scenarioOrbitManeuver
Overview
This script sets up a 3-DOF spacecraft which is orbiting Earth. The purpose is to illustrate how to start and stop the Basilisk simulation to apply some \(\Delta v\)’s for simple orbit maneuvers. Read scenarioBasicOrbit to learn how to setup an orbit simulation.
The script is found in the folder basilisk/examples and executed by using:
python3 scenarioOrbitManeuver.py
The simulation layout is shown in the following illustration. A single simulation process is created which contains the spacecraft object. The BSK simulation is run for a fixed period. After stopping, the states are changed and the simulation is resumed.
When the simulation completes 2 plots are shown for each case. One plot always shows the inertial position vector components, while the second plot either shows a plot of the radius time history (Hohmann maneuver), or the inclination angle time history plot (Inclination change maneuver).
Illustration of Simulation Results
The following images illustrate the expected simulation run returns for a range of script configurations.
show_plots = True, maneuverCase = 0
In this case a classical Hohmann transfer is being simulated to go from LEO to reach and stay at GEO. The math behind such maneuvers can be found in textbooks such as Analytical Mechanics of Space Systems.
show_plots = True, maneuverCase = 1
In this case a classical plane change is being simulated to go rotate the orbit plane first 8 degrees, then another 4 degrees after orbiting 90 degrees. The math behind such maneuvers can be found in textbooks such as Analytical Mechanics of Space Systems.
