|
| float | target_apogee_m = Field(..., gt=0, description="Target apogee AGL [m]") |
| float | apogee_tolerance_m = Field(default=15.0, ge=0, description="Apogee undershoot tolerance [m]") |
| Optional | min_burn_time_s = Field(default=None, gt=0, description="Optional lower burn-time bound [s]") |
| Optional | max_burn_time_s = Field(default=None, gt=0, description="Optional upper burn-time bound [s]") |
| List | time_array = Field(..., min_length=2, description="Time array [s]") |
| List | thrust_array = Field(..., min_length=2, description="Thrust array [N]") |
| List | mdot_O_array = Field(..., min_length=2, description="LOX mass flow array [kg/s]") |
| List | mdot_F_array = Field(..., min_length=2, description="Fuel mass flow array [kg/s]") |
| float | lox_mass_kg = Field(default=18.0, gt=0, description="Initial LOX mass [kg]") |
| float | fuel_mass_kg = Field(default=4.0, gt=0, description="Initial fuel mass [kg]") |
| Optional | lox_tank = Field(default=None, description="LOX tank configuration") |
| Optional | fuel_tank = Field(default=None, description="Fuel tank configuration") |
| Optional | environment = Field(default=None, description="Environment configuration") |
| Optional | rocket = Field(default=None, description="Rocket configuration") |
| Optional | reference_pressure_pa |
Request for minimum-fuel burn-time optimization to a target apogee.
Definition at line 241 of file flight.py.
1.15.0