def circularization_phase(body, angle, thrust):
simulation = ThrustSimulation(
body,
thrust / PROPELLANT_SPECIFIC_VELOCITY,
f_gravity +
f_drag +
(lambda b: f_thrust(b, angle, thrust)))
simulation.run(
300, dt=DELTA_T, condition=lambda b: abs(b.radial_speed) < 1)
return simulation
def launch_phase(body, angle, thrust):
simulation = ThrustSimulation(
body,
thrust / PROPELLANT_SPECIFIC_VELOCITY,
f_gravity +
f_drag +
(lambda b: f_thrust(b, angle, thrust)))
simulation.run(
300, dt=DELTA_T, condition=lambda b: b.radius > 1000 + MARS_RADIUS)
return simulation
