Final project of the lecture UUM517E - Spacecraft Dynamics.
- Anton H.J. de Ruiter, Christopher J. Damaren and James R. Forbes, Spacecraft Dynamics and Control: An Introduction, First Edition, John Wiley & Sons, Ltd., 2013.
- F. Landis Markley, John L. Crassidis, Fundamentals of Spacecraft Attitude Determination and Control, Space Technology Library, 2014
- David A. Vallado, Fundamentals of Astrodynamics and Applications, Fourth Edition, Microcosm Press, 2013.
- Howard D. Curtis, Orbital Mechanics for Engineering Students, Revised Fourth Edition, Elsevier, Aerospace Engineering Series, 2021.
(assume Earth and Mars are at the ecliptic plane with circular orbits around Sun)
- Select a suitable date and time starting from this year in order to send your spacecraft to Mars
- Determine the launch characteristics to send your spacecraft to a parking orbit at 500 km, and then to escape from the Earth’s sphere of influence
- Design an interplanetary Hohmann transfer orbit between Earth and Mars
- Let the spacecraft have a circular Mars parking orbit at 300 km altitude when it reached to Mars
- Determine the minimum time necessary before leaving Mars and coming back to Earth using an interplanetary Hohmann transfer orbit
(use your project part 1 outputs for the position information –if necessary, use planet ephemeris) (assume that you have a three-axis sun sensor)
- Design an extended Kalman filter (EKF) for estimating the direction of the Sun using the onboard sensor
- Determine the periods of being in eclipse. In case that the filter diverges in eclipse, reinitialize your code after eclipse