Data Providers: Satellite: Astrogator Values: Formation

Calc Objects for relative motion and close approaches with respect to the master satellite or a specified vehicle. See also Relative Motion. The close approach X axis is the unit vector in the direction of the cross product of the relative velocity vector with the orbit momentum vector of the reference vehicle. The close approach Y axis is the unit vector in the direction of the cross product of the X axis and the relative velocity vector. The close approach plane is the plane spanned by the X and Y axes. The close approach vector is the relative position vector from the reference vehicle.

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

Name

Dimension

Type

Description

Time

DateFormat

Real Number

Time.

CloseApproachBearing

AngleUnit

Real Number

The angle from the relative velocity vector to the reference vehicle. The Calc Object allows a choice of a central body. The default is Earth.

CloseApproachMagnitude

DistanceUnit

Real Number

The magnitude of close approach vector. The value is sqrt(x^2 + y^2). The Calc Object allows a choice of a central body. The default is Earth.

CloseApproachTheta

AngleUnit

Real Number

The angle from X to close approach vector. The Calc Object allows a choice of a central body. The default is Earth.

CloseApproachX

DistanceUnit

Real Number

The X component of close approach vector. The Calc Object allows a choice of a central body. The default is Earth.

CloseApproachY

DistanceUnit

Real Number

The Y component of close approach vector. The Calc Object allows a choice of a central body. The default is Earth.

CosineOfCloseApproachBearing

Unitless

Real Number

The cosine of the close approach bearing. The Calc Object allows a choice of a central body. The default is Earth.

RelGroundTrackError

DistanceUnit

Real Number

Ground track error compared to the reference vehicle. The value for the satellite is computed at the current state; the value for the reference is computed at either the previous or next state where the reference vehicle's argument of latitude is the same as the satellite's current value. The ground track error can be unsigned or signed based on RxV.

Rel_Mean_Arg_of_Lat

AngleUnit

Real Number

The relative mean argument of latitude compared to the reference vehicle.

Rel_Mean_Arg_of_Perigee

AngleUnit

Real Number

The relative mean argument of perigee compared to the reference vehicle.

Rel_Mean_Eccentricity

Unitless

Real Number

The relative mean eccentricity compared to the reference vehicle.

Rel_Mean_Inclination

AngleUnit

Real Number

The relative mean inclination compared to the reference vehicle.

Rel_Mean_Mean_Anomaly

AngleUnit

Real Number

The relative mean mean anomaly compared to the reference vehicle.

Rel_Mean_Period

TimeUnit

Real Number

The relative mean orbit period compared to the reference vehicle.

Rel_Mean_RAAN

AngleUnit

Real Number

The relative mean RAAN compared to the reference vehicle.

Rel_Mean_Semimajor_Axis

DistanceUnit

Real Number

The relative mean semimajor axis compared to the reference vehicle.

RelativeAtAOL

TimeUnit

Real Number

The relative value (i.e., difference between the value computed for this satellite and the reference vehicle) of a specified calculation object. The value for the satellite is computed at the current state; the value for the reference is computed at either the previous or next state where the reference vehicle's argument of latitude is the same as the satellite's current value.

RelativeValue

TimeUnit

Real Number

The relative value (i.e., difference between the value computed for this satellite and the reference vehicle) of a specified calculation object. Both values are computed at the given epoch.