Pass Event Times
Times corresponding to certain orbital events. These event times can also be reported using the Passes data provider. However, the Passes data provider only reports one event per pass. It can be the case that two events occur on one pass, while none occurs on the next pass [e.g., when the pass break occurs very close to apogee]. In such a case, an event will not be reported by that data provider. The Pass Event Times data provider, however, will report out all events irrespective of the pass to which the event belongs.Available for these objects: Satellite
Type: Interval data.
Availability: Reports | Graphs
Data Provider Elements
| Name | Dimension | Type | Description |
|---|---|---|---|
| Count | Unitless | Integer | Number of grid points at reported latitude. |
| Time of Ascen Node | Date | Real Number or Text | The time when the satellite is at the ascending node (i.e., the Z component of the inertial position vector increases through zero). The inertial position vector is expressed in the coordinate system specified on the pass break settings of the satellite, except that Inertial is used if the setting is Fixed. If the orbit is nearly equatorial, the value will not be computed. |
| Time of Descen Node | Date | Real Number or Text | The time when the satellite is at the descending node (i.e., the Z component of the inertial position vector decreases through zero). The inertial position vector is expressed in the coordinate system specified on the pass break settings of the satellite, except that Inertial is used if the setting is Fixed. If the orbit is nearly equatorial, the value will not be computed. |
| Time of Apogee | Date | Real Number or Text | The time when the range rate is decreasing through zero. The range rate is defined as the dot product of the position and velocity vectors divided by the magnitude of the position vector. If the orbit is very close to circular, the time will not be computed. |
| Time of Perigee | Date | Real Number or Text | The time when the range rate is increasing through zero. The range rate is defined as the dot product of the position and velocity vectors divided by the magnitude of the position vector. If the orbit is very close to circular, the time will not be computed. |
| Time of Min Lat | Date | Real Number or Text | The time of the minimum detic latitude, as found by determining the time at which the Z component of velocity vector is increasing through zero. The velocity vector is expressed in the vehicle's central body fixed coordinate system. If the orbit is nearly equatorial, then the value will not be computed. |
| Time of Max Lat | Date | Real Number or Text | The time of the maximum detic latitude, as found by determining the time at which the Z component of velocity vector is decreasing through zero. The velocity vector is expressed in the vehicle's central body fixed coordinate system. If the orbit is nearly equatorial, then the value will not be computed. |
| Time of Max Sun El | Date | Real Number or Text | The time of the maximum elevation angle to the sun. |
| Time of Apparent Noon | Date | Real Number or Text | The time during the pass when the satellite's apparent solar time is noon. |
| Time of Apparent Midnight | Date | Real Number or Text | The time during the pass when the satellite's apparent solar time is midnight. |
| Time of Apparent Dawn | Date | Real Number or Text | The time during the pass when the satellite's apparent solar time is 6am. |
| Time of Apparent Dusk | Date | Real Number or Text | The time during the pass when the satellite's apparent solar time is 6pm. |