engine.pipeline.flight_altitude_optimizer Namespace Reference

Classes
class	BurnTimeEval
class	AltitudeOptimizeResult

Functions
float	_integrate (np.ndarray times, np.ndarray values)
Tuple[np.ndarray, np.ndarray, np.ndarray, np.ndarray]	truncate_time_series (np.ndarray times, np.ndarray thrust, np.ndarray mdot_O, np.ndarray mdot_F, float burn_time_s)
Tuple[float, float, float]	required_propellant_at_burn_time (np.ndarray times, np.ndarray thrust, np.ndarray mdot_O, np.ndarray mdot_F, float burn_time_s)
AltitudeOptimizeResult	optimize_minimum_fuel_burn_time (*, np.ndarray times, np.ndarray thrust, np.ndarray mdot_O, np.ndarray mdot_F, float target_apogee_m, float apogee_tolerance_m, Callable[[float], BurnTimeEval] simulate_at_burn_time, Optional[float] min_burn_time_s=None, Optional[float] max_burn_time_s=None, float time_resolution_s=0.05, int max_iterations=24)

Detailed Description

Find minimum-fuel burn time to reach a target apogee for a fixed time-series curve.

For each candidate burn time T we truncate the thrust/mdot curve, load exactly the
propellant required to complete that burn (∫mdot dt), and run flight simulation.
The optimal burn time is the shortest T whose apogee meets the altitude target —
which minimizes fuel mass because fuel_required(T) increases monotonically with T.

Function Documentation

_integrate()

float engine.pipeline.flight_altitude_optimizer._integrate ( np.ndarray times, np.ndarray values )

protected

Definition at line 43 of file flight_altitude_optimizer.py.

Referenced by required_propellant_at_burn_time().

optimize_minimum_fuel_burn_time()

AltitudeOptimizeResult engine.pipeline.flight_altitude_optimizer.optimize_minimum_fuel_burn_time	(	*	,
		np.ndarray	times,
		np.ndarray	thrust,
		np.ndarray	mdot_O,
		np.ndarray	mdot_F,
		float	target_apogee_m,
		float	apogee_tolerance_m,
		Callable[[float], BurnTimeEval]	simulate_at_burn_time,
		Optional[float]	min_burn_time_s = None,
		Optional[float]	max_burn_time_s = None,
		float	time_resolution_s = 0.05,
		int	max_iterations = 24 )

Binary-search the shortest burn time that reaches target_apogee_m.

Definition at line 105 of file flight_altitude_optimizer.py.

References max, min, and required_propellant_at_burn_time().

required_propellant_at_burn_time()

Tuple[float, float, float] engine.pipeline.flight_altitude_optimizer.required_propellant_at_burn_time	(	np.ndarray	times,
		np.ndarray	thrust,
		np.ndarray	mdot_O,
		np.ndarray	mdot_F,
		float	burn_time_s )

Return (lox_kg, fuel_kg, total_impulse_Ns) for burn truncated to burn_time_s.

Definition at line 88 of file flight_altitude_optimizer.py.

References _integrate(), and truncate_time_series().

Referenced by optimize_minimum_fuel_burn_time().

truncate_time_series()

Tuple[np.ndarray, np.ndarray, np.ndarray, np.ndarray] engine.pipeline.flight_altitude_optimizer.truncate_time_series	(	np.ndarray	times,
		np.ndarray	thrust,
		np.ndarray	mdot_O,
		np.ndarray	mdot_F,
		float	burn_time_s )

Return curve arrays truncated to burn_time_s (interpolated endpoint).

Definition at line 51 of file flight_altitude_optimizer.py.

Referenced by required_propellant_at_burn_time().