Orbital Trajectory
When you select Orbital Trajectory as the Routing Mode, the Orbital Trajectory window will open.
This is where you configure your orbital trajectory before you generate it.
Start (UTC)
Set the required date and time for the start of the trajectory.
Use the dropdown arrow next to the date to open the calendar view and select the required date.
Use the arrow buttons next to the time to adjust the time forward or back.
Alternatively, you can click on a value box and enter the required date and time directly.
Simulation Length
Click on a value box and enter the required simulation length.
Mode
You can choose to use either Simple or Advanced mode for the Orbital Trajectory. Advanced mode will provide further options for the Orbital Trajectory:
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Height (km)This is the orbit height (in kilometres) above the WGS84 ellipsoid, measured at the equator. Set the required height for the trajectory. Use the arrows next to the value to increase/decrease the height. Alternatively, you can enter the required value directly into the value box. InclinationThis is the angle between the Equator (east from the ascending node) and the orbital plane (north from the ascending node). Set the required inclination for the trajectory and select whether to use Degrees or Radians. Use the arrows next to the value to increase/decrease the inclination. Alternatively, you can enter the required value directly into the value box. |
AdvancedThe Advanced Mode will provide optional parameters that you can configure for the trajectory. |
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EpochThis is the reference time for Keplerian Elements. Use the dropdown arrow to select the option you want to use from the following:
Use the dropdown arrow next to the date to open the calendar view and select the required date. Use the arrow buttons next to the time to adjust the time forward or back. Alternatively, you can click on a value box and enter the required date and time directly.
EccentricityA dimensionless parameter that determines the amount by which the orbit deviates from a perfect circle. A value of 0 defines a perfectly circular orbit, while values between 0 and 1 define elliptical orbits.
Adjust the Eccentricity by using the arrows next to the value to increase/decrease the eccentricity. Alternatively, you can enter the required value directly into the value box. Semi-Major Axis (m) or Revolutions Per DayClick the dropdown arrow to select between the following:
Set the required value for the selected option. Adjust the value by using the arrows next to it to increase/decrease the eccentricity. Alternatively, you can enter the required value directly into the value box. InclinationThe angle between the equator (east from the ascending node) and the orbital plane (north from the ascending node).
Set the required inclination for the trajectory and select whether to use Degrees or Radians. Use the arrows next to the value to increase/decrease the inclination. Alternatively, you can enter the required value directly into the value box. Longitude
Set the required longitude for the trajectory and select whether to use Degrees or Radians. Use the arrows next to the value to increase/decrease the value. Alternatively, you can enter the required value directly into the value box. Argument of PerigeeThe angle between the ascending node and the point of the orbit which is closest to the Earth, measured in the orbital plane in the direction of the moving satellite.
Set the required angle for the trajectory and select whether to use Degrees or Radians. Use the arrows next to the value to increase/decrease the inclination. Alternatively, you can enter the required value directly into the value box.
Mean AnomalyThe fraction of the orbit's period that has elapsed since the satellite passed the perigee, expressed as an angle.
Set the required angle for the trajectory and select whether to use Degrees or Radians. Use the arrows next to the value to increase/decrease the inclination. Alternatively, you can enter the required value directly into the value box. |
Orbital Period
This section will display the orbital period for the configured trajectory.
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| Note:
Equatorial orbits (including geostationary) are not supported. SatGen 4 will not simulate atmospheric drag, solar pressure, Sun and Moon pull or any other advanced effects. First and second order Earth gravitational effects are simulated. |
Help
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Click the Help button to open this Orbital Trajectory page in the User Guide on the Support Centre. |
Generate
Click the Generate button to make SatGen 4 generate the route and set the mode to Map Mode, where you can view and edit the Orbital Trajectory.
Cancel
Click Cancel to close the Orbital Trajectory window without generating a route.
Orbital Trajectory in Map Mode
When you have generated the Orbital Trajectory, SatGen 4 will open the trajectory in Map Mode.
Editing Trajectory
To edit the trajectory configuration, go to the Route Options.
This area will provide the same settings as the Orbital Trajectory configurator.
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Change the relevant settings in the configuration. The trajectory will automatically update in the Maps and on the Graph.
Creating a File With Orbital Trajectory
You can find more information and steps for creating scenario files with Orbital Trajectories in the Creating Files chapter in the User Guide.
Simulating Orbital Trajectory
You can find more information and steps for playing simulations with Orbital Trajectories in the Playing Simulations chapter in the User Guide.