Orbit Mechanics 1

(ECTS: 3; SWS: 2)

Lecturers

Univ.-Prof. Dr.phil.nat. Urs Hugentobler

Prerequisites

Objectives

At the end of the module the students should understand the basics of satellite motion. They should know how to compute orbit positions based on orbital elements and how to obtain elements starting from position and velocity vectors. They are able to represent orbits in different reference frames and to convert orbit positions between frames. They are familiar with the concept or orbit perturbations.

Lecture:

- Reference systems in space and time

- Two-body problem and Keplerian motion

- Orbit representations, Keplerian elements, groundtracks, repeat orbits

- Orbit perturbations, osculating elements, Gaussian perturbation equations, types of perturbations

Labs with Matlab:

- Representation of orbits in different frames

- Ephemeris calculation

- Transformation between inertial, earth-fixed and topocentric reference frames

Written lab reports are a requirement for the admission to the exam.

Literature

Montenbruck, Gill (2000):Satellite Orbits. Springer.
Beutler (2005):Methods of Celestial Mechanics. Springer
Lecture Notes

Downloads

Chapter 1: Introduction (1,4 MB)
Chapter 2: Two-Body Problem (356 KB)
Chapter 3: Coordinate and Time Systems (1,5 MB)
Chapter 4: Ground Tracks (449 KB)
Chapter 5: Orbit Perturbations (307 KB)
Chapter 6: Gravitational Perturbations (353 KB)
WS 10/11: Chapter 7: Special Orbits (1,3 MB)
Lecture Plan (22 KB)