This script sets up a formation flying scenario with two spacecraft. The deputy spacecraft keeps a given mean orbital element difference based on Lyapunov control theory.
This script is found in the folder
basilisk/examples and executed by using:
The simulation layout is shown in the following illustration. Two spacecraft are orbiting the earth at close distance. Only \(J_2\) gravity perturbation is included. Each spacecraft sends a Module: simpleNav output message of type NavAttMsgPayload message at a certain period to Module: meanOEFeedback, where mean orbital element difference is calculated and necessary control force is output to extForceTorque module.
Illustration of Simulation Results¶
show_plots = True, useClassicElem = True
In this case, target orbital element difference is set based on classical orbital element. This resulting feedback control error is shown below.
show_plots = True, useClassicElem = False
In this case, target orbital element difference is set based on equinoctial orbital element. This resulting feedback control error is shown below.
- scenarioFormationMeanOEFeedback.run(show_plots, useClassicElem, numOrbits)¶
At the end of the python script you can specify the following example parameters.
show_plots (bool) – Determines if the script should display plots
useClassicElem (bool) – Determines if classic orbital element is used