Launch Vehicle Properties
Simple Ascent Propagator
The simple ascent propagator creates an ascent trajectory based on launch and insertion parameters. The trajectory is a simple curve rising vertically from the launch pad that turns over smoothly to insert the launch vehicle into orbit with a zero flight path angle at the insertion point using the specified velocity.
To define the simple ascent propagator:
- Select the SimpleAscent propagator on the Trajectory page.
- If necessary, change the Start Time, Stop Time & Step Size. Use the current scenario time period by turning on Use Scenario Analysis Period.
- Select and define the simple ascent propagator elements.
Simple Ascent propagator elements
| Elements |
Description |
| Launch Location (first 3 fields) |
Select Geodetic or Geocentric Elements:
- Latitude (Geodetic), Longitude, Altitude
- Latitude (Geocentric), Longitude, Radius
If you switch between Geodetic and Geocentric elements, values for Latitude and Altitude/Radius update automatically. (Longitude does not differ along Geocentric/Geodetic lines.) |
| Burnout Velocity (4th field) |
The velocity of the launch vehicle at the Stop Time (burnout). |
| Burnout Location (last 3 fields) |
The same combinations of elements are available here as for Launch Location (above). It is not necessary to use the same type of elements (Geodetic or Geocentric) for Launch and Burnout Location. |