Satellite

Available Data Providers

Name	Description
Active Constraints	Lists the constraints that are considered when computing access for the object.
All Constraints	Descriptions of all constraints available for this object and its parent object.
Angles	Reports angle and its time rate of change rate. Angle must be defined in the Vector Geometry Tool.
Articulation	Information concerning model articulations for this object.
Astrogator Accel Hist	Generates an acceleration history file for each finite maneuver segment of an Astrogator satellite. The file data consists of five columns: Time, ACCELx, ACCELy, ACCELz, and MassChangeRate. The format of the file is compatible for ingestion by ODTK. The report itself contains a summary of files that STK generated. The name of each file reflects the maneuver segment name and the name of any associated target sequence. STK places the files in a folder called AccelHist within the scenario directory. STK creates an additional file, AllAccelHist.accelhist, that gather all the acceleration data of the separate files.
Astrogator Log	The targeter log file. This data provider requires that the Satellite use the Astrogator propagator.
Astrogator MCS Ephemeris Segments	Shows which Astrogator segment produced each interval of ephemeris. This data provider requires that the Satellite use the Astrogator propagator.
Astrogator Maneuver Ephemeris Block Final	Calc Object values corresponding to the final state of each Astrogator maneuver segment. Each Calc Object contained in the Component Browser is available for use, including user defined Calc Objects. The Calc Objects listed here are representative. This data provider requires that the Satellite use the Astrogator propagator.
Astrogator Maneuver Ephemeris Block History	Calc Object values, as a function of time, during each Astrogator maneuver segment. Each Calc Object contained in the Component Browser is available for use, including user defined Calc Objects. The Calc Objects listed here are representative.
Astrogator Maneuver Ephemeris Block Initial	Calc Object values corresponding to the initial state of each Astrogator maneuver segment. Each Calc Object contained in the Component Browser is available for use, including user defined Calc Objects. The Calc Objects listed here are representative. This data provider requires that the Satellite use the Astrogator propagator.
Astrogator Pass Data	Calc Object values at the end of each pass break. Each Calc Object contained in the Component Browser is available for use, including user defined Calc Objects. The Calc Objects listed here are representative.
Astrogator Script Summary	The results from the last run of a script created using the Scripting Tool.
Astrogator Terminal Stopping Condition	Reports information about the stopping condition that stopped the Astrogator MCS propagation.
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.
Attitude Quaternions	The attitude quaternion and angular velocity of the vehicle's body axes computed with respect to the vehicle's central body inertial coordinate system. The quaternion components q1, q2, and q3 are the vector components of the quaternion; q4 is the scalar part. The angular velocity is computed as observed from the inertial frame but resolved into body axes components.
Attitude Segment Description	General information about the different attitude segments that define the satellite's attitude over time.
Attitude Segment ECF Quaternions	The attitude quaternion and angular velocity of the vehicle's body axes computed with respect to the vehicle's central body fixed coordinate system. Additionally, provides information on the attitude segment being used at the given time. The quaternion components q1, q2, and q3 are the vector components of the quaternion; q4 is the scalar part. The angular velocity is computed as observed from the fixed frame and resolved into body components.
Attitude Segment Euler Angles	The attitude of the vehicle expressed using Euler angles. Additionally, provides information on the attitude segment being used at the given time. Euler angles use a sequence of three rotations starting from a reference coordinate frame. The rotations are performed in succession: each rotation is relative to the frame resulting from any previous rotations. The sequence of three rotations is indicated by a integer sequence where the X axis is 1, Y axis is 2, and Z axis is 3. For example, a 313 sequence uses X, then the new Z, and then finally the newest X axis.
Attitude Segment Quaternions	The attitude quaternion and angular velocity of the vehicle's body axes computed with respect to the vehicle's central body inertial coordinate system. Additionally, provides information on the attitude segment being used at the given time. The quaternion components q1, q2, and q3 are the vector components of the quaternion; q4 is the scalar part. The angular velocity is computed as observed from the inertial frame and resolved into body components.
Attitude Segment Schedule	The list of attitude segments describing the attitude for this object. Each segment is valid over its defined interval.
Attitude Segment YPR	The attitude of the vehicle with respect to the vehicle's central body inertial coordinate system, expressed using YPR angles. Additionally, provides information on the attitude segment being used at the given time. Similar to Euler angles, YPR angles specify attitude using three rotations in sequence: a rotation about the reference X axis is called roll (R), a rotation about the reference Y axis is called pitch (P), and a rotation about the reference Z axis is called yaw (Y). Unlike Euler angles, the rotations are not made about axes defined by an earlier rotation: each rotation is made about the reference system's axes. As used in YPR angles, the names yaw, pitch, and roll do *not* refer to the angles normally used in aviation; the terms yaw, pitch, and roll in aviation refer to 321 Euler angles.
Attitude YPR	The attitude of the vehicle with respect to the vehicle's central body inertial coordinate system, expressed using YPR angles. Similar to Euler angles, YPR angles specify attitude using three rotations in sequence: a rotation about the reference X axis is called roll (R), a rotation about the reference Y axis is called pitch (P), and a rotation about the reference Z axis is called yaw (Y). Unlike Euler angles, the rotations are not made about axes defined by an earlier rotation: each rotation is made about the reference system's axes. As used in YPR angles, the names yaw, pitch, and roll do *not* refer to the angles normally used in aviation; the terms yaw, pitch, and roll in aviation refer to 321 Euler angles.
Available Times	The time intervals over which the object is available to participate in access computations.
Axes Choose Axes	Reports the orientation and angular velocity of the selected set of axes relative to a chosen reference set of axes. The selected set of axes can be selected from any axes in the Vector Geometry Tool owned by the object; the reference axes may be chosen from any axes in the Vector Geometry Tool.
Beta Angle	The Beta Angle is the signed angle of the apparent vector to a central body, relative to the orbital plane. The signed angle is positive when the apparent vector is in the direction of the orbit normal. The orbit normal (which is normal to the orbital plane) is parallel to the orbital angular momentum vector, which is defined as the cross-product of the inertial position and velocity vectors. The light time delay is actually computed between the central body used to compute the beta angle and the vehicle's central body, rather than directly from the object itself.
Body Axes Orientation	Reports the orientation and angular velocity of the Body axes of the object with respect to a selected reference set of axes. The reference set of axes can be selected from any axes in the Vector Geometry Tool owned by the object. Selecting the Body axes as the reference axes results in no orientation difference nor any angular velocity between the Body axes and this reference axes.
Body Axes Orientation:YPR 123	Reports the orientation and angular velocity of the Body axes of the object with respect to a selected reference set of axes, where the Yaw, Pitch, and Roll angles are defined using the YPR 123 sequence. The reference set of axes can be selected from any axes in the Vector Geometry Tool owned by the object. Similar to Euler angles, YPR angles specify attitude using three rotations in sequence: a rotation about the reference X axis is called roll (R), a rotation about the reference Y axis is called pitch (P), and a rotation about the reference Z axis is called yaw (Y). Unlike Euler angles, the rotations are not made about axes defined by an earlier rotation: each rotation is made about the reference system's axes. As used in YPR angles, the names yaw, pitch, and roll do *not* refer to the angles normally used in aviation; the terms yaw, pitch, and roll in aviation refer to 321 Euler angles. Selecting the Body axes as the reference axes results in no orientation difference nor any angular velocity between the Body axes and this reference axes.
Body Axes Orientation:YPR 132	Reports the orientation and angular velocity of the Body axes of the object with respect to a selected reference set of axes, where the Yaw, Pitch, and Roll angles are defined using the YPR 132 sequence. The reference set of axes can be selected from any axes in the Vector Geometry Tool owned by the object. Similar to Euler angles, YPR angles specify attitude using three rotations in sequence: a rotation about the reference X axis is called roll (R), a rotation about the reference Z axis is called yaw (Y), and a rotation about the reference Y axis is called pitch (P). Unlike Euler angles, the rotations are not made about axes defined by an earlier rotation: each rotation is made about the reference system's axes. As used in YPR angles, the names yaw, pitch, and roll do *not* refer to the angles normally used in aviation; the terms yaw, pitch, and roll in aviation refer to 321 Euler angles. Selecting the Body axes as the reference axes results in no orientation difference nor any angular velocity between the Body axes and this reference axes.
Body Axes Orientation:YPR 213	Reports the orientation and angular velocity of the Body axes of the object with respect to a selected reference set of axes, where the Yaw, Pitch, and Roll angles are defined using the YPR 213 sequence. The reference set of axes can be selected from any axes in the Vector Geometry Tool owned by the object. Similar to Euler angles, YPR angles specify attitude using three rotations in sequence: a rotation about the reference Y axis is called pitch (P), a rotation about the reference X axis is called roll (R), and a rotation about the reference Z axis is called yaw (Y). Unlike Euler angles, the rotations are not made about axes defined by an earlier rotation: each rotation is made about the reference system's axes. As used in YPR angles, the names yaw, pitch, and roll do *not* refer to the angles normally used in aviation; the terms yaw, pitch, and roll in aviation refer to 321 Euler angles. Selecting the Body axes as the reference axes results in no orientation difference nor any angular velocity between the Body axes and this reference axes.
Body Axes Orientation:YPR 231	Reports the orientation and angular velocity of the Body axes of the object with respect to a selected reference set of axes, where the Yaw, Pitch, and Roll angles are defined using the YPR 231 sequence. The reference set of axes can be selected from any axes in the Vector Geometry Tool owned by the object. Similar to Euler angles, YPR angles specify attitude using three rotations in sequence: a rotation about the reference Y axis is called pitch (P), a rotation about the reference Z axis is called yaw (Y), and a rotation about the reference X axis is called roll (R). Unlike Euler angles, the rotations are not made about axes defined by an earlier rotation: each rotation is made about the reference system's axes. As used in YPR angles, the names yaw, pitch, and roll do *not* refer to the angles normally used in aviation; the terms yaw, pitch, and roll in aviation refer to 321 Euler angles. Selecting the Body axes as the reference axes results in no orientation difference nor any angular velocity between the Body axes and this reference axes.
Body Axes Orientation:YPR 312	Reports the orientation and angular velocity of the Body axes of the object with respect to a selected reference set of axes, where the Yaw, Pitch, and Roll angles are defined using the YPR 312 sequence. The reference set of axes can be selected from any axes in the Vector Geometry Tool owned by the object. Similar to Euler angles, YPR angles specify attitude using three rotations in sequence: a rotation about the reference Z axis is called yaw (Y), a rotation about the reference X axis is called roll (R), and a rotation about the reference Y axis is called pitch (P). Unlike Euler angles, the rotations are not made about axes defined by an earlier rotation: each rotation is made about the reference system's axes. As used in YPR angles, the names yaw, pitch, and roll do *not* refer to the angles normally used in aviation; the terms yaw, pitch, and roll in aviation refer to 321 Euler angles. Selecting the Body axes as the reference axes results in no orientation difference nor any angular velocity between the Body axes and this reference axes.
Body Axes Orientation:YPR 321	Reports the orientation and angular velocity of the Body axes of the object with respect to a selected reference set of axes, where the Yaw, Pitch, and Roll angles are defined using the YPR 321 sequence. The reference set of axes can be selected from any axes in the Vector Geometry Tool owned by the object. Similar to Euler angles, YPR angles specify attitude using three rotations in sequence: a rotation about the reference Z axis is called yaw (Y), a rotation about the reference Y axis is called pitch (P), and a rotation about the reference X axis is called roll (R). Unlike Euler angles, the rotations are not made about axes defined by an earlier rotation: each rotation is made about the reference system's axes. As used in YPR angles, the names yaw, pitch, and roll do *not* refer to the angles normally used in aviation; the terms yaw, pitch, and roll in aviation refer to 321 Euler angles. Selecting the Body axes as the reference axes results in no orientation difference nor any angular velocity between the Body axes and this reference axes.
Brouwer-Lyd Mean Long	These are the Mean Elements considering both the short-period and long-period terms from the Brouwer-Lyddane theory. Included perturbations are the J2, J3, J4, and J5 zonal harmonics, including terms involving J2^2. These elements are not time averages of the osculating values but are the results of a specific averaging procedure defined by the theory. In the Brouwer theory, a variation of Delaunay elements are averaged and are therefore the actual mean elements. Other "mean" elements are derived using of osculating orbit element conversions on the computed mean elements. Mean elements are computed in the selected reference frames by first transforming the osculating state to the selected frame and then applying the mean element conversion.
Brouwer-Lyd Mean Short	These are the Mean Elements considering just the short-period terms from the Brouwer-Lyddane theory, which only include J2 zonal harmonics perturbations. These elements are not time averages of the osculating values but are the results of a specific averaging procedure defined by the theory. In the Brouwer theory, a variation of Delaunay elements are averaged and are therefore the actual mean elements. Other "mean" elements are derived using of osculating orbit element conversions on the computed mean elements. Mean elements are computed in the selected reference frames by first transforming the osculating state to the selected frame and then applying the mean element conversion.
Cartesian Acceleration	The acceleration of the object as observed from the requested coordinate system, expressed in Cartesian components of that system, as a function of time.
Cartesian Position	The position of the object with respect to the object's central body, as observed from the requested coordinate system, expressed in Cartesian components as a function of time.
Cartesian Velocity	The velocity of the object with respect to the object's central body, as observed from the requested coordinate system, expressed in Cartesian components of that system, as a function of time.
Classical Elements	Classical osculating orbital elements, sometimes referred to as Keplerian elements, computed using ephemeris with respect to the object's central body, as observed from the requested coordinate system, as a function of time.
Close Approach Compute Results	Close Approach analysis results summary.
Close Approach Definition	Parameter settings for the Close Approach Tool.
Close Approach Filter Settings	Filter settings for the Close Approach Tool.
CloseApproach	The results produced by using the close approach tool, identifying vehicles that pass within a specified minimum range of the object. Also reports information concerning launch window blackout intervals when that capability is used.
CloseApproachByMinRange	The results produced by using the close approach tool, identifying vehicles that pass within a specified minimum range of the object. The data is sorted according to the minimum range. Also reports information concerning launch window blackout intervals when that capability is used.
CloseApproachBySSC	The results produced by using the close approach tool, identifying vehicles that pass within a specified minimum range of the object. The data is sorted according to the SSC number of the secondary. Also reports information concerning launch window blackout intervals when that capability is used.
Collection of Interval Lists	A time component that produces a collection of related interval lists.
Condition	Reports the value of selected scalar conditions. The scalar condition must be defined in the Calculation Tool and owned by the object.
Condition Set	Defines a set of conditions for when the elapsed time falls within specified time limits.
Configured Constraints	Lists the constraints that are configured, i.e., those that could be used by the object when computing access. Only enabled constraints participate in the access computation; disabled constraints are ignored.
Crdn Available Times	Time intervals for which a Vector Geometry Tool component for the object is available.
Data Provider Detail	Data Provider Detail - hierarchically list the available data providers and all of the included elements.
Data Provider Summary	Data Provider Summary - a list of all available data providers.
DeckAccess	Reports the output from the Deck Access tool. The Deck Access tool allows you to compute access to a set of objects, not currently defined within the STK scenario, from a single object within the scenario.
DeckAccess Data	Geometrical data involving the source and target objects of a DeckAccess computation.
Delaunay Elements	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. The elements are computed using ephemeris with respect to the object's central body, as observed from the requested coordinate system, as a function of time.
ECF Attitude Quaternions	The attitude quaternion and angular velocity of the vehicle's body axes computed with respect to the vehicle's central body fixed coordinate system. The quaternion components q1, q2, and q3 are the vector components of the quaternion; q4 is the scalar part. The angular velocity is computed as observed from the fixed frame and resolved into body components.
Eclipse Definition	The bodies considered when computing eclipse and lighting times.
Eclipse Solar Intensity	Percent of the solar disc visible, along with lighting condition and obstruction body, during eclipses by obstructing bodies.
Eclipse Summary	Provides summary information for each eclipse. Note that the Eclipse Summary data provider reports the start and stop times of penumbra which, if umbra exists, occur before and after umbra, respectively. This means that if the Eclipse Summary is generated in cases when it starts in umbra, then the start of penumbra is reported as "No Data" because it occurred prior to the start of reported data.
Eclipse Times	Generates a listing of all eclipse events. Eclipsing events are start and end of periods of partial lighting (penumbra) and periods of zero lighting (umbra).
Ecliptic Crossings	Times corresponding to the crossing of a vehicle's position through the ecliptic plane (nominally, the plane containing Earth and Sun).
Element Set	The two-line element set (TLE) for an SGP4-propagated satellite.
Ephemeris Diff	The relative ephemeris of the assigned object with respect to the primary object, as observed from the requested coordinate system, expressed in Cartesian components as a function of time. The relative velocity vector is computed as observed in the requested coordinate system, and expressed in components of that frame.
Ephemeris Diff in Curvilinear Coordinates	The relative ephemeris of the assigned object with respect to the primary object, expressed in curvilinear coordinates, as a function of time. It produces three coordinates and their rates (Crossrange, Downrange, and Crosstrack) that are defined relative to the osculating orbit of the reference satellite.
Equinoctial Elements	The position and velocity of the object, as observed from the requested coordinate system, expressed in equinoctial elements as a function of time. Equinoctial elements are a set of orbital elements that are not singular when the eccentricity becomes zero or the orbit is equatorial. Rates of the elements may also be reported. Rates are computed using variation of parameters expressions with the perturbative acceleration which is computed as the total acceleration minus the two body acceleration, expressed in the requested coordinate system. Due to the method of computation, element rates will not be consistent with finite differencing of the element values for cases where the velocity is not the true time derivative of the acceleration; for this reason, these values will not be reported for the J2, J4 and SGP4 propagators.
Euler Angles	The attitude of the vehicle (i.e., the rotation between the vehicle's body axes and the vehicle' central body's inertial frame) expressed using Euler angles. Euler angles use a sequence of three rotations starting from a reference coordinate frame. The rotations are performed in succession: each rotation is relative to the frame resulting from any previous rotations. The sequence of three rotations is indicated by a integer sequence where the X axis is 1, Y axis is 2, and Z axis is 3. For example, a 313 sequence uses Z, then the new X, and then finally the newest Z axis.
Geo Station Keeping Elements	Orbital elements useful when describing motion of geosynchronous satellites, computed with respect to the Earth TrueOfDate system, as a function of time. The literature contains a variety of metrics that have been found useful for describing and maintaining geosynchronous orbits. The elements are categorized as: Angle representing location in orbit Inertial angles (measured from Earth TrueOfDate X-axis) Mean Longitude, True Longitude, True Right Ascension, Mean Right Ascension Geodetic angles (measured from Earth Fixed X-axis) Geodetic Mean Longitude, Geodetic True Longitude, Geodetic True Longitude At Time Of Perigee, Geodetic Mean Right Ascension, Geodetic Longitude Drift in orbit (as compared to ideal motion whose rate is the sidereal rotation rate of the Earth (360.985612287742 deg/day)) Mean Drift Rate (with dimension AngleRate) Drift Rate factor (non-dimensional) These values are provided in two forms: (i) based on two-body motion; and (ii) incorporating the effects of Earth oblateness represented by J2. Eccentricity vector The location of the eccentricity vector within the orbit plane. Defined in the same manner as equinoctial elements h and k. Inclination vector The vector whose direction is the lines of nodes, with magnitude depending on the inclination angle. Different investigators use different magnitudes--several versions of the inclination vector (each with different magnitudes) are provided below. Some investigators (e.g., Soop) use the term 'inclination vector' to actually locate the projection of the unit angular momentum vector in the XY-plane, which is perpendicular to the line of nodes. The UnitAngularMomentum vector is provided separately below. Reference: Handbook of Geostationary Orbits, E. M. Soop, 1994, DOI 10.1007/978-94-015-8352-7.
Gravity Model	The name of the gravity model that is currently in use by the propagator. It includes the values of the standard gravitational parameter mu, and the J2 term in the gravity field.
Ground Ellipse Definition	Ground Ellipse Definition.
Heading	Heading information relative to the object's central body fixed coordinate system.
IIRV User Input	Data included in the Improved Inter-Range Vector (IIRV) standard message.
Interval	A time component that produces a single interval of time.
Interval List	A time component that produces an ordered list of time intervals.
Kozai-Izsak Mean	Mean Elements considering just the short period terms from the Kozai-Izsak theory. This theory removes only the first order J2 short period effects. These elements are not time averages of the osculating values, but are the results of a specific averaging procedure defined by the theory. The mean element theory is derived using a specific set of elements, other "mean" elements are derived using of osculating orbit element conversions on the computed mean elements. Mean elements are computed in the selected reference frames by first transforming the osculating state to the selected frame then applying the mean element conversion.
LLA State	The ephemeris of the object, expressed in LLA elements, as a function of time. The coordinate system is the Fixed frame of the object's central body.
LLR State	The ephemeris of the object with respect to the object's central body, as observed from the requested coordinate system, expressed in LLR elements as a function of time.
LOP Mean Elements	The ephemeris of the object, as observed from the requested coordinate system, expressed in mean orbital elements as a function of time. Mean orbital elements are calculated as used by the Long-Term Orbit Propagator (LOP). The vehicle must use the LOP propagator to produce this report.
Launch Window Definition	Parameter settings for the Launch Window Analysis Tool.
Lifetime	Orbit information produced using the Lifetime Tool. Each grid point represents one calculation, where the number of orbits per calculation is set by the lifetime tool settings.
Lighting AER	Angle and range data describing the apparent relative position vector of the Sun.
Lighting Times	Generates a listing of all lighting events. Lighting events are start and end of periods of full lighting (sunlight), partial lighting (penumbra) and periods of zero lighting (umbra). Note that the Lighting Times data provider reports all computed penumbra intervals, which means that if umbra exists, then two penumbra intervals, each with its own start and stop times, is reported--one before and one after the umbra interval. So, if lighting times that start in umbra are generated, then the first reported penumbra interval corresponds to the times that follow after the first umbra, and the penumbra interval prior to the first umbra is not reported.
Lunar Eclipse Solar Intensity	Percent of the solar disc visible, along with lighting condition, during eclipses caused by the obstruction by Earth's moon (i.e., vehicle passing through the shadow of the moon).
MCS Summary	A detailed summary of the Mission Control Sequence (MCS) for an Astrogator satellite. Gives the segment summary report for every segment in the MCS. This includes initial state, final state, maneuver information, and spacecraft configuration information. Only valid for an Astrogator satellite.
Maneuver Summary	A summary of the maneuvers for an Astrogator satellite. Only valid for an Astrogator satellite.
Mass	Satellite mass and moment of inertia information.
Mixed Spherical Elements	The position and velocity of the object, expressed in mixed spherical elements, as a function of time. The position is expressed using LLA elements, with respect to the vehicle's central body fixed coordinate system -- the requested coordinate system is immaterial. The velocity of the object is computed as observed from the requested coordinate system.
Model Area	The area of the object's 3D graphics model, as viewed from a given view direction, as computed by the Area Tool.
Model LOD 0 Articulations	The model's articulation values used for display with a level of detail of 0 (high resolution). This data provider always includes time, but the rest of its content varies depending on the model.
Model LOD 1 Articulations	The model's articulation values used for display with a level of detail of 1 (low resolution). This data provider always includes time, but the rest of its content varies depending on the model.
Modified Equinoctial Elements	Modified Equinoctial elements differ from the Equinoctial elements by using the the semilatus rectum (usually denoted by p) instead of the semimajor axis (a) and by using the the true longitude instead of the mean longitude. The elements are valid for elliptic, parabolic, and hyperbolic orbits. Due to the method of computation, element rates will not be consistent with finite differencing of the element values for cases where the velocity is not the true time derivative of the acceleration; for this reason, these values will not be reported for the J2, J4 and SGP4 propagators.
Moon AER	Angle and range data describing the apparent relative position vector of the Moon.
Moon Vector	The apparent position of the Moon with respect to the object as observed from the requested coordinate system, expressed in Cartesian components, as a function of time. The light time delay is actually computed between the Moon and the object's central body, rather than directly from the object itself.
Parameter Set: Attitude	The Attitude parameter set defines orientation of one set of Axes from VGT relative to another. This parameter includes the following sub-sets: Quaternion, Euler, DCM and AngleAxis. Quaternion includes four quaternion elements Q1, Q2, Q3, Q4. Euler includes all 12 sequences where within each there are three angles: A, B, C. DCM includes all nine elements of the direction cosine matrix; e.g., XX, XY, etc. AngleAxis includes X, Y, Z components of the unit axis of rotation and RotationAngle.
Parameter Set: Cartographic Trajectory	Cartographic Trajectory Parameter Set contains calculations that relate a specified point to the selected central body shape. This parameter set contains the following sub-sets: Cartesian, Centric and Detic. Cartesian includes X, Y, Z and Radius. Centric includes LLR with Latitude, Longitude and Radius, and SubPoint with Cartesian elements. Detic includes several LLA with Latitude, Longitude, Altitude, SurfaceNormal with Cartesian elements without Radius, and SubPoint with Cartesian elements. It also includes Terrain and MSL both with LLA and SubPoint subsets of their own.
Parameter Set: Orbit	The Orbit parameter set defines orbital element sets for a Point from VGT orbiting the specified Central Body in the specified coordinate System. Element sets include: Cartesian, Classical, Delaunay, Spherical and Equinoctial (Posigrade and Retrograde).
Parameter Set: Trajectory	The Trajectory parameter set defines the position of a specified Point from VGT with respect to the reference System. This parameter set includes the following sub-sets: Cartesian, Cylindrical and Spherical. Cartesian includes X, Y, Z and Radius. Cylindrical includes Azimuth, Height, Radius. Spherical includes Azimuth, Elevation, CoElevation, and Radius.
Parameter Set: Vector	The Vector parameter defines the position of one access object relative to the other. The position data can be reported in multiple different reference frames.
Pass Event Times	Times corresponding to certain orbital events. These event times can also be reported using the Passes data provider. However, the Passes data provider only reports one event per pass. It can be the case that two events occur on one pass, while none occurs on the next pass [e.g., when the pass break occurs very close to apogee]. In such a case, an event will not be reported by that data provider. The Pass Event Times data provider, however, will report out all events irrespective of the pass to which the event belongs.
Passes	Data reported for each pass of the satellite's orbit. The time of ascending node occurs twice per pass for a full pass when passes are defined by ascending node. When that occurs, the reported value of the time of ascending node for a pass will be the start time of the pass. For a partial pass, the time of ascending node will occur only once, but it may occur at either the start time or the stop time of the pass. Thus, the time of ascending node for the first reported pass may exactly match the time of ascending node for the second pass if the first pass is a partial pass and passes are defined by ascending node.
Planes Choose System	Reports the selected plane and its velocity in a specified reference coordinate system. Both plane and coordinate system must be defined in the Vector Geometry Tool.
Planes(Fixed)	Reports the selected plane and its velocity in the object's central body fixed coordinate system. The plane must be defined in the Vector Geometry Tool.
Planes(ICRF)	Reports the selected plane and its velocity in the object's central body ICRF coordinate system. The plane must be defined in the Vector Geometry Tool.
Planes(Inertial)	Reports the selected plane and its velocity in the object's central body inertial coordinate system. The plane must be defined in the Vector Geometry Tool.
Planes(J2000)	Reports the selected plane and its velocity in the object's central body J2000 coordinate system. The plane must be defined in the Vector Geometry Tool.
Pointing Covariance (Projection)	Projection of the equal probability density ellipsoid defined by the pointing covariance matrix onto the plane perpendicular to the mean pointing direction. The data requires position covariance to be defined for the object and/or its target.
Points Choose Plane	Reports projection of the selected point and its velocity on a specified reference plane. Both point and plane must be defined in the Vector Geometry Tool.
Points Choose System	Reports the selected point and its velocity in a specified reference coordinate system. Both point and coordinate system must be defined in the Vector Geometry Tool.
Points(Fixed)	Reports the selected point and its velocity in the object's central body fixed coordinate system. The point must be defined in the Vector Geometry Tool.
Points(ICRF)	Reports the selected point and its velocity in the object's central body ICRF coordinate system. The point must be defined in the Vector Geometry Tool.
Points(Inertial)	Reports the selected point and its velocity in the object's central body inertial coordinate system. The point must be defined in the Vector Geometry Tool.
Points(J2000)	Reports the selected point and its velocity in the object's central body J2000 coordinate system. The point must be defined in the Vector Geometry Tool.
Pos Vel Projected Covariance	Provides data about position/velocity covariance matrix relative to selected set of axes. The covariance is transformed into the requested reference frame using a 6x6 block diagonal transformation matrix consisting of two 3x3 coordinate transformation matrices along the diagonal. The result of this transformation is that the original covariance is simply expressed relative to the new axes and the effects of the rotation of the axes are ignored. Any set of axes defined in the Vector Geometry Tool is available for use, including user defined sets. The data requires position/velocity covariance to be defined for the object.
Pos Vel Rotated Covariance	Provides data about position/velocity covariance matrix relative to selected set of axes. The covariance is transformed into the requested reference frame using a 6x6 transformation matrix consisting of two 3x3 coordinate transformation matrices along the diagonal and the skew-symmetric 3x3 matrix representing the angular velocity between the axes in the lower left. The result of this transformation is that the original covariance is re-expressed relative to the new axes including the effects of the rotation of the axes. The resultant covariance matrix represents the uncertainty of the position/velocity expressed in the new axes. Any set of axes defined in the Vector Geometry Tool is available for use, including user defined sets. The data requires position/velocity covariance to be defined for the object.
Position Covariance	Reports data about position covariance matrix including orientation of its principal axes relative to selected set of axes. Any set of axes defined in the Vector Geometry Tool is available for use, including user defined sets. The data requires position covariance to be defined for the object. Note: This data provider does not support interpolation of the position/velocity covariance matrices. Output is limited to the times of the stored ephemeris points.
Position Covariance Choose Axes	Reports data about the position covariance matrix, including orientation of its principal axes relative to the chosen set of axes and dimensions of the associated sigma-scaled, equal probability density ellipsoid. Any set of axes defined in the Vector Geometry Tool is available for use, including user-defined sets. The data requires position covariance to be defined for the object.
Position Covariance CrossSection	Cross-section of the equal probability density ellipsoid defined by the position covariance matrix with the specified plane. Any plane defined in the Vector Geometry Tool is available for use, including user defined planes. The data requires position covariance to be defined for the object.
Position Covariance CrossSection Choose Plane	Cross-section of the equal probability density ellipsoid defined by the position covariance matrix with the specified plane. Any plane defined in the Vector Geometry Tool is available for use, including user defined planes. The data requires position covariance to be defined for the object.
Position Covariance Projection	Projection of the equal probability density ellipsoid defined by the position covariance matrix onto the specified plane. Any plane defined in the Vector Geometry Tool is available for use, including user defined planes. The data requires position covariance to be defined for the object.
Position Covariance Projection Choose Plane	Projection of the equal probability density ellipsoid defined by the position covariance matrix onto the specified plane. Any plane defined in the Vector Geometry Tool is available for use, including user defined planes. The data requires position covariance to be defined for the object.
Position Covariance in Axes	Reports data about position covariance matrix including orientation of its principal axes relative to selected set of axes and dimensions of the associated sigma scaled equal probability density ellipsoid. Any set of axes defined in the Vector Geometry Tool is available for use, including user defined sets. The data requires position covariance to be defined for the object.
Precision Passes	Numbers that indicate the pass and path of the satellites orbit.
Propagator Inputs	Parameters used by the specified propagator to propagate the vehicle.
RIC Coordinates	The relative ephemeris of the assigned object with respect to the primary object, expressed in Cartesian components, as a function of time. 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). If the ephemeris times of the assigned object do not match those of the primary object, then the ephemeris of the assigned object is interpolated to the ephemeris times of the primary object. This can lead to nonzero values reported between primary and assigned objects that should be at the same position.
Relative Motion	The relative ephemeris of the assigned object with respect to the primary object, expressed in Cartesian components, as a function of time. 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). If the ephemeris times of the assigned object do not match those of the primary object, then the ephemeris of the assigned object is interpolated to the ephemeris times of the primary object. This can lead to nonzero values reported between primary and assigned objects that should be at the same position.
SEET Debris Flux	Computes the total debris flux of all particulates. The debris model is valid only for near-circular orbits at altitudes between roughly 300 km and 2250 km. Because the model was created using averages over long time periods (e.g., many months or a few years), it is not appropriate to output a flux value at any given time - there really is no information in different evaluations of the model over short time spans. Hence, the debris flux is evaluated at just 1 sample per requested time interval, at the midpoint of the interval. Valid for vehicles whose central body is earth.
SEET GCR Differential Fluence by Energy	Computes the Galactic Cosmic Radiation (GCR) fluence as an differential fluence with respect to particle energy. The data items available for this data provider depend on the GCR model, atomic number, sample time period, and potentially other GCR model dependent parameters.
SEET GCR Differential Flux by Energy	Computes the Galactic Cosmic Radiation (GCR) differential flux with respect to particle energy. The data items available for this data provider depend on the GCR model, atomic number, and potentially other GCR model dependent parameters.
SEET GCR Integral Fluence by Energy	Computes the Galactic Cosmic Radiation (GCR) fluence as an integrated distribution with respect to particle energy. The data items available for this data provider depend on the GCR model, atomic number, sample time period, and potentially other GCR model dependent parameters.
SEET GCR Integral Flux by Energy	Computes the Galactic Cosmic Radiation (GCR) flux as an integrated distribution with respect to particle energy. The data items available for this data provider depend on the GCR model, atomic number, and potentially other GCR model dependent parameters.
SEET GCR Model	Parameter settings for the object's Galactic Cosmic Radiation (GCR) model.
SEET Magnetic Conjugacy	Computes the time intervals when the vehicle is magnetically conjugate with a target object. The user must specify the target object and the maximum separation angle between their respective field lines that will indicate conjugacy. The smaller the separation is made, the closer the field lines containing the vehicle and the target object must be. Valid for vehicles whose central body is earth.
SEET Magnetic Coordinates	Computes the vehicle's position and velocity in the requested coordinate system, as a function of time. Valid for vehicles whose central body is earth.
SEET Magnetic Field	Computes the geomagnetic field and various parameters associated with the geomagnetic field. Valid for vehicles whose central body is earth.
SEET Magnetic Field Model	Description of the parameter settings for the vehicle's Magnetic Field model.
SEET Meteor Flux	Computes the total meteoroid flux of all particulates, at the given time. Valid for vehicles whose central body is earth.
SEET Particle Distribution Fluence	Computes the fluence (i.e., the flux integrated over time) for the distribution of mass particles that are used to model meteoroid and debris particulates. Valid for vehicles whose central body is earth.
SEET Particle Fluence	Computes the total fluence (i.e., the total flux of all particulates integrated over time). Valid for vehicles whose central body is earth.
SEET Particle Flux Model	Parameter settings for the vehicle's Particle Flux model.
SEET Radiation Accumulated Dose	Computes the radiation dose as it accumulates over time for the requested time interval(s), using the step size to perform the numerical integration of dose rate with time. The data items available for this data provider depend on the shielding thicknesses in use. For each thickness, there will be data items for Electron dose, Electron-Bremsstrahlung dose, Proton dose, and Combined dose. Valid for vehicles whose central body is earth.
SEET Radiation Accumulated Dose By Thickness	Computes the radiation dose as it accumulates over time for the requested time interval(s), using the step size to perform the numerical integration of dose rate with time. The report is divided into subsections, where each subsection corresponds to a different shielding thickness. Valid for vehicles whose central body is earth.
SEET Radiation Average Dose Rate	Computes the average radiation dose rate. The data items available for this data provider depend on the shielding thicknesses in use. For each thickness, there will be data items for Model, Electron dose, Electron-Bremsstrahlung dose, Proton dose, and Combined dose. Valid for vehicles whose central body is earth.
SEET Radiation Average Dose Rate By Thickness	Computes the average radiation dose rate for each shielding thickness. The report is divided into subsections, where each subsection corresponds to a different shielding thickness. Valid for vehicles whose central body is earth.
SEET Radiation Dose Depth	Computes the radiation dose over the requested time interval(s), using the step size to perform the numerical integration of dose rate with time. Valid for vehicles whose central body is earth.
SEET Radiation Dose Rate	Computes the radiation dose rate. The data items available for this data provider depend on the shielding thicknesses in use. For each thickness, there will be data items for Model, Electron dose, Electron-Bremsstrahlung dose, Proton dose, and Combined dose. Valid for vehicles whose central body is earth.
SEET Radiation Dose Rate By Thickness	Computes the radiation dose rate for each shielding thickness. The report is divided into subsections, where each subsection corresponds to a different shielding thickness. Valid for vehicles whose central body is earth.
SEET Radiation Flux	Computes the radiation flux at each electron and proton energy level. The energy levels are determined by the computational mode. There will be data items for electrons and protons at each of their respective energy levels. Valid when using NASA or CRRES models. Valid for vehicles whose central body is earth.
SEET Radiation Flux by Energy	Computes the radiation flux at each electron and proton energy level. The energy levels are determined by the computational mode. The report is divided into subsections, where each subsection corresponds to a different constituent and energy level. Valid when using NASA or CRRES models. Valid for vehicles whose central body is earth.
SEET Radiation Integral Flux	Computes the integral radiation flux at each electron and proton energy level. The energy levels are determined by the computational mode. There will be data items for electrons and protons at each of their respective energy levels. Valid when using NASA or CRRES models. Valid for vehicles whose central body is earth.
SEET Radiation Integral Flux by Energy	Computes the integral radiation flux at each electron and proton energy level. The energy levels are determined by the computational mode. The report is divided into subsections, where each subsection corresponds to a different constituent and energy level. Valid when using NASA or CRRES models. Valid for vehicles whose central body is earth.
SEET Radiation Model	Parameter settings for the vehicle's Radiation model.
SEET SAA Contour Settings	Parameter settings for the vehicle's SAA (South Atlantic Anomaly) contour.
SEET SAA Crossing Times	Computes the SAA (South Atlantic Anomaly) transit times for the vehicle for the channel and flux level specified by the vehicle's SAA contour settings. Valid for vehicles whose central body is earth.
SEET SAA Flux Intensity	Computes the flux intensity within the SAA (South Atlantic Anomaly). Valid for vehicles whose central body is earth.
SEET SEP Energy by Fluence	The fluence value for the energy in the selected model based on the specified probability.
SEET SEP Fluence by Probability per Energy	A distribution of fluence and probabilities for each energy level in the selected model.
SEET SEP Model	Parameter settings for the object's Solar Energetic Particle (SEP) model.
SEET Vehicle Temperature	Computes the vehicle temperature considering incident sunlight heating, earth albedo, earth thermal radiation, and internal dissipation.
SEET Vehicle Temperature Model	Parameter settings for the vehicle's Temperature model.
STM Eigendecomposition	The eigenvalues and eigenvectors of the 6x6 cartesian State Transition Matrix (STM), formatted as text for better readability. The STM describes the effect of position-velocity perturbations made at the start of propagation on the position-velocity state at the reported time. The coordinate system of the STM is required pre-data. Updated data is generated only for segments with a propagator that has a State Transition Matrix propagator function. When accessing after the MCS has been run, the eigenvalues are sorted for consistency between ephemeris points. When accessing during an MCS run, the eigenvalues are sorted by absolute value of the real part.
Scalar Calculations	Calculation component that produces scalar time-varying calculations.
Segment Summary	Astrogator Mission Control Sequence (MCS) segment information. Normally the segment summary should be generated through the segment summary button on the Astrogator panel, not through this data provider. This data provider may give inconsistent results because it does not know which segment to use.
Shadow LLA	The location of the object's shadow on the object's central body surface, produced by the Sun at its apparent position as computed at the object's location. Note that the shadow point is defined as the intersection on the object's central body the line emanating from the center of the apparent Sun toward the object. Thus, the effects of the finite size of the Sun are ignored. In addition, no light time delay is computed for the light traveling between the object and the intersection point.
Solar Apparent Time	An angular measure of the true direction of the object, expressed as a time where 360 degrees is 24:00:00.00.
Solar Intensity	Percent of the solar disc visible, along with lighting condition and name of obscuring central body.
Solar Panel Angles	Data generated by the Solar Panel Tool related to the area of the solar panels illuminated by the sun evaluated for a set of possible incidence angles at a given time.
Solar Panel Area	Data generated by the Solar Panel Tool related to the area of the solar panels illuminated by the sun.
Solar Panel Area No Sum	Data generated by the Solar Panel Tool related to the area of the solar panels illuminated by the sun. Does not include data for All Solar Panel Groups.
Solar Panel Power	Data generated by the Solar Panel Tool related to the power captured from the solar panels illuminated by the sun.
Solar Panel Power No Sum	Data generated by the Solar Panel Tool related to the power captured from the solar panels illuminated by the sun. Does not include data for All Solar Panel Groups.
Solar Specular Point	The solar specular reflection point is the point on the object's central body surface where the reflected light of the Sun about the surface normal reaches the object. Light time delay effects are considered on both legs: From the Sun to the point on the surface. From the surface to the object itself. There may be times where the specular point does not exist.
Spherical Elements	The position and velocity of the object with respect to the object's central body, as observed from the requested coordinate system, expressed in spherical elements as a function of time.
State Transition Matrix	The 6x6 State Transition Matrix (STM) for the cartesian position and velocity, formatted as text lines that align columns for better readability. The STM describes the effect of position-velocity perturbations made at the start of propagation on the position-velocity state at the reported time. The coordinate system of the STM is required pre-data for this data provider. Updated data is generated only for segments with a propagator that has a State TransitionMatrix propagator function.
Sun Vector	The apparent position of the Sun with respect to the object as observed from the requested coordinate system, expressed in Cartesian components, as a function of time. The light time delay is actually computed between the Sun and the object's central body, rather than directly from the object itself.
Swath Points	The location of the object's horizon on the central body surface that is to the side of the motion of the object, reported as left and right horizon points over time. For the Ground Elevation Envelope or Vehicle Half Angle Envelope swath types, the left/right swath point may not exist. If it does not, the point being reported at that time uses the Ground Elevation or Vehicle Half Angle swath setting as appropriate.
TLE Residual Data	Residual information concerning the solved-for TLE created by the Generate TLE tool. A residual is the position difference between the satellite's ephemeris and the ephemeris created using the generated TLE.
TLE Set Data	Reports the values in a TLE Set.
TLE Summary Data	The summary of the criteria used to generate a TLE set, a summary of the iterative fit process and the TLE set itself.
Time Array	A time component that produces intervals of time within which there are ordered arrays of times.
Time Instant	A time component that produces a single moment in time.
True Anomaly Step	Classical osculating orbital elements, sometimes referred to as Keplerian elements, computed using ephemeris with respect to the object's central body, as observed from the requested coordinate system, as a function of true anomaly. The output is reported in constant steps of true anomaly as opposed to constant time steps.
User Supplied Data	Values of custom data associated with the object.
Vector Choose Axes	Reports the selected vector and its derivative in a specified reference set of axes. Both vector and axes must be defined in the Vector Geometry Tool.
Vector Choose Plane	Reports projection of the selected vector and its derivative on a specified reference plane. Both vector and plane must be defined in the Vector Geometry Tool.
Vectors(Body)	Reports the selected vector and its derivative in the object's body axes. The vector must be defined in the Vector Geometry Tool.
Vectors(Fixed)	Reports the selected vector and its derivative in the object's central body fixed axes. The vector must be defined in the Vector Geometry Tool.
Vectors(Fixed_VVLH)	Reports the selected vector and its derivative in the object's Fixed_VVLH axes. The vector must be defined in the Vector Geometry Tool.
Vectors(ICRF)	Reports the selected vector and its derivative in ICRF axes. The vector must be defined in the Vector Geometry Tool.
Vectors(Inertial)	Reports the selected vector and its derivative in the object's central body inertial axes. The vector must be defined in the Vector Geometry Tool.
Vectors(J2000)	Reports the selected vector and its derivative in J2000 axes. The vector must be defined in the Vector Geometry Tool.
Vectors(LVLH)	Reports the selected vector and its derivative in the object's LVLH axes. The vector must be defined in the Vector Geometry Tool.
Vectors(VNC)	Reports the selected vector and its derivative in the object's VNC axes. The vector must be defined in the Vector Geometry Tool.
Vectors(VVLH(CBF))	Reports the selected vector and its derivative in the object's VVLH(CBF) axes. The vector must be defined in the Vector Geometry Tool.
Vectors(VVLH)	Reports the selected vector and its derivative in the object's VVLH axes. The vector must be defined in the Vector Geometry Tool.
Velocity Projected Covariance	Provides data about velocity covariance matrix relative to selected set of axes. The covariance is transformed into the requested reference frame using a 3x3 coordinate transformation matrix. The result of this transformation is that the original covariance is simply expressed relative to the new axes and the effects of the rotation of the axes are ignored. Any set of axes defined in the Vector Geometry Tool is available for use, including user defined sets. The data requires position/velocity covariance to be defined for the object.