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
def phase_2(body, thrust_y, h_3=0):
body.area = pi * 2.25 ** 2
body.c_drag = 2.8
body.r_nose = 16.7
simulation = ThrustSimulation(
body,
abs(thrust_y / c),
f_gravity +
f_drag +
(lambda b: b.position.unit * thrust_y))
r_3 = radius_mars + h_3
simulation.run(1000, small_delta_t, condition=lambda b: b.radius <= r_3)
return simulation
def phase_1(body, thrust_x, h_2=400):
body.area = pi * 2.25 ** 2
body.c_drag = 2.8
body.r_nose = 16.7
simulation = ThrustSimulation(
body,
thrust_x / c,
f_gravity +
f_drag +
(lambda b: - b.direction * thrust_x))
r_2 = radius_mars + h_2
simulation.run(3000, small_delta_t, condition=lambda b: b.radius <= r_2)
if simulation is not None:
body.mass -= simulation.engine_mass
return simulation