0.06670986115534407 0.001665869512245407; 0.08577981435177857 -0.05793119355590426 0.011165188393882227; 0.08758545440549516 -0.0339816665457332 0.026794441364176573; 0.08293133779344392 -0.02340157704539268 0.034551607127364624; 0.07757395448326561 -0.006354368804274271 0.03802615353405709; 0.0644275187408338 0.00817115132820835 0.04477293215146323; 0.052643603336670175 0.021208603088669686 0.04641877730052604; 0.0422696791291819 0.03249686419539815 0.04293455453504036; 0.0299947244754212 0.0342146829206795 0.04610828643246764; 0.028375921792895057 0.031929570942726804 0.04880758017415033; 0.021457075341902082 0.03512409953676916 0.047848639128187716; 0.014050820576587325 0.03598753239044044 0.048208234639668036; 0.01239374458074181 0.03519088938079009 0.04991578465780201; 0.005554038390401058 0.03590306275800209 0.04943448284625346; 0.004594710645977571 0.03473960951290201 0.05085953544892566; 0.004962419167461687 0.03677569856463667 0.05029354676804025; 0.0007318114245317572 0.03710676170960615 0.050422609329575686; -0.0008906817624837742 0.03770220933797602 0.05041455076147805; -0.006778334873847526 0.03779829345387088 0.04962125740173904; -0.007046493202932243 0.03568043355312452 0.051960594399799505; -0.008049628911291552 0.03913802154188755 0.05028104660474625; -0.010537903266724359 0.03672325453597655 0.051884804336631986; -0.00818351261490794 0.038741730202093635 0.05210658416215128; -0.010666656787731375 0.03849972475725258 0.05243476797310733; -0.012555727410020852 0.0382137309957785 0.05268364578100002; -0.009820005328087349 0.03916769798664862 0.05359353372069135; -0.012387176669361927 0.03970296584000698 0.05331339060382668; -0.01244834483921497 0.041886262658702045 0.05253893772334037; -0.013444072160084112 0.04262744032016184 0.05253898626998434; -0.012523862311046558 0.04142301768047668 0.05454027471095643; -0.012895225834978194 0.042511978835118515 0.0544877324498131; -0.012679086383971097 0.04485961538708221 0.05361843203762159; -0.01233563279407355 0.04412582031595734 0.05489553351056654; -0.011291838361870397 0.04737557615034447 0.05363956736166156; -0.011230502857283789 0.04704594850205801 0.05467457973688944; -0.008797763456055051 0.04928744387907065 0.05415511568853677; -0.008048802844087589 0.05075747730843418 0.0538825677403911; -0.0056970113123549744 0.05224183281724393 0.05369505177198884; -0.006070834938122434 0.052936925948144475 0.05379731537648658; -0.0024653651357053295 0.05567255160163994 0.05213940324181525; -0.000733453786943943 0.057067189219935754 0.05145199179114529; 0.0012456777227569263 0.059943358064031824 0.04907287600209174; 0.004373513720293685 0.06169575905345249 0.047206183474067936; 0.009873790970193171 0.06486640320654036 0.04255101782330187; 0.013319573203495716 0.06692522008245975 0.03887179390451873; 0.018201455983236366 0.06835502892414509 0.034298233864195185; 0.023662275014910684 0.06904022589813187 0.029150000528514425; 0.02774195908046571 0.07005784655018363 0.02165291283778826; 0.031997497603024734 0.06946489515884077 0.015502921841459603] %
Mass Used: 121.86921799846004 kg
Launch C3: 12.743654889305812 km²/s²
||V∞_in||: 5.58118860132149 km/s
Mass Used: 61.61570260672124 kg
Launch C3: 14.463364075014354 km²/s²
||V∞_in||: 5.730725224643533 km/s

85
julia/test/nlp_solver.jl
View File

@@ -4,72 +4,37 @@
println("Testing NLP solver")
# Test the optimizer for a one-phase mission
# The lambert's solver said this should be pretty valid
launch_window = DateTime(1992,11,1), DateTime(1992,12,1)
latest_arrival = DateTime(1993,6,1)
leave, arrive = DateTime(1992,11,19), DateTime(1993,4,1)
test_leave = DateTime(1992,11,12)
earth_state = state(Earth, leave)
venus_state = state(Venus, arrive)
v∞_out, v∞_in, tof = Thesis.lamberts(Earth, Venus, leave, arrive)
# We can get the thrust profile and tof pretty wrong and still be ok
phase = Phase(Venus, 1.1v∞_in, v∞_in, 0.9*tof, 0.1*ones(20,3))
guess = Mission_Guess(bepi, 3_600., test_leave, 0.9*v∞_out, [phase])
m = solve_mission(guess, launch_window, latest_arrival, 200., 20., verbose=true)
@test typeof(m) == Mission
# Now we can plot the results to check visually
p = plot(m, title="NLP Test Solution")
savefig(p,"../plots/nlp_test_1_phase.html")
store(m, "missions/nlp_1_phase")
# Now we can look at a slightly more complicated trajectory
flybys = [Earth, Venus, Mars]
# This will be the only test to verify rather than testing different complexities
n = 50
flybys = [Earth, Venus, Mars]#, Jupiter]
launch_window = DateTime(2021,10,1), DateTime(2021,12,1)
latest_arrival = DateTime(2023,1,1)
dates = [DateTime(2021,11,1), DateTime(2022,3,27), DateTime(2022,8,28)]
latest_arrival = DateTime(2028,1,1)
dates = [DateTime(2021,11,1),
DateTime(2022,3,27),
DateTime(2022,8,28)]
# DateTime(2028,3,1)]
phases = Vector{Phase}()
launch_v∞, _, tof1 = Thesis.lamberts(flybys[1], flybys[2], dates[1], dates[2])
for i in 1:length(dates)-2
v∞_out1, v∞_in1, tof1 = Thesis.lamberts(flybys[i], flybys[i+1], dates[i], dates[i+1])
v∞_out2, v∞_in2, tof2 = Thesis.lamberts(flybys[i+1], flybys[i+2], dates[i+1], dates[i+2])
push!(phases, Phase(flybys[i+1], v∞_in1, v∞_out2, tof1, 0.01*ones(20,3)))
v∞_in1, tof1 = Thesis.lamberts(flybys[i], flybys[i+1], dates[i], dates[i+1])[2:3]
v∞_out2 = Thesis.lamberts(flybys[i+1], flybys[i+2], dates[i+1], dates[i+2])[1]
push!(phases, Phase(flybys[i+1], v∞_in1, v∞_out2, tof1, 0.01*ones(50,3)))
end
v∞_out, v∞_in, tof = Thesis.lamberts(flybys[end-1], flybys[end], dates[end-1], dates[end])
push!(phases, Phase(flybys[end], v∞_in, v∞_in, tof, 0.01*ones(20,3)))
v∞_in, tof = Thesis.lamberts(flybys[end-1], flybys[end], dates[end-1], dates[end])[2:3]
push!(phases, Phase(flybys[end], v∞_in, v∞_in, tof, 0.01*ones(50,3)))
guess = Mission_Guess(bepi, 3_600., dates[1], launch_v∞, phases)
m = solve_mission(guess, launch_window, latest_arrival, 200., 20., verbose=true)
m = solve_mission(guess,
launch_window,
latest_arrival,
200.,
20.,
verbose=true,
print_level=4)
@test typeof(m) == Mission
p = plot(m, title="NLP Test Solution (2 Phases)")
savefig(p,"../plots/nlp_test_2_phase.html")
store(m, "missions/nlp_2_phase")
# Here is the final, most complicated, trajectory to test
# Ignoring for now as the initial guess makes the test take too long to converge with mbh settings
# flybys = [Earth, Venus, Earth, Mars, Earth, Jupiter]
# launch_window = DateTime(2023,1,1), DateTime(2024,1,1)
# latest_arrival = DateTime(2031,1,1)
# dates = [DateTime(2023,5,23),
# DateTime(2023,10,21),
# DateTime(2024,8,24),
# DateTime(2025,2,13),
# DateTime(2026,11,22),
# DateTime(2032,1,1)]
# phases = Vector{Phase}()
# launch_v∞, _, tof1 = Thesis.lamberts(flybys[1], flybys[2], dates[1], dates[2])
# for i in 1:length(dates)-2
# v∞_out1, v∞_in1, tof1 = Thesis.lamberts(flybys[i], flybys[i+1], dates[i], dates[i+1])
# v∞_out2, v∞_in2, tof2 = Thesis.lamberts(flybys[i+1], flybys[i+2], dates[i+1], dates[i+2])
# push!(phases, Phase(flybys[i+1], 1.02v∞_in1, 0.98v∞_out2, 1.02tof1, 0.02*ones(20,3)))
# end
# v∞_out, v∞_in, tof = Thesis.lamberts(flybys[end-1], flybys[end], dates[end-1], dates[end])
# push!(phases, Phase(flybys[end], v∞_in, v∞_in, tof, 0.01*ones(20,3)))
# guess = Mission_Guess(bepi, 3_600., dates[1], launch_v∞, phases)
# m = solve_mission(guess, launch_window, latest_arrival, 200., 20., verbose=true)
# @test typeof(m) == Mission
# p = plot(m, title="NLP Test Solution (5 Phases)")
# savefig(p,"../plots/nlp_test_5_phase.html")
# store(m, "missions/nlp_5_phase")
if typeof(m) == Mission
p = plot(m, title="NLP Test Solution (2 Phases)")
savefig(p,"../plots/nlp_test_2_phase.html")
store(m, "missions/nlp_2_phase")
end
end

26
julia/test/propagator.jl
View File

@@ -1,21 +1,27 @@
@testset "Propagator" begin
println("Testing propagator")
using PlotlyJS: savefig
using Thesis: prop_one
println("Testing Propagator")
# Set up
start_mass = 10_000.
start = gen_orbit(rand(.5year : hour : 2year), start_mass)
stepsize = rand(hour : second : 6hour)
time = rand(0.2year : second : 0.5year)
n = 1_000
# Test that Laguerre-Conway is the default propagator for spacecrafts
state = prop_one([0., 0., 0.], start, no_thrust, stepsize)
@test laguerre_conway(start, stepsize) ≈ state[1:6]
@test state[7] == start_mass
# Test that Propagation works
states = prop(zeros(n,3), start, no_thrust, time)
@test states[1,:] != states[end,:]
# Test that mass is reduced properly
state = prop_one([1., 0., 0.], start, bepi, stepsize)
@test state[7] == start_mass - mfr(bepi)*stepsize
states = prop(ones(n,3)/√3, start, bepi, time)
@test states[end,7] ≈ start_mass - mfr(bepi)*time
# Test that the propagator works backwards
backwards = prop(ones(n,3)/√3, states[end,:], bepi, -time)
p = plot([states, backwards])
savefig(p,"../plots/prop_back.html")
@test backwards[end,:] ≈ start
end

12
julia/test/runtests.jl
View File

@@ -3,7 +3,7 @@ using Random
using LinearAlgebra
using SPICE
using Thesis
using Dates: DateTime, Millisecond, Dates, Second, format, datetime2unix, unix2datetime
using Dates: DateTime, Millisecond, Dates, Second, format, datetime2julian, julian2datetime
try
furnsh("../../spice_files/naif0012.tls")
@@ -14,10 +14,10 @@ catch
end
@testset "All Tests" begin
include("plotting.jl")
include("laguerre-conway.jl")
# include("plotting.jl")
# include("laguerre-conway.jl")
include("propagator.jl")
include("nlp_solver.jl")
include("mbh.jl")
include("genetic_algorithm.jl")
# include("nlp_solver.jl")
# include("mbh.jl")
# include("genetic_algorithm.jl")
end