5 research outputs found
Bounded gain-scheduled LQR satellite control using a tilted wheel
From the beginning of the satellite usage, the momentum created by its
movements has been a concern that has to be taken into account for every
space mission. Depending on the dimensions, weight and objective during its
use, a momentum e
xchange device might, actually, be one of the best systems
to control the satellite attitude in its three axis.
In this paper, a tilted wheel system with variable tilt angles and wheel
acceleration, plus a redundant wheel spinning at constant speed in opp
osite
direction, is studied as a control system for a rigid satellite model.
From the mathematical model of the satellite body and the tilted wheel system,
a Simulink diagram is used to simulate their implementations in the satellite.
On top of it, a clas
sical LQR and Set
-
Point Tracking LQR control law are
studied to control the satellite system.
These control laws have proven to be worth to take them into consideration to
control the whole system. By its versatility, stability, rapidity and optimal result
s,
LQR is a good option to control a rigid satellite with a tilted wheel as
momentum exchange device.
In addition, the tilted wheel has demonstrated to surpass all the previous
momentum exchange actuators capabilities, making it one of the best systems
to
control a body by momentum.
Using the LQR control law previously commented, a further study was done
using a High Performance Bounded Gain
-
Scheduled control. In this variation of
LQR, a gain tuning law is imposed for a better response of the satellite,
a
djusting the gains in relation with the response obtained in every time. This
method allows solving analytically the algebraic Ricatti equation, not as LQR
that solves it numerically.
Regarding this second study, a faster response was obtained, as expected
from the theoretical part.
Despite the successful results obtained in the simulations. A further study
should be needed for a better implementation of the constraints, such as the
slew rat
Bounded Gain-Scheduled LQR Satellite Control using a Tilted Wheel
Satellite attitude control is normally performed with actuators such as CMGs, reaction wheels. This research considers a novel type of 3-DOF actuator that uses a spinning wheel and tilt mechanism, which has less mass, more simplicity and is singularity-free during nominal operation in comparison to existing actuators. A novel high-performance bounded LQR control law is also presented which is capable of gain-scheduling its parameters. High-fidelity 3-DOF simulations demonstrate feasibility for both wheel and control law
Bounded gain-scheduled LQR satellite control using a tilted wheel
Satellite attitude control is normally performed with actuators such as CMGs, reaction wheels. This research considers a novel type of 3-DOF actuator that uses a spinning wheel and tilt mechanism, which has less mass, more simplicity and is singularity-free during nominal operation in comparison to existing actuators. A novel high-performance bounded LQR control law is also presented which is capable of gain-scheduling its parameters. High-fidelity 3-DOF simulations demonstrate feasibility for both wheel and control law
Bounded gain-scheduled LQR satellite control using a tilted wheel
From the beginning of the satellite usage, the momentum created by its
movements has been a concern that has to be taken into account for every
space mission. Depending on the dimensions, weight and objective during its
use, a momentum e
xchange device might, actually, be one of the best systems
to control the satellite attitude in its three axis.
In this paper, a tilted wheel system with variable tilt angles and wheel
acceleration, plus a redundant wheel spinning at constant speed in opp
osite
direction, is studied as a control system for a rigid satellite model.
From the mathematical model of the satellite body and the tilted wheel system,
a Simulink diagram is used to simulate their implementations in the satellite.
On top of it, a clas
sical LQR and Set
-
Point Tracking LQR control law are
studied to control the satellite system.
These control laws have proven to be worth to take them into consideration to
control the whole system. By its versatility, stability, rapidity and optimal result
s,
LQR is a good option to control a rigid satellite with a tilted wheel as
momentum exchange device.
In addition, the tilted wheel has demonstrated to surpass all the previous
momentum exchange actuators capabilities, making it one of the best systems
to
control a body by momentum.
Using the LQR control law previously commented, a further study was done
using a High Performance Bounded Gain
-
Scheduled control. In this variation of
LQR, a gain tuning law is imposed for a better response of the satellite,
a
djusting the gains in relation with the response obtained in every time. This
method allows solving analytically the algebraic Ricatti equation, not as LQR
that solves it numerically.
Regarding this second study, a faster response was obtained, as expected
from the theoretical part.
Despite the successful results obtained in the simulations. A further study
should be needed for a better implementation of the constraints, such as the
slew rat