Data Provider Groups | Data Provider Elements

Astrogator Values

Calc Object values, as a function of time. Each Calc Object contained in the Component Browser is available for use, including user defined Calc Objects. The Calc Objects listed here are representative.

Available for these objects: Aircraft, GroundVehicle, Satellite, Ship

Type: Time-varying data.

Availability: Reports | Graphs | Dynamic Displays | Strip Charts

Data Provider Groups

Name	Description
Top	Time measures.
Access	An Access calculation object that computes access between two objects.
Cartesian Elems	Calc Objects for the ephemeris of the object, expressed in Cartesian components. Each Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Cartesian STM	The 36 position and velocity state transition matrix elements for use in combination with the State Transition Matrix propagator function and valid for consecutive Propagate Segments. Expressed in Cartesian components, and allowing for choice of coordinate system. The default is Earth Centered Inertial.
Constants	Constant values used in astrodynamic calculations.
Delaunay Elems	A set of canonical angle-action variables commonly used in general perturbation theories. An orbit is defined by a set of conjugate angle-action pairs.
Environment	Calc Objects for the satellite environment.
Equinoctial Elems	Calc Objects for the ephemeris of the object, expressed in equinoctial elements. Each Calc Object allows a choice of element type (Osculating elements, Kozai-Izsak Mean elements, Brouwer-Lyddane Mean elements using only short period terms, and Brouwer-Lyddane Mean elements using both short and long period terms). The default is osculating. Each Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Formation	Calc Objects for relative motion and close approaches with respect to the master satellite or a specified vehicle. See also Relative Motion. The close approach X axis is the unit vector in the direction of the cross product of the relative velocity vector with the orbit momentum vector of the reference vehicle. The close approach Y axis is the unit vector in the direction of the cross product of the X axis and the relative velocity vector. The close approach plane is the plane spanned by the X and Y axes. The close approach vector is the relative position vector from the reference vehicle.
GeoStationary	Calc Objects that are useful for station keeping of geostationary satellites. Each Calc Object allows a choice of a central body. The default is Earth.
Geodetic	Calc Objects for the ephemeris of the object, expressed in LLA elements. Each Calc Object allows a choice of a central body. The default is Earth.
Ground Track	Calc Objects for maintaining a repeating ground track.
Keplerian Elems	Calc Objects for the ephemeris of the object, expressed in keplerian (i.e., instantaneous two-body) elements. Each Calc Object allows a choice of element type (Osculating elements, Kozai-Izsak Mean elements, Brouwer-Lyddane Mean elements using only short period terms, and Brouwer-Lyddane Mean elements using both short and long period terms). The default is osculating.
Maneuver	Maneuver related Calc Objects.
Math	Used to perform functions on other Calc Objects.
Mean Elems	Calc Objects for the ephemeris of the object, expressed in Keplerian elements. Each Calc Object allows a choice of element type (Osculating elements, Kozai-Izsak Mean elements, Brouwer-Lyddane Mean elements using only short period terms, and Brouwer-Lyddane Mean elements using both short and long period terms). The default is Kozai-Izsak mean elements. The mean elements are computed using mean element theory (not simply a numerical average of the element over a period), considering only gravity perturbations (J2 and for some theories J3 through J5).
MultiBody	Used for targeting a different central body. See also B-plane targeting under Astrogator help.
Other Orbit	Miscellaneous Calc Objects.
Power	Calc Objects that compute power.
Relative Motion	Calc Objects for relative ephemeris. The relative ephemeris is computed with respect to two rotating frames, the RIC (Radial, In-Track, Cross-Track) frame and the NTC (Normal, Tangential, and Cross-Track) frames, that are defined using the primary's ephemeris. Cross-track refers to the direction perpendicular to the position and inertial velocity; in-track refers to the direction perpendicular to both the radial and cross-track (positive in the direction of motion); tangential refers to the direction along the velocity vector; and normal refers to the direction perpendicular to the velocity and cross-track directions (positive outward along radial). Each Calc Object allows a choice of a central body. The default is Earth. See Also Formation.
SEET	Calc Objects utilizing computations provided by SEET.
Scalar	Scalar calculation component.
Scripts	Values from Astrogator plugin scripts.
Spacecraft Properties	Calc objects for spacecraft properties.
Spherical Elems	Calc Objects for the ephemeris of the object, expressed in spherical elements.
Target Vector	Data for incoming and outgoing asymptotes as well as C3 energy.
Time	Time related Calc Objects.
UserValues	User Variable related Calc Objects.
Vector	Vector-related Calc Objects.
Segment Data	Properties of each MCS segment in the Astrogator satellite.

Data Provider Elements

Top
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Epoch	Date	Real Number or Text	The reference epoch for the object.

Access
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Access	Unitless	Real Number	Indicates whether there is access between two objects. 1 = access, and 0 = no access.

Cartesian Elems
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Vx	Rate	Real Number	X Cartesian component of velocity.
Vy	Rate	Real Number	Y Cartesian component of velocity.
Vz	Rate	Real Number	Z Cartesian component of velocity.
X	Distance	Real Number	The X component of the position vector in the coordinate system specified by this Calc Object.
Y	Distance	Real Number	The Y component of the position vector in the coordinate system specified by this Calc Object.
Z	Distance	Real Number	The Z component of the position vector in the coordinate system specified by this Calc Object.

Cartesian STM
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
STMPosXPosX	Unitless	Real Number	State transition function: delta(PosX,tf) = [this value] * delta(PosX,ti).
STMPosXPosY	Unitless	Real Number	State transition function: delta(PosX,tf) = [this value] * delta(PosY,ti).
STMPosXPosZ	Unitless	Real Number	State transition function: delta(PosX,tf) = [this value] * delta(PosZ,ti).
STMPosXVelX	Unitless	Real Number	State transition function: delta(PosX,tf) = [this value] * delta(VelX,ti).
STMPosXVelY	Unitless	Real Number	State transition function: delta(PosX,tf) = [this value] * delta(VelY,ti).
STMPosXVelZ	Unitless	Real Number	State transition function: delta(PosX,tf) = [this value] * delta(VelZ,ti).
STMPosYPosX	Unitless	Real Number	State transition function: delta(PosY,tf) = [this value] * delta(PosX,ti).
STMPosYPosY	Unitless	Real Number	State transition function: delta(PosY,tf) = [this value] * delta(PosY,ti).
STMPosYPosZ	Unitless	Real Number	State transition function: delta(PosY,tf) = [this value] * delta(PosZ,ti).
STMPosYVelX	Unitless	Real Number	State transition function: delta(PosY,tf) = [this value] * delta(VelX,ti).
STMPosYVelY	Unitless	Real Number	State transition function: delta(PosY,tf) = [this value] * delta(VelY,ti).
STMPosYVelZ	Unitless	Real Number	State transition function: delta(PosY,tf) = [this value] * delta(VelZ,ti).
STMPosZPosX	Unitless	Real Number	State transition function: delta(PosZ,tf) = [this value] * delta(PosX,ti).
STMPosZPosY	Unitless	Real Number	State transition function: delta(PosZ,tf) = [this value] * delta(PosY,ti).
STMPosZPosZ	Unitless	Real Number	State transition function: delta(PosZ,tf) = [this value] * delta(PosZ,ti).
STMPosZVelX	Unitless	Real Number	State transition function: delta(PosZ,tf) = [this value] * delta(VelX,ti).
STMPosZVelY	Unitless	Real Number	State transition function: delta(PosZ,tf) = [this value] * delta(VelY,ti).
STMPosZVelZ	Unitless	Real Number	State transition function: delta(PosZ,tf) = [this value] * delta(VelZ,ti).
STMVelXPosX	Unitless	Real Number	State transition function: delta(VelX,tf) = [this value] * delta(PosX,ti).
STMVelXPosY	Unitless	Real Number	State transition function: delta(VelX,tf) = [this value] * delta(PosY,ti).
STMVelXPosZ	Unitless	Real Number	State transition function: delta(VelX,tf) = [this value] * delta(PosZ,ti).
STMVelXVelX	Unitless	Real Number	State transition function: delta(VelX,tf) = [this value] * delta(VelX,ti).
STMVelXVelY	Unitless	Real Number	State transition function: delta(VelX,tf) = [this value] * delta(VelY,ti).
STMVelXVelZ	Unitless	Real Number	State transition function: delta(VelX,tf) = [this value] * delta(VelZ,ti).
STMVelYPosX	Unitless	Real Number	State transition function: delta(VelY,tf) = [this value] * delta(PosX,ti).
STMVelYPosY	Unitless	Real Number	State transition function: delta(VelY,tf) = [this value] * delta(PosY,ti).
STMVelYPosZ	Unitless	Real Number	State transition function: delta(VelY,tf) = [this value] * delta(PosZ,ti).
STMVelYVelX	Unitless	Real Number	State transition function: delta(VelY,tf) = [this value] * delta(VelX,ti).
STMVelYVelY	Unitless	Real Number	State transition function: delta(VelY,tf) = [this value] * delta(VelY,ti).
STMVelYVelZ	Unitless	Real Number	State transition function: delta(VelY,tf) = [this value] * delta(VelZ,ti).
STMVelZPosX	Unitless	Real Number	State transition function: delta(VelZ,tf) = [this value] * delta(PosX,ti).
STMVelZPosY	Unitless	Real Number	State transition function: delta(VelZ,tf) = [this value] * delta(PosY,ti).
STMVelZPosZ	Unitless	Real Number	State transition function: delta(VelZ,tf) = [this value] * delta(PosZ,ti).
STMVelZVelX	Unitless	Real Number	State transition function: delta(VelZ,tf) = [this value] * delta(VelX,ti).
STMVelZVelY	Unitless	Real Number	State transition function: delta(VelZ,tf) = [this value] * delta(VelY,ti).
STMVelZVelZ	Unitless	Real Number	State transition function: delta(VelZ,tf) = [this value] * delta(VelZ,ti).

Constants
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Gravitational_Parameter	Grav Parameter	Real Number	Gravitational Parameter of a central body.
Gravity_Coefficient	Unitless	Real Number	Coefficient value of a gravity field.
Pi	Unitless	Real Number	The common mathematical constant consistent with the ratio of a circle's circumference to its diameter.
Reference_Radius	Distance	Real Number	Reference radius of a central body.
Speed_of_Light	Rate	Real Number	Light speed.

Delaunay Elems
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Delaunay_G	Area Rate	Real Number	The magnitude of the orbital angular momentum: sqrt (GM * p).
Delaunay_H	Area Rate	Real Number	The Z component of the orbital angular momentum: G cos(inc).
Delaunay_L	Area Rate	Real Number	sqrt (GM * a).
Semi-latus_Rectum	Distance	Real Number	The distance from focus to orbit at true anomaly of 90 degrees.

Environment
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
AtmosDensity	Density	Real Number	The density of the atmosphere. The default is the US Standard Atmosphere, though other models are available.
AtmosPressure	Pressure	Real Number	The pressure of the atmosphere. The default is the US Standard Atmosphere, though other models are available. Some density models do not compute the pressure, in which case an error condition is returned.
AtmosTemperature	Temperature	Real Number	The temperature of the atmosphere. The default is the US Standard Atmosphere, though other models are available. Some density models do not compute the temperature, in which case an error condition is returned.

Equinoctial Elems
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Equinoctial_h	Unitless	Real Number	h = eccentricity * sin(right_ascension_of_the_ascending_node + argument_of_periapse). Equinoctial elements h and k together describe the shape of the orbit and the location of the periapse.
Equinoctial_k	Unitless	Real Number	k = eccentricity * cos(right_ascension_of_the_ascending_node + argument_of_periapse). Equinoctial elements h and k together describe the shape of the orbit and the location of the periapse.
Equinoctial_p	Unitless	Real Number	p = tan(inclination/2) * sin(right_ascension_of_the_ascending_node). Equinoctial elements p and q together describe the orientation of the orbit plane. Retrograde orbits have a singularity at zero inclination, and posigrade orbits have a singularity at 180 deg inclination.
Equinoctial_q	Unitless	Real Number	q = tan(inclination/2) * cos(right_ascension_of_the_ascending_node). Equinoctial elements p and q together describe the orientation of the orbit plane. Retrograde orbits have a singularity at zero inclination, and posigrade orbits have a singularity at 180 deg inclination.
Mean_Longitude	Angle	Real Number or Text	mean longitude is the sum: right_ascension_of_the_ascending_node + argument_of_periapse + mean_anomaly. A measure of the location within the orbit.

Formation
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
CloseApproachBearing	Angle	Real Number or Text	The angle from the relative velocity vector to the reference vehicle. The Calc Object allows a choice of a central body. The default is Earth.
CloseApproachMagnitude	Distance	Real Number	The magnitude of close approach vector. The value is sqrt(x^2 + y^2). The Calc Object allows a choice of a central body. The default is Earth.
CloseApproachTheta	Angle	Real Number or Text	The angle from X to close approach vector. The Calc Object allows a choice of a central body. The default is Earth.
CloseApproachX	Distance	Real Number	The X component of close approach vector. The Calc Object allows a choice of a central body. The default is Earth.
CloseApproachY	Distance	Real Number	The Y component of close approach vector. The Calc Object allows a choice of a central body. The default is Earth.
CosineOfCloseApproachBearing	Unitless	Real Number	The cosine of the close approach bearing. The Calc Object allows a choice of a central body. The default is Earth.
Rel_Mean_Arg_of_Lat	Angle	Real Number or Text	The relative mean argument of latitude compared to the reference vehicle.
Rel_Mean_Arg_of_Perigee	Angle	Real Number or Text	The relative mean argument of perigee compared to the reference vehicle.
Rel_Mean_Eccentricity	Unitless	Real Number	The relative mean eccentricity compared to the reference vehicle.
Rel_Mean_Inclination	Angle	Real Number or Text	The relative mean inclination compared to the reference vehicle.
Rel_Mean_Mean_Anomaly	Angle	Real Number or Text	The relative mean mean anomaly compared to the reference vehicle.
Rel_Mean_Period	Time	Real Number	The relative mean orbit period compared to the reference vehicle.
Rel_Mean_RAAN	Angle	Real Number or Text	The relative mean RAAN compared to the reference vehicle.
Rel_Mean_Semimajor_Axis	Distance	Real Number	The relative mean semimajor axis compared to the reference vehicle.
RelativeAtAOL	Time	Real Number	The relative value (i.e., difference between the value computed for this satellite and the reference vehicle) of a specified calculation object. The value for the satellite is computed at the current state; the value for the reference is computed at either the previous or next state where the reference vehicle's argument of latitude is the same as the satellite's current value.
RelativeValue	Time	Real Number	The relative value (i.e., difference between the value computed for this satellite and the reference vehicle) of a specified calculation object. Both values are computed at the given epoch.
RelGroundTrackError	Distance	Real Number	Ground track error compared to the reference vehicle. The value for the satellite is computed at the current state; the value for the reference is computed at either the previous or next state where the reference vehicle's argument of latitude is the same as the satellite's current value. The ground track error can be unsigned or signed based on RxV.

GeoStationary
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Longitude_Drift_Rate	AngleRate	Real Number	The difference between the mean orbital rate and the central body rotation rate. The Calc Object allows a choice of element type (Osculating elements, Kozai-Izsak Mean elements, Brouwer-Lyddane Mean elements using only short period terms, and Brouwer-Lyddane Mean elements using both short and long period terms). The default is osculating. The mean orbital rate is computing using the element type and accounting for the effects of J2 of the central body.
Mean_Earth_Longitude	Angle	Real Number or Text	Mean longitude, computed in the True Of Date coordinate system, minus the Greenwich hour angle. This Calc Object is only valid for the Earth central body.
RectifiedLongitude	Angle	Real Number or Text	Two-body rectified longitude with respect to central body. The rectified motion moves nearly uniformally in true anomaly. The value is computed by first determining the two-body orbital elements, re-assigning the true anomaly value to the value of the mean anomaly, computing the cartesian position using these modified elements, and then computing the corresponding longitude from that position.

Geodetic
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Altitude	Distance	Real Number	The altitude value (i.e., magnitude of the relative position vector between the object and its detic subpoint).
AltitudeRate	Rate	Real Number	The rate of change of altitude.
Height_above_terrain	Distance	Real Number	The height above the terrain.
Latitude	Angle	Real Number or Text	The detic latitude (i.e., angle between the detic subpoint's surface normal vector and the XY plane).
LatitudeRate	AngleRate	Real Number	The rate of change of the detic latitude.
Longitude	Angle	Real Number or Text	The detic longitude (i.e., angle from the X-axis locating the projection of the detic subpoint's surface normal vector onto the XY plane.) Longitude increases in the direction found using the right-hand rule about the Z-axis.
LongitudeRate	AngleRate	Real Number	The rate of change of the detic longitude.

Ground Track
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
RepeatingGroundTrackEquatorError	Distance	Real Number	The difference between the current longitude and the nearest grid point longitude computed as point of an orbit with the specified repeat count and reference longitude. This Calc Object should only be evaluated at an XY plane crossing. The reference longitude can range from -360 to 360 deg. The repeat count gives the number of orbits before the ground track repeats over the same longitude. The Calc Object allows a choice of a central body. The default is Earth.

Keplerian Elems
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Altitude_Of_Apoapsis	Distance	Real Number	The difference between the radius of apoapsis and the central body's equatorial radius. The Calc Object allows a choice of a central body. The default is Earth.
Altitude_Of_Periapsis	Distance	Real Number	The difference between the radius of apoapsis and the central body's equatorial radius. The Calc Object allows a choice of a central body. The default is Earth.
Argument_of_Latitude	Angle	Real Number or Text	The sum of the argument of periapsis and true anomaly. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Argument_of_Periapsis	Angle	Real Number or Text	The angle from the ascending node to the periapsis vector measured in the orbit plane in the direction of the object's motion. The periapsis vector locates the closest point of the orbit. For a circular orbit, the value is defined to be zero (i.e., periapsis at the ascending node). The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Eccentric_Anomaly	Angle	Real Number or Text	An angle used for converting between true and mean anomaly. Has a geometrical definition as the angle between the line of apsides and a line running from the center of the ellipse to a point Q on a circle circumscribed about the ellipse. The point Q is a projection of the satellite along a line parallel to the minor axis of the ellipse. The Calc Object allows a choice of a central body. The default is Earth.
Eccentricity	Unitless	Real Number	A measure of the shape of the orbit. Values <1 indicate an ellipse (where zero is a circular orbit) and values >1 indicate a hyperbola.
Inclination	Angle	Real Number or Text	The angle between the orbit plane and the XY plane of the coordinate system.
Longitude_Of_Ascending_Node	Angle	Real Number or Text	A measure of the right ascension of the ascending node, made in the Fixed frame. The value is the detic longitude of the orbit's ascending node. The ascending node crossing is assumed to be at, or prior to, the current position in the orbit in the same nodal revolution. The Calc Object allows a choice of a central body. The default is Earth.
Mean_Motion	AngleRate	Real Number	A measure of the osculating period of the orbit, expressed as an angular rate. The value is 2pi rad / orbit_period. The Calc Object allows a choice of a central body. The default is Earth.
MeanAnomaly	Angle	Real Number or Text	A measure of the time past periapsis passing, expressed as an angle. The Calc Object allows a choice of a central body. The default is Earth.
Orbit_Period	Time	Real Number	Time required for a complete revolution as computed from osculating semi-major axis length. The Calc Object allows a choice of a central body. The default is Earth.
RAAN	Angle	Real Number or Text	The angle in the XY plane from the X axis to the ascending node, measured in a right-handed sense about the Z axis. in the equatorial plane. For equatorial orbits, the ascending node is defined to be directed along the positive X axis, and thus the value is 0.0. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Radius_Of_Apoapsis	Distance	Real Number	The magnitude of the apoapsis vector. The apoapsis vector (defined only when the eccentricity is <1) locates the position in the orbit furthest from the central body. The Calc Object allows a choice of a central body. The default is Earth.
Radius_Of_Periapsis	Distance	Real Number	The magnitude of the periapsis vector. The periapsis vector locates the position in the orbit closest to the central body. The Calc Object allows a choice of a central body. The default is Earth.
Semimajor_Axis	Distance	Real Number	A measure of the size of the orbit. Orbits with eccentricity less than 1 are ellipses, with major and minor axes identifying the symmetry axes of the ellipse, the major axis being the longer one. The value is half the length of the major axis. The Calc Object allows a choice of a central body. The default is Earth.
Time_Past_Asc_Node	Time	Real Number	The elapsed time since passing the last ascending node crossing based on assumed two-body motion.. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Time_Past_Periapsis	Time	Real Number	The elapsed time since passing the last periapsis crossing based on assumed two-body motion.. The Calc Object allows a choice of a central body. The default is Earth.
True_Anomaly	Angle	Real Number or Text	The angle from the periapsis vector, measured in the orbit plane in the direction of motion, to the position vector. The Calc Object allows a choice of a central body. The default is Earth.

Maneuver
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
DeltaV	Rate	Real Number	Delta-V magnitude integrated along the trajectory path.
DeltaV_Squared	Speed Change Squared	Real Number	Square of DeltaV integrated along path.
Fuel_Density	SmallDensity	Real Number	Density of the fuel.
Fuel_Used	Mass	Real Number	Fuel used since the initial state of the spacecraft.
FuelMass	Mass	Real Number	Fuel mass remaining.
Inertial_DeltaV_Magnitude	Rate	Real Number	The magnitude of accumulated Delta-V integrated in inertial coordinates. Computed by integrating the thrust acceleration over time.
Inertial_DeltaVx	Rate	Real Number	The X component of accumulated Delta-V integrated in inertial coordinates.
Inertial_DeltaVy	Rate	Real Number	The Y component of accumulated Delta-V integrated in inertial coordinates.
Inertial_DeltaVz	Rate	Real Number	The Z component of accumulated Delta-V integrated in inertial coordinates.
MCS_DeltaV	Speed Change	Real Number	Sum of DeltaV magnitude for all maneuvers in MCS.
MCS_DeltaV_Squared	Speed Change Squared	Real Number	Sum of squares of DeltaV magnitude for all maneuvers in MCS.
Specific_Impulse	SpecificImpulse	Real Number	The specific impulse during the maneuver, accounting for all engines, computed using the rocket equation.
Tank_Pressure	Pressure	Real Number	Fuel tank pressure.
Tank_Temperature	Temperature	Real Number	Fuel tank temperature.
Thrust_Vector_X	Force	Real Number	The X component of the total thrust vector. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Thrust_Vector_Y	Force	Real Number	The Y component of the total thrust vector. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Thrust_Vector_Z	Force	Real Number	The Z component of the total thrust vector. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Total_Mass	Mass	Real Number	Total mass (fuel plus dry mass).
Total_Mass_Flow_Rate	Mass Per Time	Real Number	The total mass flow rate, accounting for all engines, during a maneuver.

Math
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Absolute_Value	Date	Real Number or Text	The absolute value of a specified calculation object.
Difference	Time	Real Number	The difference of a specified calculation object. Difference is from the initial value.
Negative	Date	Real Number or Text	The negative of a specified calculation object.

Mean Elems
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Mean_Argument_of_Latitude	Angle	Real Number or Text	The sum of the argument of periapsis and true anomaly, where the angles are computed using Kozai-Izsak mean elements. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Mean_Argument_of_Perigee	Angle	Real Number or Text	The angle from the ascending node to the periapsis vector measured in the orbit plane in the direction of the object's motion. The periapsis vector locates the closest point of the orbit. For a circular orbit, the value is defined to be zero (i.e., periapsis at the ascending node). The ascending node and periapsis vector are computed using Kozai-Izsak mean elements. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Mean_Eccentricity	Unitless	Real Number	A measure of the shape of the orbit. Values <1 indicate an ellipse (where zero is a circular orbit) and values >1 indicate a hyperbola. The value is computed using Kozai-Izsak mean elements. The Calc Object allows a choice of a central body. The default is Earth.
Mean_Inclination	Angle	Real Number or Text	The angle between the orbit plane and the XY plane of the coordinate system, where the orbit angular momentum vector is perpendicular to the orbit plane. The orbit angular momentum vector is computed using Kozai-Izsak mean elements. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Mean_Mean_Anomaly	Angle	Real Number or Text	A measure of the time past periapsis passing, expressed as an angle. The periapsis direction is computed using Kozai-Izsak mean elements. The Calc Object allows a choice of a central body. The default is Earth.
Mean_Orbit_Period	Time	Real Number	Time required for a complete revolution as computed from the mean semi-major axis length, computed using Kozai-Izsak mean elements. The Calc Object allows a choice of a central body. The default is Earth.
Mean_RAAN	Angle	Real Number or Text	The angle in the XY plane from the X axis to the ascending node, measured in a right-handed sense about the Z axis. in the equatorial plane. For equatorial orbits, the ascending node is defined to be directed along the positive X axis, and thus the value is 0.0. The ascending node vector is computed using Kozai-Izsak mean elements. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Mean_Semimajor_Axis	Distance	Real Number	A measure of the size of the orbit. Orbits with eccentricity <1 are ellipses, with major and minor axes identifying the symmetry axes of the ellipse, the major axis being the longer one. The value is half the length of the major axis. The value is computed using Kozai-Izsak mean elements. The Calc Object allows a choice of a central body. The default is Earth.
Mean_True_Anomaly	Angle	Real Number or Text	The angle from the periapsis vector, measured in the orbit plane in the direction of motion, to the position vector. The periapsis vector and position vector are computed using Kozai-Izsak mean elements. The Calc Object allows a choice of a central body. The default is Earth.

MultiBody
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
BDotR	Distance	Real Number	Dot product of B-Plane vectors B and R. B-vector is defined as the intersection of the B-plane and the trajectory plane, starting on the targeted central body and ending at the spot where the incoming asymptote crosses the B-plane. R is one of the axes of the B-plane.
BDotT	Distance	Real Number	Dot product of B-Plane vectors B and T. B-vector is defined as the intersection of the B-plane and the trajectory plane, starting on the targeted central body and ending at the spot where the incoming asymptote crosses the B-plane. T is one of the axes of the B-plane.
BMagnitude	Distance	Real Number	Magnitude of the B-plane B-vector. B-vector is defined as the intersection of the B-plane and the trajectory plane, starting on the targeted central body and ending at the spot where the incoming asymptote crosses the B-plane.
BTheta	Angle	Real Number or Text	B-Plane theta angle is the angle between the B-vector and the T-axis of the B-plane.
Delta_Declination	Angle	Real Number or Text	Delta Declination is the difference between the declination of the target body and that of the satellite with respect to the target body's parent body.
Delta_Right_Asc	Angle	Real Number or Text	Delta Right Ascension is the difference between the right ascension of the target body and that of the satellite. The right ascension is measured with respect to the target body's parent body, in the parent body's inertial coordinate system.
JacobiConstant	Unitless	Real Number	The single integral of the motion of the circular restricted three-body problem. Requires a valid Astrogator CR3BP propagated ephemeris for correct evaluation.

Other Orbit
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Apparent_Solar_Time	Angle	Real Number or Text	Apparent solar time expressed as an angle. The Calc Object allows a choice of a central body. The default is Earth.
Beta_Angle	Angle	Real Number or Text	The angle between the orbit plane and the apparent sun direction. The Calc Object allows a choice of a central body. The default is Earth.
Earth_Mean_Local_Time_of_Ascending_Node	Angle	Real Number or Text	The Mean Solar (Local) Time of the instantaneously evaluated ascending node. The ascending node is computed by converting the osculating right ascension of the ascending nodes to its equivalent longitude of ascending node. This value is then used to compute the associated instantaneous Mean Solar Time. The resulting evolution is a slowly varying smooth function between the nodes that matches the Mean Solar Time at the ascending node. The value is computed as an angle with units of degrees by default with 0/360 degrees being directly opposite the Mean Sun in shadow and 180 degrees aligned with the Mean Sun in light. Units of HMS for the angle are also available.
Earth_Mean_Solar_Time	Angle	Real Number or Text	Apparent solar time modified for earth's equation of time, expressed as an angle. The Calc Object allows a choice of a central body. The default is Earth.
Local_Apparent_Solar_Longitude	Angle	Real Number or Text	Apparent solar longitude minus vehicle longitude. The Calc Object allows a choice of a central body. The default is Earth.
Longitude_of_Periapsis	Angle	Real Number or Text	The sum of the right ascension of the ascending node and the argument of periapsis. The Calc Object allows a choice of element type (Osculating elements, Kozai-Izsak Mean elements, Brouwer-Lyddane Mean elements using only short period terms, and Brouwer-Lyddane Mean elements using both short and long period terms). The default is osculating. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Orbit_State_Value	Date	Real Number or Text	Computes the value of the specified Calc Object given the specified input values of position and velocity.
SignedEccentricity	Unitless	Real Number	The eccentricity multiplied by either 1.0 or -1.0. The value is positive if the mean anomaly is within pi/2 radians of the periapsis, else it is negative. The Calc Object allows a choice of element type (Osculating elements, Kozai-Izsak Mean elements, Brouwer-Lyddane Mean elements using only short period terms, and Brouwer-Lyddane Mean elements using both short and long period terms). The default is osculating.
SignedInclination	Angle	Real Number or Text	The inclination multiplied by either 1.0 or -1.0. The value is positive if the argument of latitude is within pi/2 radians of the ascending node, else it is negative. The Calc Object allows a choice of element type (Osculating elements, Kozai-Izsak Mean elements, Brouwer-Lyddane Mean elements using only short period terms, and Brouwer-Lyddane Mean elements using both short and long period terms). The default is osculating.
True_Longitude	Angle	Real Number or Text	The sum of the right ascension of the ascending node, the argument of periapsis, and the true anomaly. The Calc Object allows a choice of element type (Osculating elements, Kozai-Izsak Mean elements, Brouwer-Lyddane Mean elements using only short period terms, and Brouwer-Lyddane Mean elements using both short and long period terms). The default is osculating. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.

Power
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Power	Power	Real Number	The power generated by a power source. The source can be solar panels, internal, or processed.

Relative Motion
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
CrossTrack	Distance	Real Number	The cross-track component of the relative position vector.
CrossTrackRate	Rate	Real Number	The cross-track component of the relative velocity vector as observed in the RIC rotating frame.
InTrack	Distance	Real Number	The in-track component of the relative position vector.
InTrackRate	Rate	Real Number	The in-track component of the relative velocity vector as observed in the RIC rotating frame.
Normal	Distance	Real Number	The normal component of the relative position vector.
NormalRate	Rate	Real Number	The normal component of the relative velocity vector as observed in the NTC rotating frame.
Radial	Distance	Real Number	The radial component of the relative position vector.
RadialRate	Rate	Real Number	The radial component of the relative velocity vector as observed in the RIC rotating frame.
Range	Distance	Real Number	The range (i.e., distance between the primary and secondary object) at the given time.
RangeRate	Rate	Real Number	The rate of change of the magnitude of the relative position vector.
RICAzimuth	Angle	Real Number or Text	The angle measured in the plane formed by the in-track and cross-track directions, positive from the In-Track direction toward the Cross-Track direction.
RICAzimuthRate	AngleRate	Real Number	The rate of change of the RIC azimuth.
RICElevation	Angle	Real Number or Text	The angle measured perpendicular to the plane formed by the in-track and cross-track directions, positive toward the Radial direction.
RICElevationRate	AngleRate	Real Number	The rate of change of the RIC elevation.
Tangential	Distance	Real Number	The tangential component of the relative position vector.
TangentialRate	Rate	Real Number	The tangential component of the relative velocity vector as observed in the NTC rotating frame.
TimeDifference	Time	Real Number	Alternative measure for in-track position difference, computed as duration. The duration is computed by dividing the in-track component of the relative position vector by the inertial velocity of the primary object.

SEET
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
DamageFlux	Flux	Real Number	The total impact flux that cause damage, from all meteoroid particulates, found as a simple sum of the damaging impact flux of all particulates.
DamageMassFlux	MassFlux	Real Number	The total impact mass flux that cause damage, from all meteoroid particulates, found as the integral of the damaging particle impact flux distribution with respect to mass.
GeoMagFieldDipoleL	Unitless	Real Number	The L value for the field line passing through the vehicle's location computed using the dipole approximation to the magnetic field.
GeoMagFieldFieldLineSeparation	Angle	Real Number or Text	The centric angle between the north footprint of the field line containing the vehicle's location and the north footprint of the field line containing the target's location. The north footprint is the point of intersection of the field line with the earth's surface north of the magnetic equator. If either north footprint is not defined, then the south footprint is used.
ImpactFlux	Flux	Real Number	The total impact flux from all meteoroid particulates, found as a simple sum of the impact flux of all particulates.
ImpactMassFlux	MassFlux	Real Number	The total impact mass flux from all meteoroid particulates, found as the integral of the particle impact flux distribution with respect to mass.
SAAFluxIntensity	FluxIntensity	Real Number	The SAA flux intensity at the vehicle's location for the vehicle's channel specification.
VehicleTemperature	Temperature	Real Number	Vehicle temperature, computed assuming thermal equilibrium.

Scalar
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Scalar	Unitless	Real Number	Scalar calculation component.

Scripts
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
CustomFunctionCalcObject	Unitless	Real Number	Calculation produced by a Custom Function.
JScript	Unitless	Real Number	JScript.
Matlab	Unitless	Real Number	Calculation produced by a MATLAB inline function.
Perl	Unitless	Real Number	Calculation produced by a Perl inline function.
VBScript	Unitless	Real Number	Calculation produced by a VBScript inline function.

Spacecraft Properties
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Cd	Unitless	Real Number	The dimensionless drag coefficient associated with the drag area.
Cr	Unitless	Real Number	The solar radiation pressure coefficient.
DragArea	Small Area	Real Number	The area used in the computation of atmospheric drag.
RadPressureArea	Small Area	Real Number	The area used in radiation pressure computations.
RadPressureCoefficient	Unitless	Real Number	The radiation pressure coefficient.
SRPArea	Small Area	Real Number	The area used in Solar radiation pressure computations.

Spherical Elems
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Cosine_of_Vertical_FPA	Unitless	Real Number	The dot product of the unit position and unit velocity vectors. The Calc Object allows a choice of a central body. The default is Earth.
Declination	Angle	Real Number or Text	The signed angle measured from the XY plane to the position vector, where positive angles are used for locations above the XY plane, and negative for those below.
Declination_Rate	AngleRate	Real Number	The rate of change in the declination.
Flight_Path_Angle	Angle	Real Number or Text	The angle between the position and velocity vectors. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
R_Mag	Distance	Real Number	The magnitude of the position vector (i.e. the radius vector). The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Right_Asc	Angle	Real Number or Text	The signed angle measured from the X axis to the projection of the position vector into the XY plane. The angle increases in the direction found by the right hand rule about the Z axis. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Right_Asc_Rate	AngleRate	Real Number	Right Ascension Rate.
V_Mag	Rate	Real Number	The magnitude of the velocity vector, as observed in the coordinate system. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Velocity_Azimuth	Angle	Real Number or Text	The angle, measured in the plane perpendicular to the position vector, between the local north direction and the projection of the velocity vector onto that plane, measured as positive moving toward local east. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.

Target Vector
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
C3_Energy	Rate Squared	Real Number	An energy defined as -(mu/semi-major-axis). The Calc Object allows a choice of a central body. The default is Earth.
Incoming_Asymptote_Dec	Angle	Real Number or Text	Declination of incoming asymptote or apsides. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Incoming_Asymptote_RA	Angle	Real Number or Text	Right Ascension of incoming asymptote or apsides. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Incoming_Vel_Az_at_Periapsis	Angle	Real Number or Text	Velocity azimuth at periapsis for incoming trajectory. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Outgoing_Asymptote_Dec	Angle	Real Number or Text	Declination of outgoing asymptote or apsides. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Outgoing_Asymptote_RA	Angle	Real Number or Text	Right Ascension of outgoing asymptote or apsides. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Outgoing_Vel_Az_at_Periapsis	Angle	Real Number or Text	Velocity azimuth at periapsis for outgoing trajectory. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.

Time
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Duration	Time	Real Number	The duration of the event.
Number_of_Revolutions	Unitless	Real Number	The fraction of the osculating or mean orbit period since the startTime (not always monotonic).

UserValues
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
User_value	Unitless	Real Number	The value of a user variable.

Vector
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Angle	Angle	Real Number or Text	The value of the angle at the given time.
Angle_Between_Vectors	Angle	Real Number or Text	The angle between two specified vectors.
Dot_Product	Unitless	Real Number	The dot Product of two specified vectors.
Vector_Dec	Angle	Real Number or Text	The declination of the specified vector.
Vector_Mag	Unitless	Real Number	The magnitude of the specified vector.
Vector_RA	Angle	Real Number or Text	The right ascension of the specified vector.
Vector_X	Unitless	Real Number	The X component of the specified vector.
Vector_Y	Unitless	Real Number	The Y component of the specified vector.
Vector_Z	Unitless	Real Number	The Z component of the specified vector.

Segment Data
Name	Dimension	Type	Description
Time	Date	Real Number or Text	Time.
Segment Name	Unitless	Text	The name of the segment that produced ephemeris over this interval.
Segment Type	Unitless	Text	The type of the segment.