flight.py File Reference

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Classes
class	backend.routers.flight.EnvironmentConfig
class	backend.routers.flight.FinsConfig
class	backend.routers.flight.RocketConfig
class	backend.routers.flight.TankConfig
class	backend.routers.flight.FlightSimRequest
class	backend.routers.flight.FlightTrajectory
class	backend.routers.flight.TruncationInfo
class	backend.routers.flight.MassCapInfo
class	backend.routers.flight.PropellantDiagnostics
class	backend.routers.flight.FlightSimResponse
class	backend.routers.flight.FlightOptimizeRequest
class	backend.routers.flight.FlightOptimizeResponse

Namespaces
namespace	backend
namespace	backend.routers
namespace	backend.routers.flight

Functions
tuple	backend.routers.flight._propellant_densities (config)
float	backend.routers.flight.calculate_tank_capacity (float height, float radius, float density, float fill_factor=0.95)
	backend.routers.flight.convert_numpy (obj)
Optional[str]	backend.routers.flight.generate_rocket_diagram (flight_obj)
	backend.routers.flight.extract_flight_series (flight_obj, float elevation=0.0)
	backend.routers.flight.build_flight_config (base_config, FlightSimRequest request)
tuple[dict, dict, float|None, float|None, float]	backend.routers.flight._apply_propellant_mass_caps (dict config_dict, base_config)
float	backend.routers.flight._integrate_series (np.ndarray times, np.ndarray values)
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)
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)
float	backend.routers.flight._thrust_reference_pressure (base_config, FlightSimRequest request)
Optional[float]	backend.routers.flight.ceiling_agl_m (design_requirements, float elevation_m)
Optional[dict]	backend.routers.flight._ceiling_check (flight_config, pressure_curves, float burn_time, float nominal_apogee_agl)
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)
	backend.routers.flight.simulate_flight (FlightSimRequest request, UserSession session=Depends(get_session))
FlightSimResponse	backend.routers.flight._simulate_flight (FlightSimRequest request, config)
	backend.routers.flight.optimize_flight_altitude (FlightOptimizeRequest request, UserSession session=Depends(get_session))
FlightOptimizeResponse	backend.routers.flight._optimize_flight_altitude (FlightOptimizeRequest request, config)
	backend.routers.flight.check_rocketpy ()

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