|
| float | airframe_mass = Field(default=78.72, gt=0, description="Airframe mass (no propulsion) [kg]") |
| float | engine_mass = Field(default=8.0, gt=0, description="Engine + plumbing mass [kg]") |
| float | lox_tank_structure_mass = Field(default=5.0, gt=0, description="Empty LOX tank mass [kg]") |
| float | fuel_tank_structure_mass = Field(default=3.0, gt=0, description="Empty fuel tank mass [kg]") |
| float | radius = Field(default=0.1015, gt=0, description="Rocket radius [m]") |
| float | rocket_length = Field(default=3.5, gt=0, description="Rocket total length [m]") |
| float | motor_position = Field(default=0.0, ge=0, description="Motor position from tail [m]") |
| List | inertia = Field(default=[8.0, 8.0, 0.5], min_length=3, max_length=3, description="Inertia [Ixx, Iyy, Izz] [kg·m²]") |
| Optional | fins = Field(default=None, description="Fins configuration") |
| str | nose_kind = Field(default="vonKarman", description="Nosecone profile (RocketPy kind)") |
| float | nose_fineness_ratio = Field(default=4.5, gt=0, description="Nose length / body diameter (von Kármán ~4.5:1)") |
| Optional | nose_length = Field(default=None, gt=0, description="Explicit nose length [m] (overrides fineness ratio)") |
| float | avionics_payload_length_m = Field(default=4.0, ge=0, description="Avionics/payload/recovery length above propulsion, before the nose [m]") |
| Optional | copv_dry_mass = Field(default=None, gt=0, description="Empty COPV mass [kg]") |
| Optional | surface_roughness_m = Field(default=None, ge=0, description="Skin roughness for the drag build-up [m]") |
| Optional | fin_thickness_m = Field(default=None, gt=0, description="Fin thickness for the drag build-up [m]") |
| Optional | fin_profile = Field(default=None, description="Fin edge profile for the drag build-up") |
Rocket configuration for flight simulation.
Definition at line 114 of file flight.py.
1.15.0