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.Available for these objects: Satellite
Type: Time-varying data. Intended to be used only with elements from this same data provider.
Availability: Reports | Graphs
Data Provider Elements
| Name | Dimension | Type | Description |
|---|---|---|---|
| Time | Date | Real Number or Text | Time. |
| Semi-parameter | Distance | 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 | Distance | 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 | Angle | Real Number or Text | The angle between the orbit plane and the XY plane of the coordinate system. |
| Arg of Perigee | Angle | Real Number or Text | 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 | Angle | Real Number or Text | The angle in the XY plane from the X axis to the ascending node, measured in a right-handed sense about the Z axis. in the equatorial plane. For equatorial orbits, the ascending node is defined to be directed along the positive X axis, and thus the value is 0.0. |
| Height of Apogee | Distance | 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 | Distance | 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 | Time | 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 | AngleRate | Real Number | The change in inclination divided by the current period. |
| Arg of Perigee Rate | AngleRate | Real Number | The change in argument of periapse divided by the current period. |
| RAAN Rate | AngleRate | Real Number | The change in RAAN divided by the current period. |
| Shadow Duration | Time | Real Number | The average duration of the interval over which the satellite is in eclipse. |
| FBar | Unitless | Real Number | Averaged index of the solar flux at a wavelength of 10.7 cm at the Earth's orbit. |
| Ap | Unitless | Real Number | Geomagnetic activity index. |