@testset "Inner Loop" begin

  println("Testing Inner Loop")

  using Dates, SPICE, PlotlyJS

  sc = Sc("test")

  launch_date = DateTime(2016,3,28)
  launch_j2000 = utc2et(Dates.format(launch_date,"yyyy-mm-ddTHH:MM:SS"))
  leg1_tof = 3600*24*30*10.75
  leg2_tof = 3600*24*365*5.5
  v∞s = [ [0.34251772594197877, -2.7344726708862477, -1.1854707164631975],
          [-1.1, -3., -2.6],
          [3.5, 3.5, √(5^2 - 2*3.5^2)],
          [0.3, 1., 0.] ]
  p1 = "Mars"
  p2 = "Saturn"
  start_mass = 10_000.

  phase1 = Phase("Earth", p1, leg1_tof, v∞s[1], v∞s[2])
  phase2 = Phase(p1, p2, leg2_tof, v∞s[3], v∞s[4])

  # For finding the best trajectories
  earth_state = [spkssb(Thesis.ids["Earth"], launch_j2000, "J2000"); start_mass]
  p1_state = [spkssb(Thesis.ids[p1], launch_j2000+leg1_tof, "J2000"); start_mass]
  p2_state = [spkssb(Thesis.ids[p2], launch_j2000+leg1_tof+leg2_tof, "J2000"); start_mass]
  earth = prop(zeros(100,3), earth_state, sc, μs["Sun"], 3600*24*365.)[1]
  p1_path = prop(zeros(100,3), p1_state, sc, μs["Sun"], 3600*24*365*2.)[1]
  p2_path = prop(zeros(100,3), p2_state, sc, μs["Sun"], 3600*24*365*8.)[1]
  leg1, leg1_final = prop(zeros(400,3),
                          earth_state+[zeros(3);v∞s[1];start_mass],
                          copy(sc),
                          μs["Sun"],
                          leg1_tof)
  leg2, leg2_final = prop(zeros(400,3),
                          p1_state+[zeros(3);v∞s[3];start_mass],
                          copy(sc),
                          μs["Sun"],
                          leg2_tof)
  savefig(plot_orbits(  [earth, p1_path, p2_path, leg1, leg2],
                primary="Sun",
                labels=["Earth", p1, p2, "Leg 1", "Leg 2"],
                title="Inner Loop without thrusting",
                colors=["#0000FF", "#FF0000", "#FFFF00", "#FF00FF", "#00FFFF"]  ),
         "../plots/inner_loop_before.html")

  # The first leg should be valid
  fresh_sc = copy(sc)
  mass, thrusts = inner_loop( launch_date,
                              sc,
                              start_mass,
                              [phase1],
                              verbose=true,
                              mbh_specs=(25,50) )
  @test sc.mass > sc.dry_mass
  path, final = prop(thrusts[1], earth_state+[zeros(3);v∞s[1]], fresh_sc, μs["Sun"], leg1_tof)
  @test final ≈ p1_state + [zeros(3); v∞s[2]]
  savefig(plot_orbits(  [earth, p1_path, path],
                primary="Sun",
                labels=["Earth", p1, "Leg 1"],
                title="Inner Loop with thrusting",
                colors=["#0000FF", "#FF0000", "#FF00FF"]  ),
          "../plots/inner_loop_after.html")

  # The second one was too hard to figure out on my own, so I'm letting it fail
  @test_throws ErrorException inner_loop( launch_date,
                                          sc,
                                          start_mass,
                                          [phase1, phase2],
                                          verbose=true,
                                          mbh_specs=(10,10) )

end