scenarioFormationMeanOEFeedback

Overview

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 xmera/examples and executed by using:

python3 scenarioFormationMeanOEFeedback.py

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 simpleNav output message of type NavAttMsgPayload message at a certain period to 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.