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.
| Name |
Dimension |
Type |
Description |
| Time |
DateFormat |
Real Number |
Time. |
| Semi-parameter |
DistanceUnit |
Real Number |
The semi-latus rectum, often designated by the
letter p, related to the semimajor axis a and eccentricity e by p =
a*(1-e^2). |
| Semi-major Axis |
DistanceUnit |
Real Number |
A measure of the size of the orbit. Orbits with
eccentricity <1 are ellipses, with major and minor axes
identifying the symmetry axes of the ellipse, the major axis being
the longer one. The value is half the length of the major
axis. |
| Eccentricity |
Unitless |
Real Number |
A measure of the shape of the orbit. Values <1
indicate an ellipse (where zero is a circular orbit) and values
>1 indicate a hyperbola. |
| Inclination |
AngleUnit |
Real Number |
The angle between the orbit plane and the XY plane
of the coordinate system. |
| Arg of Perigee |
AngleUnit |
Real Number |
The angle from the ascending node to the periapsis
vector measured in the orbit plane in the direction of the object's
motion. The periapsis vector locates the closest point of the
orbit. For a circular orbit, the value is defined to be zero (i.e.,
periapsis at the ascending node). |
| RAAN |
AngleUnit |
Real Number |
Not defined for this class of object. |
| Height of Apogee |
DistanceUnit |
Real Number |
The difference between the apogee radius and the
equatorial radius of the vehicle's central body (an approximation
for the altitude). |
| Height of
Perigee |
DistanceUnit |
Real Number |
The difference between the perigee radius and the
equatorial radius of the vehicle's central body (an approximation
for the altitude). |
| Sidereal Period |
TimeUnit |
Real Number |
The period of the orbit, computed using the
two-body formula involving the semimajor axis and the gravitational
constant of the vehicle's central body. |
| Orbit Count |
Unitless |
Integer |
The current orbit count. |
| Semi-parameter
Rate |
Rate |
Real Number |
The change in semi-parameter divided by the current
period. |
| Semi-major
Axis Rate |
Rate |
Real Number |
Rate of change of semi-major axis. Computed by
applying the variation of parameters equations of motion to the
perturbative acceleration. |
| Eccentricity
Rate |
Unitless Per Time |
Real Number |
The change in eccentricity divided by the current
period. |
| Inclination Rate |
AngleRateUnit |
Real Number |
The change in inclination divided by the current
period. |
| Arg of Perigee
Rate |
AngleRateUnit |
Real Number |
The change in argument of periapse divided by the
current period. |
| RAAN Rate |
AngleRateUnit |
Real Number |
The change in RAAN divided by the current
period. |
| Shadow Duration |
TimeUnit |
Real Number |
The average duration of the interval over which the
satellite is in eclipse. |