Research Article  Open Access
Using of HInfinity Control Method in Attitude Control System of RigidFlexible Satellite
Abstract
The attitude control systems of satellites with rigid and flexible components are demanding more and more better performance resulting in the development of several methods control. For that reason, control design methods presently available, including parameters and states estimation, robust and adaptive control, as well as linear and nonlinear theory, need more investigation to know their capability and limitations. In this paper the investigated technique is HInfinity method in the performance of the Attitude Control System of a RigidFlexible Satellite.
1. Introduction
The rapidly complexity increase of systems and processes to be controlled has stimulated the development of sophisticated analysis and design methods called advanced techniques. The HInfinity control theory, introduced by Zames [1], is one of the advanced techniques and its application in several problems of control has been growing rapidly.
The employment of flexible structures in the spatial area is another problem of control system which has been growing up too. Flexible systems offer several advantages compared with the rigid system. Some advantages are relatively smaller actuators, lower overall mass, faster response, lower energy consumption, in general, and lower cost. With the study of the Attitude Control System (ACS) of space structures with flexible antennas and/or panel and robotic manipulators, one becomes more complex when the dimensions of such structures increase due to necessity to consider a bigger number of vibration modes in its model in order to improve the model fidelity [2]. Examples of projects that involve flexible space structures are the International Space Station (ISS), the Lunar Reconnaissance Orbiter (LRO), the Lunar Crater Observation and Sensing Satellite (LCROSS), the Hubble Space Telescope, and so forth.
In RigidFlexible Satellite (RFS) the function of the ACS is to stabilize and orient the satellite during its mission, counteracting external disturbances torques and forces. In this paper is investigated multivariable control method for attitude control of an RFS consisting of a rigid body and two flexible panels. The satellite modeling was built following the Lagrangian approach and the discretization was done using the assumedmodes method. The equations of motion obtained were written in its modal state space form.
2. The RigidFlexible Satellite Model
Figure 1 shows the picture of the satellite used in this work, which is composed of a rigid body of cubic shape and two flexible panels. The center of mass of the satellite is in the point 0 origin of the system of coordinates that coincides with its main axis of inertia. The elastic appendixes with the beam format are connected in the central body, being treated as a punctual mass in its free extremity. The length of the panel is represented by the mass is represented by , and is the elastic displacement in relation to the axis The moment of inertia of the rigid body of the satellite in relation to the mass center is The moment of inertia of the panel in relation to its own mass center is given by
3. Equations of Motion
In the Lagrang approach are considered the equation of motion of the satellite around in and the elastic displacement of the panels. The Lagrange equations [3] for the problem can be written in the following form: In (3.1) is the torque of the reaction wheel, is the Lagrangian, and is the rotation angle of the satellite around the axis In (3.2) is the dissipation energy associated to the deformation of the panel it represents each one of the generalized coordinates of the problem.
The beam deflection variable is discretized using the expansion where represents the number of manners to be adopted in the discretization and represents each one of the own modes of the system. The admissible functions are given by [4] where and are the eigenvalues of the free system and undamped.
For the complete system, the total kinetic energy is given by therefore, where is the density of the panels and is the area. The dissipation energy function is where is the dissipation constant. So is given by
In (3.8) is constant elastic of the panels. After some manipulations of (3.8) [5] and using the orthogonalization property of vibration modes of the beam [6], one has
Finally, two equations are obtained. These equations represent the dynamics of rotation motion of the satellite and the elastic displacement of the panels, respectively, where the term nonlinear in (3.10) is defined as centripetal rigidity, and in (3.11) is a Piezoelectric actuator adapted for the following simulations where will be considered (one mode), and the constants are given by
4. HInfinity Control Method
4.1. Introduction
Throughout the decades of 1980 and 1990, HInfinity control methodhad a significant impact in the development of control systems; nowadays the technique has become fully grown and it is applied on industrial problems [5]. In the control theory in order to achieve robust performance or stabilization, the HInfinity control method is used. The control designer expresses the control problem as a mathematical optimization problem finding the controller solution. techniques have the advantage over classical control techniques in which the techniques are readily applicable to problems involving multivariable systems with crosscoupling between channels; disadvantages of techniques include the high level of mathematical understanding needed to apply them successfully and the need for a reasonably good model of the system to be controlled. The problem formulation is important, since any synthesized controller will be “optimal” in the formulated sense.
The name derives from the fact that mathematically the problem may be set in the space which consists of all bounded functions that are analytic in the righthalf complex plane. We do not go to this length. The norm is the maximum singular value of the function; let us say that it can be interpreted as a maximum gain in any direction and at any frequency; for SISO (Single In, Single Out) systems, this is effectively the maximum magnitude of the frequency response. method is also used to minimize the closedloop impact of a perturbation: depending on the problem formulation, the impact will be measured in terms of either stabilization or performance. Thus, one concludes that the procedures to project control systems are a difficult task due to the cited terms which are conflicting properties [7].
4.2. Modeling
This problem is defined by the configuration of Figure 2. The “plant” is a given system with two inputs and two outputs. It is often referred to as the generalized plant. The signal is an external input and represents driving signals that generate disturbances, measurement noise, and reference inputs. The signal is the control input. The output has the meaning of control error and ideally should be zero. The output , finally, is the observed output and is available for feedback.
The project of control system is based given by A more general state space representation of the standard plant is The solution of the corresponding problem based on Riccati equations is implemented requires the following conditions to be satisfied [8]:(1)(A, B_{2}) is stabilizable and (C_{2}, A) is detectable,(2)D_{12} and D_{21} have full rank,(3)[AjwI B_{2}; C_{1}D_{12}] has full column rank for all (hence, D_{12} is tall),(4)[AjwI B_{1}; C_{2}D_{21}] has full column rank for all (hence, D_{21} is wide).
The augmented plant is formed by accounting for the weighting functions W_{1}, W_{2}, and W_{3}, as shown in Figure 3. In order to reach the acting objectives, the outputs were chosen to be transfer weight functions:
The function cost of mixed sensibility is given for where is called sensibility, is complementary sensitivity function, and does not have any name. The cost function of mixed sensibility is named alike, because it punishes and at the same time; it can also be said project requirement. The transfer function from to z_{1} is the weighted sensitivity function , which characterizes the performance objective of good tracking; the transfer function from w to is the complementary sensitivity function whose minimization ensures low control gains at high frequencies, and the transfer function from w to is KS, which measures the control effort. It is also used to impose the constraints on the control input for example, the saturation limits.
5. Simulations
The simulations were carried out by computational implementation of the software MatLab. The initials conditions used here are rad. and rad./s. The values considered for the physical parameters in the numerical simulation are presented in Table 1.

The procedure of the project of is different from other control projects knowledge such as LQR (Linear Quadratic Regulator) and LQG (Linear Quadratic Gaussian) [5]; the difference is the use of weighting functions W_{1}, W_{2}, and W_{3}, where and the others are given by where punishes the error sign , punish the control sign “”, and W_{3} punishes the exit of the plant is a parameter obtained through successive attempts.
6. Results
First we analyze the open loop of the system through transmission zeros (TZs) and the closeloop with Control. The TZs are critical frequencies where signal transmission between input and output is stopped. The importance of use of the TZs is given by their application in robust control, because they are the zeros of a MIMO system. In Table 2 are represented the values.

Following, the performances of control in the ACS are observed in Figures 4 and 5.
(a)
(b)
(a)
(b)
Both graphs, in Figure 4, have existence of overshoot, in which they could commit the system; however, the time of stabilization of both was of approximately 3.5 seconds. In other words, in spite of the existence of overshoots, the control of the system, in a long time, was reached.
In Figure 5 the behavior of the vibration of the panels is presented. The displacement of overshoot is of the order of 10^{7}, in other words, very small. The time of stabilization in the first graph is about 0.5 seconds and for the second one is about 0.45 seconds. This demonstrates that the control H∞ possesses a good performance for angle and angular velocity, as well as to control the vibration of the panels.
7. Conclusions
The problem of attitude control of satellites is not new and has been addressed by several researchers using many different approaches. The control method is one of the most advanced techniques available today for designing robust controllers. One great advantage with this technique is that it allows the designer to tackle the most general form of control architecture wherein explicit accounting of uncertainties, disturbances, actuator/sensor noises, actuator constraints, and performance measures can be accomplished. The system is very different from the methods LQR and LQG, for example. However, a great disadvantage is the experience and necessary abilities to design the form of the weighting functions and the fact that the plant can increase. Basically, the success of the method depends on the correct choice of the weight functions transfer.
Acknowledgments
The authors would like to thank CAPES and INPE/DMC. This work was supported by CAPES thought the Brasil—Portugal Cooperation Project PCT no. 241/09.
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Copyright
Copyright © 2009 Ximena Celia Méndez Cubillos and Luiz Carlos Gadelha de Souza. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.