Manages the multi-phase rocket flight simulation with event-driven transitions.

Functions¶

simulate_ascent¶

Main simulation entry point.

def simulate_ascent(config: AscentConfig) -> Trajectory:

Phases:

1. Vertical Ascent → Event: Pitchover altitude
2. Gravity Turn → Event: Stage 1 burnout
3. Coast → Fixed duration
4. Stage 2 Burn → Events: Time limit, fuel depletion

Returns: Complete trajectory with all phase data concatenated.

simulate_ascent_final¶

Simulation for optimization (returns only final state).

def simulate_ascent_final(config: AscentConfig) -> FinalState:

More efficient when only the terminal state is needed.

Event Functions¶

def _cond_ground(t, y, args, **kwargs):
    """Ground impact detection."""
    return y[_R] - args["earth"].r_e

def _cond_pitch_over(t, y, args, **kwargs):
    """Pitchover altitude reached."""
    return y[_R] - (args["earth"].r_e + args["h_pitch"])

def _cond_stage1_burnout(t, y, args, **kwargs):
    """Stage 1 propellant exhausted."""
    return y[_M] - args["m1_end"]

def _cond_fuel_depletion(t, y, args, **kwargs):
    """All propellant exhausted."""
    return y[_M] - args["m_min"]

ODE Solver Configuration¶