Functions
	config ()
	_pressure_profiles (config, float duration_s, int n_points=101)
	_run_timeseries (config, float duration_s)
	_run_flight (config, data, float lox_kg, float fuel_kg)
	test_fuel_mass_is_capped_to_tank_and_left_alone_when_it_fits (config)
	test_apogee_increases_with_propellant_when_truncated (config)
	test_excess_propellant_does_not_increase_apogee (config)
	test_longer_burn_time_changes_impulse_and_apogee_with_enough_propellant (config)

Variables
str	CONFIG = Path(__file__).resolve().parents[1] / "configs" / "default.yaml"

Detailed Description

Flight-sim propellant iteration -- regression tests against the shipped default config.

- Tank caps: a fuel tank too small for the requested load is capped by the flight router, a tank
  that fits the load is not, and an explicit design_requirements capacity wins over geometry.
- Apogee rises with propellant while the burn is truncated.
- Excess propellant above the full-burn requirement does not raise apogee.
- A longer burn with enough propellant raises impulse and apogee.

The previous version of this module read a config out of one developer's ~/Downloads folder and
asserted a property of that file's tank, so it skipped on every other machine and failed on his
once the file changed. Everything here is built from configs/default.yaml.

Function Documentation

◆ _pressure_profiles()

test_flight_propellant_iteration._pressure_profiles	(		config,
		float	duration_s,
		int	n_points = 101 )

protected

Exponential blowdown from each tank's configured initial pressure to 70% of it.

Definition at line 40 of file test_flight_propellant_iteration.py.

Referenced by _run_timeseries().

◆ _run_flight()

test_flight_propellant_iteration._run_flight	(		config,
			data,
		float	lox_kg,
		float	fuel_kg )

protected

Definition at line 60 of file test_flight_propellant_iteration.py.

Referenced by test_apogee_increases_with_propellant_when_truncated(), test_excess_propellant_does_not_increase_apogee(), and test_longer_burn_time_changes_impulse_and_apogee_with_enough_propellant().

◆ _run_timeseries()

test_flight_propellant_iteration._run_timeseries	(		config,
		float	duration_s )

protected

Definition at line 51 of file test_flight_propellant_iteration.py.

References _pressure_profiles().

Referenced by test_apogee_increases_with_propellant_when_truncated(), test_excess_propellant_does_not_increase_apogee(), and test_longer_burn_time_changes_impulse_and_apogee_with_enough_propellant().

◆ config()

test_flight_propellant_iteration.config ( void )

Definition at line 28 of file test_flight_propellant_iteration.py.

◆ test_apogee_increases_with_propellant_when_truncated()

test_flight_propellant_iteration.test_apogee_increases_with_propellant_when_truncated ( config )

Definition at line 113 of file test_flight_propellant_iteration.py.

References _run_flight(), _run_timeseries(), and max.

◆ test_excess_propellant_does_not_increase_apogee()

test_flight_propellant_iteration.test_excess_propellant_does_not_increase_apogee ( config )

Definition at line 131 of file test_flight_propellant_iteration.py.

References _run_flight(), and _run_timeseries().

◆ test_fuel_mass_is_capped_to_tank_and_left_alone_when_it_fits()

test_flight_propellant_iteration.test_fuel_mass_is_capped_to_tank_and_left_alone_when_it_fits ( config )

The flight router caps a load the tank cannot hold, matches the shared resolver, does not
touch a load that fits, and honours an explicit design_requirements capacity over geometry.

Definition at line 77 of file test_flight_propellant_iteration.py.