Missile
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. |
| 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 Schedule | The list of attitude segments describing the attitude for this object. Each segment is valid over its defined interval. |
| 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. |
| 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. |
| 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 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 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. |
| 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. |
| Flight Airspeed and Atmosphere | Aeronautical data elements based on the 1976 US Standard Atmosphere |
| Flight Attitude | Attitude of the body axes, expressed using standard aeronautical terms. |
| 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. |
| Ground Range | The ground range and altitude of the vehicle over time. |
| Heading | Heading information relative to the object's central body fixed coordinate system. |
| Interval | A time component that produces a single interval of time. |
| Interval List | A time component that produces an ordered list of time intervals. |
| 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. |
| Launch Clear Intervals | The time intervals for which a launch produced no close approaches within the specified range threshold. |
| Launch Window Definition | Parameter settings for the Launch Window Analysis Tool. |
| LaunchBlackout | Launch window blackout time intervals determined by the close approach tool. Only valid if the launch window capability has been used. During a launch window blackout interval, the vehicle will have a close approach with some secondary vehicle if it were to be launched during that interval. |
| LaunchBlackout By Launch | The Launch Blackout report results, sorted by primary launch object. |
| LaunchWindow | The results produced by using the Launch Window Analysis tool, identifying vehicles that pass within a specified minimum range of the object. |
| LaunchWindowByLaunch | The Launch Window report results, sorted by primary launch object. |
| LaunchWindowByLaunchID | The Launch Window report results, sorted by primary launch SSC. |
| LaunchWindowByLaunchName | The Launch Window report results, sorted by primary launch name. |
| LaunchWindowByMinRange | The Launch Window report results, sorted by minimum range. |
| LaunchWindowBySSC | The Launch Window report results, sorted by secondary SSC. |
| 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. |
| 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. |
| 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. |
| 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 CrossSection Impact | Position Covariance CrossSection Impact computes cross-section of the position covariance ellipsoid in a plane perpendicular to the object's CBF velocity at the stop time (impact time). The resulting ellipse is projected further along the CBF velocity which makes up an elliptical cylinder. The cylinder's intersection with the local horizontal plane makes the final ellipse which is reported by this data provider. |
| 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 Projection Impact | Position Covariance Projection Impact computes projection of the position covariance ellipsoid onto a plane perpendicular to the object's CBF velocity at the stop time (impact time). The resulting ellipse is projected further along the CBF velocity which makes up an elliptical cylinder. The cylinder's intersection with the local horizontal plane makes the final ellipse which is reported by this data provider. |
| 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. |
| Propagator Inputs | Parameters used by the specified propagator to propagate the vehicle. |
| 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. |
| Scalar Calculations | Calculation component that produces scalar time-varying calculations. |
| 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 Intensity | Percent of the solar disc visible, along with lighting condition and name of obscuring central body. |
| 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:
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. |
| 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. |
| 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. |
| 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. |