TY  - INPR
N2  - Upper stages of launchers sometimes drift, with the main engine switched-off, for a longer period of time until re-ignition and subsequent payload release. During this period a large amount of propellant is still in the tank and the motion of the fluid (sloshing) has an impact on the attitude of the stage. For the flight phase the classical spring/damper or pendulum models cannot be applied. A more elaborate sloshing-aware model is described in the paper involving a time-varying inertia tensor.

Using principles of hybrid systems theory we model the minimum impulse bit (MIB) effect, that is, the minimum torque that can be exerted by the thrusters. We design a hybrid model predictive control scheme for the attitude control of a launcher during its long coasting period, aiming at minimising the actuation count of the thrusters.
KW  - Aerospace
KW  -  hybrid systems
KW  -  predictive control for linear systems
UR  - https://controls.papercept.net/conferences/conferences/ECC15/program/ECC15_ContentListWeb_3.html#tha4_04
TI  - Sloshing-aware attitude control of impulsively actuated spacecraft
ID  - eprints2673
M2  - Linz, Austria
AV  - public
A1  - Sopasakis, Pantelis
A1  - Bernardini, Daniele
A1  - Strauch, Hans
A1  - Bennani, Samir
A1  - Bemporad, Alberto
T2  - European Control Conference
Y1  - 2015/07//
PB  - IEEE
ER  -