Installed Styles: Satellite

The following is the list of installed Report and Graph styles for use with the Report Manager. Users may create their own styles to report/graph their desired content using the available data providers.

Reports

Name	Description
Accel File	Creates an acceleration history file to model manuevers for use in ODTK. Uses a data provider to compute thrust, mass, and mass flow rate over time, and then uses a Perl script to format that content into a .accelHist file. The location of the .accelHist file appears as the first line of the report. Perl must be installed on your computer and the extension *.pl must be associated with perl.exe.
Accel File Python	Creates an acceleration history file to model manuevers for use in ODTK. Uses a data provider to compute thrust, mass, and mass flow rate over time, and then uses a python script to format that content into a collection of .accelHist files, output to the directory C:\AccelFiles, one file per maneuver. Python, including pandas, must be installed on your computer and the extension .py must be associated with python.exe.
Active Constraints	Lists the constraints that are applied when computing the access.
Apogee	Reports the time of apoapsis (i.e., apogee when the object's central body is Earth) for each pass during the requested interval. If the orbit is circular, reports the text 'Circular'. If the apoapsis does not occur within a pass, reports the text 'Not in Pass'. This may occur during a partial pass when the requested interval doesn't start/end on a pass break, and the apoapsis does not occur within that partial pass.
Ascending Node	Reports the times at which the satellite is at its ascending node, during the requested interval.
Astrogator Log	The targeter log file. This data provider requires that the Satellite use the Astrogator propagator.
Astrogator Script Summary	The results from the last run of a script created using the Scripting Tool.
Attitude Quaternions	The attitude quaternion 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.
Attitude Schedule	The list of attitude segments describing the attitude for this object. Each segment is valid over its defined interval.
Attitude Segment	A list of the attitude segments describing the attitude for this object.
B1950 Position Velocity	The position and velocity of the object with respect to Earth, as observed from its B1950 coordinate system, expressed in Cartesian components as a function of time. Only available for objects whose central body is Earth.
Beta Angle	Reports the beta angle (i.e., the signed angle of the apparent vector to the Sun) over time, 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.
Classical Orbit Elements	Classical osculating orbital elements, sometimes referred to as Keplerian elements, computed using ephemeris with respect to the object's J2000 coordinate system, as a function of time.
Close Approach	Reports Close Approach tool settings and the list of conjunctions between the object and secondary vehicles that eventually become within a specified minium range threshold, as computed by the Close Approach tool.
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.
DeckAccessCommonName	Reports the output from the Deck Access tool, including the common name if available. 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.
Descending Node	Reports the time of descending node for each pass during the requested interval. If the orbit is equatorial, reports the text 'Equatorial'. If the descending node does not occur within a pass, reports the text 'Not in Pass'. This may occur during a partial pass when the requested interval doesn't start/end on a pass break, and the descending node does not occur within that partial pass.
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).
Ephemeris-IFT	The position and velocity of the object with respect to Earth, as observed from its AlignmentAtEpoch coordinate system, expressed in Cartesian components as a function of time. The AlignmentAtEpoch system is the non-rotating coordinate system (i.e., a constant offset from ICRF) coincident with the Fixed system evaluated at the object's coordinate reference epoch (usually, the initial orbit epoch). Only available for objects whose central body is Earth.
Ephemeris-IFT-LLA	The position of the object (expressed in LLA elements), and the velocity of the object (expressed in Cartesian components of the object's central body's Fixed coordinate system) as a function of time.
EphemerisChooseAxes	Reports the object's Position and Velocity vectors in a specified reference set of axes. The user chooses the reference axes, which must be defined in the Vector Geometry Tool.
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 313 Euler angles, as a function of 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 313 sequence uses Z, then the new X, and then finally the newest Z axis.
Fixed Acceleration	The acceleration of the object with respect to the object's central body, as observed from its central body's Fixed coordinate system, expressed in Cartesian components as a function of time.
Fixed LLR Position	The ephemeris of the object with respect to the object's central body, as observed from the Fixed coordinate system, expressed in LLR elements as a function of time.
Fixed Position Velocity	The position and velocity of the object with respect to the object's central body, as observed from its central body's Fixed coordinate system, expressed in Cartesian components as a function of time.
Generated TLE	The TLE that was generated using the Generate TLE tool, used to fit an ephemeris using the SGP4 propagator.
Inertial Acceleration	The acceleration of the object as observed in the object's central body's intertial coordinate system, expressed in Cartesian components, as a function of time.
Inertial Position Velocity	The position and velocity of the object with respect to the object's central body, as observed from its central body's inertial coordinate system, expressed in Cartesian components as a function of time.
J2000 Acceleration	The acceleration of the object with respect to the object's central body, as observed from its central body's J2000 coordinate system, expressed in Cartesian components as a function of time.
J2000 Position Velocity	The position and velocity of the object with respect to the object's central body, as observed from its central body's J2000 coordinate system, expressed in Cartesian components as a function of time.
LLA Position	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.
LOP Mean Elements	The ephemeris of the object, as observed in the object's central body's inertial 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.
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 Times	A listing of lighting intervals organized into 3 sections: (i) sunlight (full lighting) intervals, (ii) penumbra (partial lighting) intervals, and (iii) umbra (zero lighting) intervals.
Lunar Vector Fixed	The apparent position of the Moon with respect to the object as observed from the object's central body's Fixed 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.
Lunar Vector J2000	The apparent position of the Moon with respect to the object as observed from the object's central body's J2000 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.
Lunar Vector TOD	The apparent position of the Moon with respect to the object as observed from the object's central body's True of Date 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.
MCS Ephemeris Segments	Shows which Astrogator segment produced each interval of ephemeris. This data provider requires that the Satellite use the Astrogator propagator.
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.
MOD Position Velocity	The position and velocity of the object with respect to the object's central body, as observed from its central body's Mean Of Date coordinate system, expressed in Cartesian components as a function of time.
Maneuver History	Reports thrust maneuver metrics, as a function of time, during each Astrogator maneuver segment.
Maneuver Summary	A summary of the maneuvers for an Astrogator satellite. Only valid for an Astrogator satellite.
Model Area	The area of the object's 3D graphics model, as viewed from a given view direction, as computed by the Area Tool.
Pass Data	A report of events during the passes of the satellite, including apoapsis, periapsis, ascending node, and descending node. 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.
Penumbra	A listing of the penumbra (partial lighting) intervals.
Penumbra Start	A listing of the penumbra (partial lighting) start times.
Penumbra Stop	A listing of the penumbra (partial lighting) stop times.
Perigee	Reports the time of periapsis (i.e., perigee when the object's central body is Earth) for each pass during the requested interval. If the orbit is circular, reports the text 'Circular'. If the periapsis does not occur within a pass, reports the text 'Not in Pass'. This may occur during a partial pass when the requested interval doesn't start/end on a pass break, and the periapsis does not occur within that partial pass.
Propagator Inputs	Parameters used by the specified propagator to propagate the vehicle.
RIC	The relative position of the assigned object with respect to the primary object, expressed in Cartesian components of the RIC (Radial, In-Track, Cross-Track) frame defined using the primary's ephemeris, as a function of time. Cross-track refers to the direction perpendicular to the position and inertial velocity (in direction of the cross product of position with velocity); in-track refers to the direction perpendicular to both the radial and cross-track (positive in the direction of motion). 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 being reported between primary and assigned objects that should be at the same position (but interpolation noise gets reported because of the time grid mis-match).
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.
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.
Solar AER	The azimuth, elevation, and range of the apparent relative position vector of the Sun over time, with respect to Inertial VVLH axes (ECIVVLH).
Solar Intensity	The percent of the solar disc visible over time.
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. Users must select a time (when the object is not in umbra).
Solar Panel Area	The effective area and solar intensity of the solar panels illuminated by the sun.
Solar Panel Power	The power and solar intensity of the solar panels illuminated by the sun.
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	A listing of the sunlight (full lighting) intervals.
Sun Start	A listing of the sunlight (full lighting) start times.
Sun Stop	A listing of the sunlight (full lighting) stop times.
Sun Vector Fixed	The apparent relative position of the Sun to the object, expressed in Cartesian components, using the object's central body's Fixed coordinate system, as a function of time.
Sun Vector J2000	The apparent relative position of the Sun to the object, expressed in Cartesian components, using the object's central body's J2000 coordinate system, as a function of time.
Sun Vector TOD	The apparent relative position of the Sun to the object, expressed in Cartesian components, using the object's central body's True of Date coordinate system, as a function of time.
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. The left horizon point is on the left side of the horizontal component of velocity vector, where the velocity vector is measured as observed from the object's central body fixed coordinate system. The horizontal component is that component not along the detic zenith of the object. The right horizon point is on the right side. 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.
TEMEofDate Position Velocity	The position and velocity of the object with respect to Earth, as observed from its TEME of Date coordinate system, expressed in Cartesian components as a function of time. Only available for objects whose central body is Earth.
TEMEofEpoch Position Velocity	The position and velocity of the object with respect to Earth, as observed from its TEME of Epoch coordinate system, expressed in Cartesian components as a function of time. Only available for objects whose central body is Earth.
TLE	The GP (General Perturbations) data that is used with the SGP4 propagator, formatted as TLEs (two-line element sets.
TLE Solution Summary	The summary of the criteria used to generate a TLE set, a summary of the iterative fit process and the TLE set itself.
TLE TEME Residuals	The residuals between the object's position and the position created using the solved-for TLE created by the Generate TLE tool, as computed in the TEME coordinate systrem, as a function of time.
TOD Position Velocity	The position and velocity of the object with respect to the object's central body, as observed from its central body's True Of Date coordinate system, expressed in Cartesian components as a function of time.
Umbra	A listing of the umbra (zero lighting) intervals.
Umbra Start	A listing of the umbra (zero lighting) start times.
Umbra Stop	A listing of the umbra (zero lighting) stop times.
Yaw Pitch Roll	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 321 YPR angles, as a function of time. YPR angles use a sequence of three rotations starting from a reference coordinate frame. 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. The 321 sequence uses Z, then Y, and then finally the X axis. 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.

Graphs

Name	Type	Description
Beta Angle	Time XY	Plots the beta angle (i.e., the signed angle of the apparent vector to the Sun) over time, 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.
Classical Orbit Elements	Time XY	A plot of the angles and the semimajor axis of the classical osculating orbital elements, sometimes referred to as Keplerian elements, computed using ephemeris with respect to the object's J2000 coordinate system, as a function of time. Eccentricity is not plotted.
Close Approach Periods	Interval	An Interval graph of the conjunction time intervals where at least one conjunction occurs with a secondary vehicle, as computed by the Close Approach tool. A conjunction occurs if the object becomes with the specified minimum range threshold to a secondary vehicle at some time.
Cumulative Sunlight	Cumulative Pie	A Pie chart showing the total duration of full sunlight within the graph's requested time interval. Gaps in the chart indicate the total duration of penumbra and umbra durations.
Eclipse Times	Interval	An Interval graph of the penumbra (partial lighting) and umbra (zero lighting) intervals.
Euler Angles	Time XY	A plot of 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 313 Euler angles, over 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 313 sequence uses Z, then the new X, and then finally the newest Z axis.
Fixed Position Velocity	Time XY	The position and velocity of the object with respect to the object's central body, as observed from its central body's Fixed coordinate system, expressed in Cartesian components as a function of time.
Inertial Position Velocity	Time XY	The position and velocity of the object with respect to the object's central body, as observed from its central body's inertial coordinate system, expressed in Cartesian components as a function of time.
J2000 Position Velocity	Time XY	The position and velocity of the object with respect to the object's central body, as observed from its central body's J2000 coordinate system, expressed in Cartesian components as a function of time.
LLA Position	Time XY	The position 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.
Lifetime	Time XY	A plot of the apogee height, perigee height, and eccentricity of the object over time, as computed using the Lifetime Tool.
Lifetime Space Weather	Time XY	A plot of the space weather (F10.7 and Ap values) used when computing the object's lifetime using the Lifetime Tool.
Lighting Times	Interval	An Interval graph of the sunlight (full lighting) intervals, penumbra (partial lighting) intervals and umbra (zero lighting) intervals. Each lighting condition's intervals are plotted on separate lines.
Model Area	Time XY	A plot of the area of the object's 3D graphics model over time, as viewed from a given view direction, as computed by the Area Tool.
RIC	Time XY	A plot of the relative position of the assigned object with respect to the primary object, expressed in Cartesian components of the RIC (Radial, In-Track, Cross-Track) frame defined using the primary's ephemeris, as a function of time. Cross-track refers to the direction perpendicular to the position and inertial velocity (in direction of the cross product of position with velocity); in-track refers to the direction perpendicular to both the radial and cross-track (positive in the direction of motion). 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 being reported between primary and assigned objects that should be at the same position (but interpolation noise gets plotted because of the time grid mis-match).
Solar AER	Time XY	A plot of the azimuth, elevation, and range over time, describing the apparent relative position vector of the Sun with respect to Inertial VVLH axes (ECIVVLH).
Solar Az-El	Polar	A polar plot with elevation as radius and azimuth as angle theta over time, describing the apparent relative position vector of the Sun with respect to Inertial VVLH axes (ECIVVLH).
Solar Elevation - Body Fixed	Time XY	A plot of the solar elevation over time, describing the apparent relative position vector of the Sun with respect to the object. The elevation angle is measured from the XY plane of the object's body axes, positive in the +Z direction.
Solar Intensity	Time XY	A plot of the percent of the solar disc visible over time.
Solar Panel Area	Time XY	A plot of the effective area of the solar panels illuminated by the sun over time.
Solar Panel Power	Time XY	A plot of the power of the solar panels illuminated by the sun over time.
Sun Vector Fixed	Time XY	A plot of the apparent relative position of the Sun to the object, expressed in Cartesian components, using the object's central body's Fixed coordinate system, as a function of time.
Sunlight Intervals	Interval Pie	A Pie chart showing each interval of full sunlight within the graph's requested time interval, separated by gaps indicating the intervals of penumbra/umbra lighting condition before and after each sunlight interval.
TLE TEME Residuals	Time XY	A plot of the final residuals, computed between the object's position and the position created using the solved-for TLE created by the Generate TLE tool, as computed in the TEME coordinate systrem, as a function of time.
Yaw Pitch Roll	Time XY	A plot of 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 321 YPR angles, as a function of time. YPR angles use a sequence of three rotations starting from a reference coordinate frame. 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. The 321 sequence uses Z, then Y, and then finally the X axis. 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.