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Event Name: L3: Cislunar - Understanding the State Transition Matrix
Location: Online
Date(s): Apr-13
Time: 12:00 p.m. - 1:00 p.m. (ET)
Price: Free
Launching missions in Earth-Moon space requires you to understand the stability characteristics of a satellite's orbit in that regime. Understanding the stability information provides you with hints into the localized linear motion that could be extended to the underlying nonlinear solution. This State Transition Matrix (STM) Primer will show you how to get the eigenvalues and eigenvectors for your orbits. You will also examine an application of the Lambert Search Profile that connects our satellite's initial orbit into a manifold arc that takes it into its final halo orbit. Upon completion of this class, you will be able to:

  • Generate the STM results
  • Understand the significance of the resulting eigenvalues
  • Connect the trajectory arc with the manifold