Spacecraft Attitude Stabilization with Piecewise-constant Magnetic Dipole Moment Fabio Celani School of Aerospace Engineering
Outline • • • • •
attitude control problem model of spacecraft with magnetorquers separation between measurement and actuation design of piecewise-constant control case study
Fabio Celani Sapienza University of Rome – RAST 2015
Page 2
Attitude control problem Z
spacecraft on a circular Low Earth Orbit
Geocentric Inertial (GCI) frame
body frame Y
X, !
objective: body frame aligned with GCI frame parametrize attitude of body frame with respect to GCI frame using quaternion vector part of body frame aligned with GCI frame Fabio Celani Sapienza University of Rome – RAST 2015
Page 3
Model of spacecraft with magnetorquers relative kinematics dynamics
spacecraft is equipped with three coils aligned with body axis vector of coils’ magnetic dipole moments geomagnetic field in body frame
spacecraft model
Fabio Celani Sapienza University of Rome – RAST 2015
Page 4
Control problem spacecraft model objective: design control law for
so that
and
PD-like feedback
locally exponentially stable [C., Lovera-Astolfi]
Fabio Celani Sapienza University of Rome – RAST 2015
Page 5
Separation between measurement and actuation not measurable measure of
set
Fabio Celani Sapienza University of Rome – RAST 2015
Page 6
Piecewise-constant control continuous control
piecewise-constant control
objective: design parameters
Fabio Celani Sapienza University of Rome – RAST 2015
so that
and
Page 7
Case study
circular orbit
inclination 87°
• initial state
altitude 450 km
€
• desired final state
Fabio Celani Sapienza University of Rome – RAST 2015
Page 8
Design of piece-wise constant control – step 1/3 design continuous control by trial-and-error
keep Fabio Celani Sapienza University of Rome – RAST 2015
for piecewise-constant control Page 9
Design of piece-wise constant control - step 2/3 determine
such that matrix
is stable for all
and fix
in case study pick
Fabio Celani Sapienza University of Rome – RAST 2015
Page 10
Design of piece-wise constant control - step 3/3 pick
sufficiently small where
in case study pick
Fabio Celani Sapienza University of Rome – RAST 2015
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Simulation
Fabio Celani Sapienza University of Rome – RAST 2015
Page 12
Conclusions • attitude stabilization method for spacecraft using piecewise-constant magnetic dipole moment • piecewise-constant attitude and attitude rate feedback • piecewise-constant attitude only feedback (no rategyros) in conference proceedings
Fabio Celani Sapienza University of Rome – RAST 2015
Spacecraft Attitude Stabilization with Piecewise ...
attitude control problem. ⢠model of spacecraft with magnetorquers. ⢠separation between measurement and actuation. ⢠design of piecewise-constant control. ⢠case study. Page 3. Attitude control problem. Fabio Celani. Sapienza University of Rome â RAST 2015. Page 3. X,. Y. Z. Geocentric Inertial (GCI) frame body frame.
Jan 5, 2016 - Let Bi be the geomagnetic field at spacecraft expressed in inertial frame Fi. .... In order to simplify forthcoming expressions let us define â.
determined by length of measurement process (not a control design parameter) ... closed-loop dynamics given by sampled-data nonlinear time-varying system.
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The book documents the development of the important ... determination and control systems. It provides ... Spacecraft Systems Engineering (Aerospace Series).
Sapienza University of Rome â DyCoSS 2014. Page 2. ⢠three-axis inertial pointing. ⢠model for spacecraft and geomagnetic field. ⢠spacecraft controllability.
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GeoCentric Inertial (GCI) frame body frame parametrize attitude of ... spacecraft with magnetorquers on a circular Low Earth Orbit body frame aligned with GCI ...
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