Spacecraft relative motion control has many applications including rendezvous and docking, circumnavigation, on orbit assembly, servicing, etc. The course Spacecraft Relative Motion Kinematics and Kinetics covers the fundamentals of describing the motion of one spacecraft as seen by another spacecraft.
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A range of relative coordinates are investigated. Further, the course covers developing the differential equations of motion of the relative motion and considers a range of assumptions on separation distances. Finally, the impact of the J2 perturbation on the relative motion is studied.
After this course, you will be able to...
- Describe relative motion using rectilinear or curvilinear Hill frame coordinates, using relative orbit elements, as well as using differential orbit elements.
- Develop the differential equations of relative motion for both near circular and highly elliptical chief motions
- Predict the impact of perturbations on the relative motion
- Understand how to setup relative orbits that remain bounded to the chief.
Please note: this is an advanced course, best suited for working engineers or students with college-level knowledge in mathematics and physics.
This course is part of the Spacecraft Formation Relative Orbits Specialization.
What you'll learn
- Describe relative motion with a range of coordinates
- Understand standard relative orbit prototypes
- Assess the impact of perturbations on the relative motion
- Setup bounded relative orbits for a range of chief eccentricities
Syllabus
Revisiting Basics of Keplerian Motion
Module 1
This week is a review of the fundamentals of un-perturbed Keplerian motion of a spacecraft. The material is taught at a fast pace assuming the learner has seen this matrial before.
Variation of Parameters
Module 2
This week you will learn the mathematics to derivate the variational equations of parameters that are invariants of the unperturbed problem.
Spacecraft Formation Flying
Module 3
This week you will explore the kinematics and kinetics of spacecraft relative motion.
Bounded Relative Motion
Module 4
In this final week, you will determine the naturally occurring relative orbit solutions for circular chief, eccentric chief and if J2 perturbations are present.
