Print Email Facebook Twitter Guidance & Stability of Parachute Systems for Planetary Descent Title Guidance & Stability of Parachute Systems for Planetary Descent Author Trovarelli, Federico (TU Delft Aerospace Engineering) Contributor Mooij, E. (mentor) Degree granting institution Delft University of Technology Programme Aerospace Engineering | Astrodynamics & Space Missions Date 2018-03-15 Abstract A key requirement for enabling Mars manned mission is the capability to land a payload within 100 m from its nominal target. State of the art technology, however, is still far from reaching this objective. A possible solution for improving the landing accuracy on Mars is the development of a guidance system that exploits thrusters installed on the backshell of the descent vehicle to control its position during the parachute flight. The research aims at evaluating how the stability properties of the parachute-payload spacecraft are influenced by the control action and what performance the resulting closed-loop system can achieve. To do this, first the dynamics of the spacecraft, modelled as a rigid body, has been investigated analytically. Second, its response in different mission scenarios was simulated by means of a multibody model. The results are encouraging and prove that the parachute descent guidance system could efficiently contribute to improving the landing accuracy on Mars. Subject parachuteguidancestabilitymultibody To reference this document use: http://resolver.tudelft.nl/uuid:89b85454-8833-4f05-ab54-a0f7ad751f20 Embargo date 2019-03-29 Part of collection Student theses Document type master thesis Rights © 2018 Federico Trovarelli Files PDF thesis.pdf 21.47 MB Close viewer /islandora/object/uuid:89b85454-8833-4f05-ab54-a0f7ad751f20/datastream/OBJ/view