Classes
class	EnvironmentConfig
class	FinsConfig
class	RocketConfig
class	TankConfig
class	FlightSimRequest
class	FlightTrajectory
class	TruncationInfo
class	MassCapInfo
class	PropellantDiagnostics
class	FlightSimResponse
class	FlightOptimizeRequest
class	FlightOptimizeResponse

Functions
tuple	_propellant_densities (config)
float	calculate_tank_capacity (float height, float radius, float density, float fill_factor=0.95)
	convert_numpy (obj)
Optional[str]	generate_rocket_diagram (flight_obj)
	extract_flight_series (flight_obj, float elevation=0.0)
	build_flight_config (base_config, FlightSimRequest request)
tuple[dict, dict, float\|None, float\|None, float]	_apply_propellant_mass_caps (dict config_dict, base_config)
float	_integrate_series (np.ndarray times, np.ndarray values)
MassCapInfo	_build_mass_cap_info (str branch, float requested_kg, float effective_kg, float tank_volume_m3, float max_fill_kg, float fill_factor)
PropellantDiagnostics	_compute_propellant_diagnostics (*, np.ndarray times, np.ndarray thrust_array, np.ndarray mdot_O_array, np.ndarray mdot_F_array, float lox_requested, float fuel_requested, float lox_effective, float fuel_effective, Optional[float] lox_tank_max, Optional[float] fuel_tank_max, Optional[TruncationInfo] truncation, dict mass_caps, Optional[float] target_apogee_m, Optional[float] propellant_tank_fill_factor=None)
float	_thrust_reference_pressure (base_config, FlightSimRequest request)
Optional[float]	ceiling_agl_m (design_requirements, float elevation_m)
Optional[dict]	_ceiling_check (flight_config, pressure_curves, float burn_time, float nominal_apogee_agl)
FlightSimResponse	_execute_flight_simulation (base_config, FlightSimRequest request, *, Optional[np.ndarray] time_array=None, Optional[np.ndarray] thrust_array=None, Optional[np.ndarray] mdot_O_array=None, Optional[np.ndarray] mdot_F_array=None, Optional[float] lox_mass_kg=None, Optional[float] fuel_mass_kg=None, bool check_ceiling=True)
	simulate_flight (FlightSimRequest request, UserSession session=Depends(get_session))
FlightSimResponse	_simulate_flight (FlightSimRequest request, config)
	optimize_flight_altitude (FlightOptimizeRequest request, UserSession session=Depends(get_session))
FlightOptimizeResponse	_optimize_flight_altitude (FlightOptimizeRequest request, config)
	check_rocketpy ()

Variables
	router = APIRouter(prefix="/api/flight", tags=["flight"])
float	PSI_TO_PA = 6894.76
float	PA_TO_PSI = 1.0 / PSI_TO_PA
float	LOX_DENSITY_FALLBACK = 1141.0
float	FUEL_DENSITY_FALLBACK = 800.0

Detailed Description

Flight simulation endpoints.

Function Documentation

◆ _apply_propellant_mass_caps()

tuple[dict, dict, float \| None, float \| None, float] backend.routers.flight._apply_propellant_mass_caps	(	dict	config_dict,
			base_config )

protected

Cap LOX/fuel masses to tank capacity. Returns (mass_adjustments, lox_max, fuel_max, fill_factor).

Definition at line 433 of file flight.py.

References _propellant_densities(), and min.

Referenced by _execute_flight_simulation().

◆ _build_mass_cap_info()

MassCapInfo backend.routers.flight._build_mass_cap_info	(	str	branch,
		float	requested_kg,
		float	effective_kg,
		float	tank_volume_m3,
		float	max_fill_kg,
		float	fill_factor )

protected

Definition at line 505 of file flight.py.

Referenced by _compute_propellant_diagnostics().

◆ _ceiling_check()

Optional[dict] backend.routers.flight._ceiling_check	(		flight_config,
			pressure_curves,
		float	burn_time,
		float	nominal_apogee_agl )

protected

Apogee against the ceiling at its high-apogee corner.

The corner is the most vertical, lowest-drag flight the config admits: the rail at 90 deg, the
windless ISA, and -- when drag is the build-up -- a hydraulically smooth skin (roughness 0), the
floor of turbulent friction. A user's drag table has no band and is flown as given.

Definition at line 672 of file flight.py.

References ceiling_agl_m().

Referenced by _execute_flight_simulation().

◆ _compute_propellant_diagnostics()

PropellantDiagnostics backend.routers.flight._compute_propellant_diagnostics	(	*	,
		np.ndarray	times,
		np.ndarray	thrust_array,
		np.ndarray	mdot_O_array,
		np.ndarray	mdot_F_array,
		float	lox_requested,
		float	fuel_requested,
		float	lox_effective,
		float	fuel_effective,
		Optional[float]	lox_tank_max,
		Optional[float]	fuel_tank_max,
		Optional[TruncationInfo]	truncation,
		dict	mass_caps,
		Optional[float]	target_apogee_m,
		Optional[float]	propellant_tank_fill_factor = None )

protected

Definition at line 523 of file flight.py.

References _build_mass_cap_info(), and _integrate_series().

Referenced by _execute_flight_simulation().

◆ _execute_flight_simulation()

FlightSimResponse backend.routers.flight._execute_flight_simulation	(		base_config,
		FlightSimRequest	request,
		*	,
		Optional[np.ndarray]	time_array = None,
		Optional[np.ndarray]	thrust_array = None,
		Optional[np.ndarray]	mdot_O_array = None,
		Optional[np.ndarray]	mdot_F_array = None,
		Optional[float]	lox_mass_kg = None,
		Optional[float]	fuel_mass_kg = None,
		bool	check_ceiling = True )

protected

Run one flight simulation (shared by /simulate and /optimize-altitude).

Definition at line 719 of file flight.py.

References _apply_propellant_mass_caps(), _ceiling_check(), _compute_propellant_diagnostics(), _thrust_reference_pressure(), build_flight_config(), convert_numpy(), extract_flight_series(), and generate_rocket_diagram().

Referenced by _optimize_flight_altitude(), and _simulate_flight().

◆ _integrate_series()

float backend.routers.flight._integrate_series	(	np.ndarray	times,
		np.ndarray	values )

protected

Definition at line 497 of file flight.py.

Referenced by _compute_propellant_diagnostics().

◆ _optimize_flight_altitude()

FlightOptimizeResponse backend.routers.flight._optimize_flight_altitude	(	FlightOptimizeRequest	request,
			config )

protected

Definition at line 961 of file flight.py.

References _execute_flight_simulation(), and ceiling_agl_m().

◆ _propellant_densities()

tuple backend.routers.flight._propellant_densities ( config )

protected

(oxidizer, fuel) liquid densities [kg/m³] from the loaded config's fluids, so propellant
mass-capping follows the selected propellant rather than a hardcoded fuel. Falls back to generic
densities only if the config doesn't carry them.

Definition at line 28 of file flight.py.

Referenced by _apply_propellant_mass_caps().

◆ _simulate_flight()

FlightSimResponse backend.routers.flight._simulate_flight	(	FlightSimRequest	request,
			config )

protected

Definition at line 922 of file flight.py.

References _execute_flight_simulation().

◆ _thrust_reference_pressure()

float backend.routers.flight._thrust_reference_pressure	(		base_config,
		FlightSimRequest	request )

protected

The ambient pressure the thrust curve was computed at [Pa].

The time series ran on the SESSION config, so its elevation (not an elevation the Flight tab
overrides afterwards) sets the reference; the request can state it outright.

Definition at line 641 of file flight.py.

Referenced by _execute_flight_simulation().

◆ build_flight_config()

backend.routers.flight.build_flight_config	(		base_config,
		FlightSimRequest	request )

Build a flight-ready config by merging base config with request overrides.

Definition at line 339 of file flight.py.

Referenced by _execute_flight_simulation().

◆ calculate_tank_capacity()

float backend.routers.flight.calculate_tank_capacity	(	float	height,
		float	radius,
		float	density,
		float	fill_factor = 0.95 )

Calculate max propellant mass for a cylindrical tank.

Args:
    height: Tank height in meters
    radius: Tank radius in meters
    density: Fluid density in kg/m³
    fill_factor: Fill factor (default 95% to avoid overfill)

Returns:
    Maximum propellant mass in kg

Definition at line 43 of file flight.py.

◆ ceiling_agl_m()

Optional[float] backend.routers.flight.ceiling_agl_m	(		design_requirements,
		float	elevation_m )

design_requirements.max_apogee_m as metres above the pad, or None when no ceiling is set.

Definition at line 659 of file flight.py.

Referenced by _ceiling_check(), and _optimize_flight_altitude().

◆ check_rocketpy()

backend.routers.flight.check_rocketpy ( )

Check if RocketPy is available for flight simulation.

Definition at line 1109 of file flight.py.

◆ convert_numpy()

backend.routers.flight.convert_numpy ( obj )

Recursively convert numpy types to Python native types.

Definition at line 60 of file flight.py.

References convert_numpy().

Referenced by _execute_flight_simulation(), and convert_numpy().

◆ extract_flight_series()

backend.routers.flight.extract_flight_series	(		flight_obj,
		float	elevation = 0.0 )

Extract flight time series from RocketPy flight object.

Returns:
    Tuple of (time_array, altitude_agl_array, velocity_array)

Definition at line 311 of file flight.py.

Referenced by _execute_flight_simulation().

◆ generate_rocket_diagram()

Optional[str] backend.routers.flight.generate_rocket_diagram ( flight_obj )

Generate rocket diagram as base64-encoded PNG.

Returns:
    Base64-encoded PNG string, or None if generation fails.

Definition at line 270 of file flight.py.

References decode().

Referenced by _execute_flight_simulation().

◆ optimize_flight_altitude()

backend.routers.flight.optimize_flight_altitude	(	FlightOptimizeRequest	request,
		UserSession	session = Depends(get_session) )

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

In the thread pool: the search flies a dozen RocketPy flights (~7 s on the LE4 stand), and
inline on the event loop /api/health went unanswered for all of it. Every flight of the
search uses the one config read here.

Definition at line 945 of file flight.py.

◆ simulate_flight()

backend.routers.flight.simulate_flight	(	FlightSimRequest	request,
		UserSession	session = Depends(get_session) )

Run flight simulation using time-series data.

Uses provided thrust/mdot arrays from time-series analysis.
Returns apogee, max velocity, and flight trajectory.

In the thread pool: a RocketPy flight is about a second of CPU, and inline on the event loop
it froze every other request (/api/health included) for as long. The config is read once.

Definition at line 904 of file flight.py.

Variable Documentation

◆ FUEL_DENSITY_FALLBACK

float backend.routers.flight.FUEL_DENSITY_FALLBACK = 800.0

Definition at line 25 of file flight.py.

◆ LOX_DENSITY_FALLBACK

float backend.routers.flight.LOX_DENSITY_FALLBACK = 1141.0

Definition at line 24 of file flight.py.

◆ PA_TO_PSI

float backend.routers.flight.PA_TO_PSI = 1.0 / PSI_TO_PA

Definition at line 19 of file flight.py.

◆ PSI_TO_PA

float backend.routers.flight.PSI_TO_PA = 6894.76

Definition at line 18 of file flight.py.

◆ router

backend.routers.flight.router = APIRouter(prefix="/api/flight", tags=["flight"])

Definition at line 14 of file flight.py.

Classes

Functions

Variables

Detailed Description

Function Documentation

◆ _apply_propellant_mass_caps()

◆ _build_mass_cap_info()

◆ _ceiling_check()

◆ _compute_propellant_diagnostics()

◆ _execute_flight_simulation()

◆ _integrate_series()

◆ _optimize_flight_altitude()

◆ _propellant_densities()

◆ _simulate_flight()

◆ _thrust_reference_pressure()

◆ build_flight_config()

◆ calculate_tank_capacity()

◆ ceiling_agl_m()

◆ check_rocketpy()

◆ convert_numpy()

◆ extract_flight_series()

◆ generate_rocket_diagram()

◆ optimize_flight_altitude()

◆ simulate_flight()

Variable Documentation

◆ FUEL_DENSITY_FALLBACK

◆ LOX_DENSITY_FALLBACK

◆ PA_TO_PSI

◆ PSI_TO_PA

◆ router