Param

Member	Value	Description
eVAControlInitStateFuelMass	300	Fuel Mass - the mass of the spacecraft propellant. Enter a value in the selected mass unit (e.g. kg).
eVAControlInitStateCartesianVx	301	Vx Component - the X component of the spacecraft velocity vector.
eVAControlInitStateCartesianVy	302	Vy Component - the Y component of the spacecraft velocity vector.
eVAControlInitStateCartesianVz	303	Vz Component - the Z component of the spacecraft velocity vector.
eVAControlInitStateCartesianX	304	X Component - the X component of the spacecraft position vector.
eVAControlInitStateCartesianY	305	Y Component - the Y component of the spacecraft position vector.
eVAControlInitStateCartesianZ	306	Z Component - the Z component of the spacecraft position vector.
eVAControlInitStateCd	307	Drag Coefficient (Cd) - the dimensionless drag coefficient associated with the drag area.
eVAControlInitStateCr	308	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.
eVAControlInitStateDragArea	309	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.
eVAControlInitStateDryMass	310	Dry Mass - the mass of the spacecraft exclusive of propellant. Enter a value in the selected mass unit (e.g. kg).
eVAControlInitStateEpoch	311	Epoch - the orbit epoch.
eVAControlInitStateFuelDensity	312	Fuel Density - the density of the fuel tank.
eVAControlInitStateK1	313	GPS Solar Radiation Pressure K1 - if you are using a non-spherical SRP model, this field defines the model's K1 (scale) value.
eVAControlInitStateK2	314	GPS Solar Radiation Pressure K2 - if you are using a non-spherical SRP model, this field defines the model's K2 (Y bias) value.
eVAControlInitStateKeplerianEcc	315	Eccentricity - the ratio of the distance between the foci to the major axis of the orbital ellipse. Dimensionless.
eVAControlInitStateKeplerianInc	316	Inclination - the angle from the +Z axis of the coordinate system to the angular momentum vector of the spacecraft's orbit.
eVAControlInitStateKeplerianRAAN	317	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.
eVAControlInitStateKeplerianSMA	318	Semimajor Axis - half the length of the major (longest) axis of the orbital ellipse.
eVAControlInitStateKeplerianTA	319	True Anomaly - the angle from the periapsis of the orbit to the spacecraft's position vector, measured in the direction of spacecraft motion.
eVAControlInitStateKeplerianW	320	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.
eVAControlInitStateModifiedKeplerianEcc	321	This enumeration is deprecated.
eVAControlInitStateModifiedKeplerianInc	322	This enumeration is deprecated.
eVAControlInitStateModifiedKeplerianRAAN	323	This enumeration is deprecated.
eVAControlInitStateModifiedKeplerianRp	324	This enumeration is deprecated.
eVAControlInitStateModifiedKeplerianTA	325	This enumeration is deprecated.
eVAControlInitStateModifiedKeplerianW	326	This enumeration is deprecated.
eVAControlInitStateRadiationPressureArea	327	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.
eVAControlInitStateCk	328	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.
eVAControlInitStateSphericalAz	329	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.
eVAControlInitStateSphericalDec	330	Declination - the angle from the X-Y plane of the coordinate system to the spacecraft position vector.
eVAControlInitStateSphericalHorizFPA	331	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).
eVAControlInitStateSphericalRA	332	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.
eVAControlInitStateSphericalRMag	333	Radius Magnitude - the magnitude of the spacecraft position vector.
eVAControlInitStateSphericalVMag	334	Velocity Magnitude - the magnitude of the spacecraft velocity vector.
eVAControlInitStateSRPArea	335	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.
eVAControlInitStateTankPressure	336	Tank Pressure - the fuel tank pressure.
eVAControlInitStateTankTemp	337	Tank Temperature - the temperature of the fuel tank.
eVAControlInitStateTargetVecInAsympDec	338	Declination of Incoming Asymptote - the declination of the incoming asymptote in the selected coordinate system.
eVAControlInitStateTargetVecInAsympRA	339	Right Ascension of Incoming Asymptote - the right ascension of the hyperbolic incoming asymptote in the selected coordinate system.
eVAControlInitStateTargetVecInVelAzAtPeriapsis	340	Velocity Azimuth at Periapsis - the inertial flight path azimuth of the trajectory measured at periapsis.
eVAControlInitStateTargetVecInC3	341	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.
eVAControlInitStateTargetVecInRadOfPeriapsis	342	Radius of Periapsis - distance from the center of mass of the central body to the periapsis of the hyperbolic orbit.
eVAControlInitStateTargetVecInTrueAnomaly	343	True Anomaly - the angle from the periapsis of the orbit to the spacecraft's position vector, measured in the direction of spacecraft motion.
eVAControlInitStateTargetVecOutAsympDec	344	Declination of Outgoing Asymptote - the declination of the outgoing asymptote in the selected coordinate system.
eVAControlInitStateTargetVecOutAsympRA	345	Right Ascension of Outgoing Asymptote - the right ascension of the hyperbolic outgoing asymptote in the selected coordinate system.
eVAControlInitStateTargetVecOutVelAzAtPeriapsis	346	Velocity Azimuth at Periapsis - the inertial flight path azimuth of the trajectory measured at periapsis.
eVAControlInitStateTargetVecOutC3	347	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.
eVAControlInitStateTargetVecOutRadOfPeriapsis	348	Radius of Periapsis - distance from the center of mass of the central body to the periapsis of the hyperbolic orbit.
eVAControlInitStateTargetVecOutTrueAnomaly	349	True Anomaly - the angle from the periapsis of the orbit to the spacecraft's position vector, measured in the direction of spacecraft motion.
eVAControlInitStateMaxFuelMass	350	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.
eVAControlInitStateTankVolume	351	Tank Volume - the volume of the fuel tank.
eVAControlInitStateDelaunayG	352	G - Magnitude of orbital angular momentum, sqrt(GM * p).
eVAControlInitStateDelaunayH	353	H - Z component of orbital angular momentum, G cos(inc).
eVAControlInitStateDelaunayInc	354	Inclination - The angle between the angular momentum vector (perpendicular to the plane of the orbit) and the inertial Z axis.
eVAControlInitStateDelaunayL	355	L - Related to two-body orbital energy, sqrt(GM * a)
eVAControlInitStateDelaunayMeanAnomaly	356	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.
eVAControlInitStateDelaunayRAAN	357	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.
eVAControlInitStateDelaunaySemiLatusRectum	358	Semi-latus Rectum - Distance from focus to orbit at true anomaly of 90 degrees
eVAControlInitStateDelaunaySMA	359	Semimajor Axis - Half the length of the major (longest) axis of the orbital ellipse.
eVAControlInitStateDelaunayW	360	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.
eVAControlInitStateEquinoctialH	361	H - With K, describe the shape and position of periapsis of the orbit, ecc * sin(RAAN + w)
eVAControlInitStateEquinoctialK	362	K - With H, describe the shape and position of periapsis of the orbit, ecc * cos(RAAN + w)
eVAControlInitStateEquinoctialMeanLongitude	363	Mean Longitude - RAAN + w + M
eVAControlInitStateEquinoctialMeanMotion	364	Mean Motion - The number of orbits per day (86400 sec/period), based on assumed two-body motion.
eVAControlInitStateEquinoctialP	365	P - With Q, describes the orientation of the orbit plane, tan(inc/2) * sin(RAAN)
eVAControlInitStateEquinoctialQ	366	Q - With P, describes the orientation of the orbit plane, tan(inc/2) * cos(RAAN)
eVAControlInitStateEquinoctialSMA	367	Semimajor Axis - Half the length of the major (longest) axis of the orbital ellipse.
eVAControlInitStateMixedSphericalAltitude	368	Altitude - The object's position above or below the reference ellipsoid. Altitude is measured along a normal to the surface of the reference ellipsoid.
eVAControlInitStateMixedSphericalAzimuth	369	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.
eVAControlInitStateMixedSphericalHorizFPA	370	Horizontal Flight Path Angle - The complement of the angle between the inertial velocity vector and the radius vector.
eVAControlInitStateMixedSphericalLatitude	371	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.
eVAControlInitStateMixedSphericalLongitude	372	Longitude
eVAControlInitStateMixedSphericalVerticalFPA	373	Vertical Flight Path Angle - The angle between the inertial velocity vector and the radius vector.
eVAControlInitStateMixedSphericalVMag	374	Velocity Magnitude - The magnitude of the inertial velocity vector.
eVAControlInitStateSphericalVerticalFPA	375	Vertical Flight Path Angle - The angle between the inertial velocity vector and the radius vector.
eVAControlInitStateKeplerianApoapsisAltShape	376	Apoapsis Altitude - Shape Parameter - Distance from the surface of the central body to the point of maximum radius in the orbit.
eVAControlInitStateKeplerianApoapsisAltSize	377	Apoapsis Altitude - Size Parameter - Distance from the surface of the central body to the point of maximum radius in the orbit.
eVAControlInitStateKeplerianApoapsisRadShape	378	Apoapsis Radius - Shape Parameter - Distance from the center of the central body to the point of maximum radius in the orbit.
eVAControlInitStateKeplerianApoapsisRadSize	379	Apoapsis Radius - Size Parameter - Distance from the center of the central body to the point of maximum radius in the orbit.
eVAControlInitStateKeplerianArgLat	380	Argument of Latitude - The sum of the True Anomaly and the Argument of Perigee.
eVAControlInitStateKeplerianEccAnomaly	381	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.
eVAControlInitStateKeplerianLAN	382	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.
eVAControlInitStateKeplerianMeanAnomaly	383	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.
eVAControlInitStateKeplerianMeanMotion	384	Mean Motion - The number of orbits per day (86400 sec/period), based on assumed two-body motion.
eVAControlInitStateKeplerianPeriapsisAltShape	385	Periapsis Altitude - Shape Parameter - Distance from the surface of the central body to the point of minimum radius in the orbit.
eVAControlInitStateKeplerianPeriapsisAltSize	386	Periapsis Altitude - Size Parameter - Distance from the surface of the central body to the point of minimum radius in the orbit.
eVAControlInitStateKeplerianPeriapsisRadShape	387	Periapsis Radius - Shape Parameter - Distance from the center of the central body to the point of minimum radius in the orbit.
eVAControlInitStateKeplerianPeriapsisRadSize	388	Periapsis Radius - Size Parameter - Distance from the surface of the central body to the point of minimum radius in the orbit.
eVAControlInitStateKeplerianPeriod	389	Period - The duration of one orbit, based on assumed two-body motion.
eVAControlInitStateKeplerianTimePastAN	390	Time Past Ascending Node - The elapsed time since the last ascending node crossing based on assumed two-body motion.
eVAControlInitStateKeplerianTimePastPeriapsis	391	Time Past Periapsis - The elapsed time since the last perigee passage based on assumed two-body motion.

IAgVAMCSInitialState Interface