pub struct Sample {Show 16 fields
pub time_s: f64,
pub phase: Phase,
pub state: State,
pub cg_enu_m: DVec3,
pub cg_velocity_enu_m_s: DVec3,
pub height_above_ground_m: f64,
pub vertical_speed_m_s: f64,
pub acceleration_enu_m_s2: DVec3,
pub airspeed_m_s: f64,
pub mach: f64,
pub angle_of_attack_rad: f64,
pub dynamic_pressure_pa: f64,
pub axial_coefficient: f64,
pub thrust_n: f64,
pub mass_kg: f64,
pub recovery_drag_area_m2: f64,
}Expand description
The flight’s state and the quantities derived from it at one instant.
Fields§
§time_s: f64Time since launch, s: the flight’s clock, from which each motor’s ignition is counted.
phase: PhaseThe phase the flight was in.
state: StateThe integrated state.
cg_enu_m: DVec3The center of mass in the launch frame, m.
cg_velocity_enu_m_s: DVec3The center of mass’s velocity relative to the launch frame, m/s.
height_above_ground_m: f64The center of mass’s ellipsoidal height above the launch site, m.
vertical_speed_m_s: f64The rate of that height, m/s.
acceleration_enu_m_s2: DVec3The nose tip’s acceleration relative to the launch frame, m/s².
airspeed_m_s: f64The airspeed of the center of mass, m/s.
mach: f64Its Mach number.
angle_of_attack_rad: f64The total angle of attack at the center of mass, rad.
dynamic_pressure_pa: f64The dynamic pressure, Pa.
axial_coefficient: f64The axial force coefficient C_A on the reference area.
thrust_n: f64The thrust, N.
mass_kg: f64The mass, kg.
recovery_drag_area_m2: f64The drag area C_D S of the open recovery devices, m² (zero before any deploys).