UsafGeneralPerturbationElements Properties 
The UsafGeneralPerturbationElements type exposes the following members.
Name  Description  

ArgumentOfPerigee 
Gets or sets the argument of perigee, in degrees.
(Inherited from Sgp4Elements.)  
BallisticCoefficient 
Gets or sets the ballistic coefficient or the area times
the drag coefficient divided by the mass. This value has
the units of m^2/kg.
 
BStar 
Gets or sets the BSTAR drag term, in units of 1 / EarthRadii.
This term represents a modification of the ballistic coefficient
(Coefficient of drag times area over mass). The value is modified
by one half atmospheric density and expressed in units of inverse
Earth radii. Source: https://celestrak.com/ (Inherited from Sgp4Elements.)  
Classification 
Gets or sets the classification.
 
Eccentricity 
Gets or sets the eccentricity
(Inherited from Sgp4Elements.)  
ElementNumber 
Gets or sets the element number.
 
EnergyDissipationRate 
Gets or sets the energy dissipation rate of the
satellite due to atmospheric drag in watts/kg.
 
EphemerisType 
Gets or sets the ephemeris type. Ephemeris Type 0 is the correct type for Sgp4Propagator.
Ephemeris type 4 is not supported by Sgp4Propagator, and it will throw an argument exception
if a UsafGeneralPerturbationElements has ephemeris type 4.
 
Epoch 
Gets or sets the epoch at which these initial conditions are defined.
(Overrides Sgp4ElementsEpoch.)  
ErrorGrowthRate 
Gets or sets the last calculated error growth rate
in kilometers per day.
 
Inclination 
Gets or sets the inclination, in degrees
(Inherited from Sgp4Elements.)  
InternationalDesignator 
Gets or sets the international designator.
 
LastObservationTime 
Gets or sets the time of last observation that was used
by orbit determination for the satellite. This time is
in +/ fractional days relative to the
Epoch.
 
MeanAnomaly 
Gets or sets the mean anomaly, in degrees.
(Inherited from Sgp4Elements.)  
MeanMotion 
Gets or sets the mean motion, in revolutions per day.
(Inherited from Sgp4Elements.)  
MeanMotionDot 
Gets or sets the first derivative of mean motion divided by two, in revolutions per day squared.
 
MeanMotionDotDot 
Gets or sets the second derivative of mean motion divided by six, in revolutions per day cubed.
 
Name 
Gets or sets the spacecraft name.
 
ObjectType 
Gets or sets the type of orbiting body.
 
OriginalSatelliteNumber 
Gets or sets the original satellite number of
the object. This is often the same as
the SatelliteNumber.
 
RadarCrossSection 
Gets or sets the median radar cross section of
the object.
 
RawEpoch 
Gets or sets the epoch at which these initial conditions are defined,
represented in the standard form: YYYYDDD.DDDD.
(Overrides Sgp4ElementsRawEpoch.)  
RevolutionNumber 
Gets or sets the revolution number at epoch.
 
RightAscensionOfAscendingNode 
Gets or sets the right ascension of the ascending node, in degrees
(Inherited from Sgp4Elements.)  
SatelliteNumber 
Gets or sets the satellite number.
 
SolarRadiationParameter 
Gets or sets the AGOM or the area times
the solar radiation pressure coefficient (gamma)
divided by the mass. This value has the units of
m^2/kg.
 
SwitchingMethod 
Gets or sets the method to use when switching between this element set and the following element set.
By default, this is Sgp4ElementsSwitchByEpoch.
(Inherited from Sgp4Elements.)  
VisualMagnitude 
Gets or sets the median visual magnitude of the
object scaled to the standard distance of 35786 km
(elevation of GEO at zenith). This value is used
regardless of the sensor to satellite geometry.
