ControlInitState

class ansys.stk.core.stkobjects.astrogator.ControlInitState

IntEnum

Overview

Members

FUEL_MASS	Fuel Mass - the mass of the spacecraft propellant. Enter a value in the selected mass unit (e.g. kg).
CARTESIAN_VX	Vx Component - the X component of the spacecraft velocity vector.
CARTESIAN_VY	Vy Component - the Y component of the spacecraft velocity vector.
CARTESIAN_VZ	Vz Component - the Z component of the spacecraft velocity vector.
CARTESIAN_X	X Component - the X component of the spacecraft position vector.
CARTESIAN_Y	Y Component - the Y component of the spacecraft position vector.
CARTESIAN_Z	Z Component - the Z component of the spacecraft position vector.
CD	Drag Coefficient (Cd) - the dimensionless drag coefficient associated with the drag area.
CR	Solar Radiation Pressure (Spherical) Coefficient (Cr) - the reflectivity of the spacecraft used for solar radiation pressure calculations, where 2.0 is fully reflective and 1.0 is not reflective at all.
DRAG_AREA	Drag Area - the cross-sectional area of the spacecraft assumed perpendicular to the direction of motion, used for atmospheric drag calculations. Enter a value in the selected distance unit squared.
DRY_MASS	Dry Mass - the mass of the spacecraft exclusive of propellant. Enter a value in the selected mass unit (e.g. kg).
EPOCH	Epoch - the orbit epoch.
FUEL_DENSITY	Fuel Density - the density of the fuel tank.
K1	GPS Solar Radiation Pressure K1 - if you are using a non-spherical SRP model, this field defines the model’s K1 (scale) value.
K2	GPS Solar Radiation Pressure K2 - if you are using a non-spherical SRP model, this field defines the model’s K2 (Y bias) value.
KEPLERIAN_ECCENTRICITY	Eccentricity - the ratio of the distance between the foci to the major axis of the orbital ellipse. Dimensionless.
KEPLERIAN_INCLINATION	Inclination - the angle from the +Z axis of the coordinate system to the angular momentum vector of the spacecraft’s orbit.
KEPLERIAN_RAAN	Right Ascension of Ascending Node - the angle between the X direction of the coordinate system and the point where the orbit crosses the X-Y plane in the +Z direction.
KEPLERIAN_SEMIMAJOR_AXIS	Semimajor Axis - half the length of the major (longest) axis of the orbital ellipse.
KEPLERIAN_TRUE_ANOMALY	True Anomaly - the angle from the periapsis of the orbit to the spacecraft’s position vector, measured in the direction of spacecraft motion.
KEPLERIAN_W	Argument of Periapsis - the angle measured in the direction of spacecraft motion, in the orbit plane, from the ascending node to the periapsis of the orbit.
RADIATION_PRESSURE_AREA	Radiation Pressure (Albedo/Thermal) Area - the cross-sectional area of the spacecraft assumed perpendicular to the direction of central body radiation, used for central body radiation (albedo / thermal pressure) calculations.
CK	Radiation Pressure (Albedo/Thermal) Coefficient (Ck) - the reflectivity of the spacecraft used for central body radiation pressure (albedo / thermal pressure) calculations, where 2.0 is fully reflective and 1.0 is not reflective at all.
SPHERICAL_AZIMUTH	Velocity Azimuth - the angle in the spacecraft local horizontal plane between the projection of the velocity vector onto that plane and the local +Z direction measured as positive in the clockwise direction from north.
SPHERICAL_DECLINATION	Declination - the angle from the X-Y plane of the coordinate system to the spacecraft position vector.
SPHERICAL_HORIZONTAL_FLIGHT_PATH_ANGLE	Horizontal Flight Path Angle - the complement of the angle between the spacecraft velocity vector and the radius vector (90 deg minus the vertical flight path angle).
SPHERICAL_RIGHT_ASCENSION	Right Ascension - angle measured in the inertial equatorial plane from the inertial X axis in a right-handed sense about the inertial Z axis to the spacecraft position vector.
SPHERICAL_RADIUS_MAGNITUDE	Radius Magnitude - the magnitude of the spacecraft position vector.
SPHERICAL_VELOCITY_MAGNITUDE	Velocity Magnitude - the magnitude of the spacecraft velocity vector.
SRP_AREA	Solar Radiation Pressure (Spherical) Area - the cross-sectional area of the spacecraft assumed perpendicular to the direction of solar radiation, used for solar radiation calculations.
TANK_PRESSURE	Tank Pressure - the fuel tank pressure.
TANK_TEMPERATURE	Tank Temperature - the temperature of the fuel tank.
TARGET_VECTOR_INCOMING_ASYMPTOTE_DECLINATION	Declination of Incoming Asymptote - the declination of the incoming asymptote in the selected coordinate system.
TARGET_VECTOR_INCOMING_ASYMPTOTE_RIGHT_ASCENSION	Right Ascension of Incoming Asymptote - the right ascension of the hyperbolic incoming asymptote in the selected coordinate system.
TARGET_VECTOR_INCOMING_VELOCITY_AZIMUTH_AT_PERIAPSIS	Velocity Azimuth at Periapsis - the inertial flight path azimuth of the trajectory measured at periapsis.
TARGET_VECTOR_INCOMING_C3	C3 Energy - the energy of the orbit, computed as - mu / a, where mu is the gravity constant of the central body and a is the semimajor axis.
TARGET_VECTOR_INCOMING_RADIUS_OF_PERIAPSIS	Radius of Periapsis - distance from the center of mass of the central body to the periapsis of the hyperbolic orbit.
TARGET_VECTOR_INCOMING_TRUE_ANOMALY	True Anomaly - the angle from the periapsis of the orbit to the spacecraft’s position vector, measured in the direction of spacecraft motion.
TARGET_VECTOR_OUTGOING_ASYMPTOTE_DECLINATION	Declination of Outgoing Asymptote - the declination of the outgoing asymptote in the selected coordinate system.
TARGET_VECTOR_OUTGOING_ASYMPTOTE_RIGHT_ASCENSION	Right Ascension of Outgoing Asymptote - the right ascension of the hyperbolic outgoing asymptote in the selected coordinate system.
TARGET_VECTOR_OUTGOING_VELOCITY_AZIMUTH_AT_PERIAPSIS	Velocity Azimuth at Periapsis - the inertial flight path azimuth of the trajectory measured at periapsis.
TARGET_VECTOR_OUTGOING_C3	C3 Energy - the energy of the orbit, computed as - mu / a, where mu is the gravity constant of the central body and a is the semimajor axis.
TARGET_VECTOR_OUTGOING_RADIUS_OF_PERIAPSIS	Radius of Periapsis - distance from the center of mass of the central body to the periapsis of the hyperbolic orbit.
TARGET_VECTOR_OUTGOING_TRUE_ANOMALY	True Anomaly - the angle from the periapsis of the orbit to the spacecraft’s position vector, measured in the direction of spacecraft motion.
MAX_FUEL_MASS	Maximum Fuel Mass - the maximum fuel mass of the spacecraft; this parameter specifically applies to Finite Maneuver segments that are being executed in Backward Sequences.
TANK_VOLUME	Tank Volume - the volume of the fuel tank.
DELAUNAY_G	G - Magnitude of orbital angular momentum, (G: sqrt(GM * p)).
DELAUNAY_H	H - Z component of orbital angular momentum, (H: G cos(inc)).
DELAUNAY_INCLINATION	Inclination - The angle between the angular momentum vector (perpendicular to the plane of the orbit) and the inertial Z axis.
DELAUNAY_L	L - Related to two-body orbital energy, (L: sqrt(GM * a)).
DELAUNAY_MEAN_ANOMALY	Mean Anomaly - The angle from the eccentricity vector to a position vector where the satellite would be if it were always moving at its average angular rate.
DELAUNAY_RAAN	Right Ascension of Ascending Node - The angle from the inertial X axis to the ascending node measured in a right-handed sense about the inertial Z axis in the equatorial plane.
DELAUNAY_SEMILATUS_RECTUM	Semi-latus Rectum - Distance from focus to orbit at true anomaly of 90 degrees.
DELAUNAY_SEMIMAJOR_AXIS	Semimajor Axis - Half the length of the major (longest) axis of the orbital ellipse.
DELAUNAY_W	Argument of Periapsis - The angle from the ascending node to the eccentricity vector measured in the direction of the satellite’s motion and in the orbit plane.
EQUINOCTIAL_H	H - With K, describe the shape and position of periapsis of the orbit, (H: ecc * sin(RAAN + w)).
EQUINOCTIAL_K	K - With H, describe the shape and position of periapsis of the orbit, (K: ecc * cos(RAAN + w)).
EQUINOCTIAL_MEAN_LONGITUDE	Mean Longitude - (RAAN + w + M).
EQUINOCTIAL_MEAN_MOTION	Mean Motion - The number of orbits per day (86400 sec/period), based on assumed two-body motion.
EQUINOCTIAL_P	P - With Q, describes the orientation of the orbit plane, (P: tan(inc/2) * sin(RAAN)).
EQUINOCTIAL_Q	Q - With P, describes the orientation of the orbit plane, (Q: tan(inc/2) * cos(RAAN)).
EQUINOCTIAL_SEMIMAJOR_AXIS	Semimajor Axis - Half the length of the major (longest) axis of the orbital ellipse.
MIXED_SPHERICAL_ALTITUDE	Altitude - The object’s position above or below the reference ellipsoid. Altitude is measured along a normal to the surface of the reference ellipsoid.
MIXED_SPHERICAL_AZIMUTH	Azimuth - The angle in the satellite local horizontal plane between the projection of the inertial velocity vector onto this plane and the local north direction measured as positive in the clockwise direction.
MIXED_SPHERICAL_HORIZONTAL_FLIGHT_PATH_ANGLE	Horizontal Flight Path Angle - The complement of the angle between the inertial velocity vector and the radius vector.
MIXED_SPHERICAL_LATITUDE	Latitude - The geodetic latitude of a point is the angle between the normal to the reference ellipsoid that passes through the satellite position and the equatorial plane.
MIXED_SPHERICAL_LONGITUDE	Longitude.
MIXED_SPHERICAL_VERTICAL_FLIGHT_PATH_ANGLE	Vertical Flight Path Angle - The angle between the inertial velocity vector and the radius vector.
MIXED_SPHERICAL_V_MAGNITUDE	Velocity Magnitude - The magnitude of the inertial velocity vector.
SPHERICAL_VERTICAL_FLIGHT_PATH_ANGLE	Vertical Flight Path Angle - The angle between the inertial velocity vector and the radius vector.
KEPLERIAN_APOAPSIS_ALTITUDE_SHAPE	Apoapsis Altitude - Shape Parameter - Distance from the surface of the central body to the point of maximum radius in the orbit.
KEPLERIAN_APOAPSIS_ALTITUDE_SIZE	Apoapsis Altitude - Size Parameter - Distance from the surface of the central body to the point of maximum radius in the orbit.
KEPLERIAN_APOAPSIS_RADIUS_SHAPE	Apoapsis Radius - Shape Parameter - Distance from the center of the central body to the point of maximum radius in the orbit.
KEPLERIAN_APOAPSIS_RADIUS_SIZE	Apoapsis Radius - Size Parameter - Distance from the center of the central body to the point of maximum radius in the orbit.
KEPLERIAN_ARGUMENT_LATITUDE	Argument of Latitude - The sum of the True Anomaly and the Argument of Perigee.
KEPLERIAN_ECCENTRIC_ANOMALY	Eccentric Anomaly - Angle measured with an origin at the center of the ellipse from the direction of perigee to a point on a circumscribing circle from which a line perpendicular to the SMA intersects the position of the satellite on the ellipse.
KEPLERIAN_LONGITUDE_OF_ASCENDING_NODE	Longitude of Ascending Node - Longitude of the Ascending Node is the Earth-fixed longitude where the satellite has crossed the inertial equator from south to north based on an assumption of two-body motion.
KEPLERIAN_MEAN_ANOMALY	Mean Anomaly - The angle from the eccentricity vector to a position vector where the satellite would be if it were always moving at its average angular rate.
KEPLERIAN_MEAN_MOTION	Mean Motion - The number of orbits per day (86400 sec/period), based on assumed two-body motion.
KEPLERIAN_PERIAPSIS_ALTITUDE_SHAPE	Periapsis Altitude - Shape Parameter - Distance from the surface of the central body to the point of minimum radius in the orbit.
KEPLERIAN_PERIAPSIS_ALTITUDE_SIZE	Periapsis Altitude - Size Parameter - Distance from the surface of the central body to the point of minimum radius in the orbit.
KEPLERIAN_PERIAPSIS_RADIUS_SHAPE	Periapsis Radius - Shape Parameter - Distance from the center of the central body to the point of minimum radius in the orbit.
KEPLERIAN_PERIAPSIS_RADIUS_SIZE	Periapsis Radius - Size Parameter - Distance from the surface of the central body to the point of minimum radius in the orbit.
KEPLERIAN_PERIOD	Period - The duration of one orbit, based on assumed two-body motion.
KEPLERIAN_TIME_PAST_ASCENDING_NODE	Time Past Ascending Node - The elapsed time since the last ascending node crossing based on assumed two-body motion.
KEPLERIAN_TIME_PAST_PERIAPSIS	Time Past Periapsis - The elapsed time since the last perigee passage based on assumed two-body motion.
SPHERICAL_RANGE_RATE_DECLINATION	Declination - the angle from the X-Y plane of the coordinate system to the spacecraft position vector.
SPHERICAL_RANGE_RATE_RIGHT_ASCENSION	Right Ascension - angle measured in the inertial equatorial plane from the inertial X axis in a right-handed sense about the inertial Z axis to the spacecraft position vector.
SPHERICAL_RANGE_RATE_RANGE	Range - distance of an object from the center point of the coordinate system.
SPHERICAL_RANGE_RATE_DECLINATION_RATE	Declination Rate - the change of the declination angle over time.
SPHERICAL_RANGE_RATE_RIGHT_ASCENSION_RATE	Right Ascension Rate - the change of the right ascension angle over time.
SPHERICAL_RANGE_RATE_RANGE_RATE	Range Rate - the change in the range over time.

Import detail

from ansys.stk.core.stkobjects.astrogator import ControlInitState