This article has been retracted as it is essentially identical in content with a previously published paper “Luiz C. G. de Souza, Victor M. R. Arena, Design of Non Linear Controller for a Satellite Attitude Control Simulator, In Frontiers in Aerospace Engineering (FAE), 2012, Vol. 1, issue 1”.

View the full Retraction here.

#### References

- L. C. G. de Souza and V. M. R. Arena, “Design of satellite attitude control algorithm based on the SDRE method using gas jets and reaction wheels,”
*Journal of Engineering*, vol. 2013, Article ID 318072, 8 pages, 2013.

Journal of Engineering

Volume 2013, Article ID 318072, 8 pages

http://dx.doi.org/10.1155/2013/318072

## Design of Satellite Attitude Control Algorithm Based on the SDRE Method Using Gas Jets and Reaction Wheels

National Institute for Space Research (INPE), Avnida dos Astronautas, 1758 S J Campos, SP, Brazil

Received 16 August 2012; Revised 19 October 2012; Accepted 3 November 2012

Academic Editor: Luis Carlos Rabelo

Copyright © 2013 Luiz C. G. de Souza and Victor M. R. Arena. 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.

#### Abstract

An experimental attitude control algorithm design using prototypes can minimize space mission costs by reducing the number of errors transmitted to the next phase of the project. The Space Mechanics and Control Division (DMC) of INPE is constructing a 3D simulator to supply the conditions for implementing and testing satellite control hardware and software. Satellite large angle maneuver makes the plant highly nonlinear and if the parameters of the system are not well determined, the plant can also present some level of uncertainty. As a result, controller designed by a linear control technique can have its performance and robustness degraded. In this paper the standard LQR linear controller and the SDRE controller associated with an SDRE filter are applied to design a controller for a nonlinear plant. The plant is similar to the DMC 3D satellite simulator where the unstructured uncertainties of the system are represented by process and measurements noise. In the sequel the State-Dependent Riccati Equation (SDRE) method is used to design and test an attitude control algorithm based on gas jets and reaction wheel torques to perform large angle maneuver in three axes. The SDRE controller design takes into account the effects of the plant nonlinearities and system noise which represents uncertainty. The SDRE controller performance and robustness are tested during the transition phase from angular velocity reductions to normal mode of operation with stringent pointing accuracy using a switching control algorithm based on minimum system energy. This work serves to validate the numerical simulator model and to verify the functionality of the control algorithm designed by the SDRE method.

#### 1. Introduction

The design of a satellite Attitude Control System (ACS), that involves plant uncertainties [1] and large angle maneuvers followed by stringent pointing control, may require new nonlinear attitude control techniques in order to have adequate stability, good performance, and robustness. Experimental ACS design using nonlinear control techniques through prototypes is one way to increase confidence in the control algorithm. Experimental design has the important advantage of representing the satellite dynamics in a laboratory setting, from which it is possible to accomplish different simulations to evaluate the satellite ACS [2]. However, the drawback of experimental testing is the difficulty of reproducing zero gravity and torque free space conditions. A multiobjective approach [3] has been used to design a satellite controller with real codification. An investigated through experimental procedure has been used by Conti and Souza in [4] for simulator inertia parameters identification. An algorithm based on the least squares method to identify mass parameters of a rotating space vehicle during attitude maneuvers has been developed by Lee and Wertz in [5], a method with the same objectives, but based on Kaman filter theory also has been investigated by Souza in [6]. The -infinity control technique was used in [7] to design robust control laws for a satellite composed of rigid and flexible panels. In the SDRE method, the nonlinear dynamics are brought to a time-invariant, linear-like structure containing state-dependent coefficients. Infinite-horizon LQR is then applied to the linear-like structure with the coefficient matrices being evaluated at the current operational point in the state space. The process is repeated in the next sampling periods therefore producing and controlling several state-dependent linear models out of a nonlinear one. The SDRE method was applied by Souza in [8] for controlling a nonlinear satellite system with six-degrees of freedom. However, it did not incorporate the SDRE filter as a state observer for the SDRE method, so that uncertainties could be accounted for in the filtering process. In this paper the SDRE technique [9] along with the associated Kalman filter [10] is applied to design a nonlinear controller for a nonlinear simulator plant where the unstructured uncertainties of the system are represented by process and measurement noise. As a result, the satellite attitude control algorithm design using the SDRE technique and SDRE filter is able to deal with large angle maneuvers and plant uncertainties. The control strategy is based on reaction wheel and gas jets as actuators which allow the design of two control algorithms related to the transition from high angular velocity mode to the normal mode of operation with stringent pointing using an optimal switching control algorithm based on minimum system energy. Several simulations have proven the computationally feasibility for real time execution of the SDRE control algorithm using the satellite’s onboard computer [11].

#### 2. SDRE Control Methodology

The Linear Quadratic Regulation (LQR) approach is well known and its theory has been extended for the synthesis of nonlinear control laws for nonlinear systems [8]. This is the case for satellite dynamics that are inherently nonlinear [12]. A number of methodologies exist for the control design and synthesis of these highly nonlinear systems; these techniques include a large number of linear design methodologies [13] such as Jacobian linearization and feedback linearization used in conjunction with gain scheduling [14]. Nonlinear design techniques have also been proposed including dynamic inversion and sliding mode control [15], recursive back stepping, and adaptive control [16].

Compared to multiobjective optimization nonlinear control methods [3] the SDRE method has the advantage of avoiding intensive interaction calculations, resulting in simpler control algorithms that are more appropriate for implementation on a satellite’s onboard computer.

The nonlinear regulator problem [17] for a system represented in the state-dependent Riccati equation form with infinite horizon, can be formulated by minimizing the cost functional given by with the state and control subject to the nonlinear system constraints given by where and are the system input and the output matrices, and ( is the dimension of the output vector of the system). The vector initial conditions is , and are the weight matrix semi defined positive and defined positive.

Applying a direct parameterization to transform the nonlinear system into State Dependent Coefficients (SDC) representation, the dynamic equations of the system with control can be write in the form with , where is the state matrix. By and large is not unique. In fact there are an infinite number of parameterizations for SDC representation. This is true provided there are at least two parameterizations for all satisfying

The choice of parameterizations to be made must be appropriate in accordance with the control system of interest. An important factor for this choice is not violating the controllability of the system, that is, the matrix controllability state-dependent must be full rank.

The state-dependent algebraic Riccati equation (SDARE) can be obtained applying the conditions for optimality of the variational calculus. As a result, the Hamiltonian for the optimal control problem given by (1) and (2) is given by where is the Lagrange multiplier.

Applying to (5) the necessary conditions for the optimal control given by , , and , one gets

Assuming the costate in the form , which is dependent of the state, from (8) one obtains the feedback control law Substituting this result into (7) one gets

To find the function one differentiates with respect the time along the path from which one gets

Substituting (11) in the first necessary condition of optimal control (see (6)) one obtains

Arranging the terms more appropriately one has

In order to satisfy the equality of (13) one obtains two important relations. The first one is state-dependent algebraic Riccati equation (SDARE) which solution is given by The second one is the necessary condition of optimality which must be satisfied and it is given by

For the infinite time problem and considering the standard Linear Quadratic Regulator (LQR) problem, this is a condition that satisfies the optimality of the solution suboptimal control.

Finally, the nonlinear control law feedback by the states has the following form:

For some special cases, such as systems with little dependence on the state or with few state variables, (14) can be solved analytically. On the other hand, for more complex systems the numerical solution can be obtained using an adequate sampling rate. It is assumed that the parameterization of the coefficients dependent on the state is chosen so that the pair are in the linear sense for all belonging to the neighbourhood about the origin, point-to-point, stabilizable and detectable, respectively. Then the SDRE nonlinear regulator produces a closed loop solution that is locally asymptotically stable. An important factor of the SDRE method is that it does not cancel the benefits that result from the nonlinearities of the dynamic system, because, it is not a required inversion and not a dynamic feedback linearization of the nonlinear system.

The Nonlinear State Estimation problem [18] is analogous to linear method. Using the dual formulation to the nonlinear quadratic regulator problem, a nonlinear estimator can be formed, assuming that the measurement is a nonlinear function of such that One needs to form a state dependent coefficient measurement

For the optimal estimation problem, the cost function can be of the form:

Subject to the nonlinear differential constraints where is the is Gaussian zero-mean white process noise with , the variance of the process noise and is is the Gaussian zero mean white measurement noise with , the variance of the measurement noise. The SDC matrices of measurement have to satisfy the same conditions for the SDC regulator problem.

Using the dual of the regulator problem, the SDRE nonlinear estimator is given by where is also positive semidefinite solution of another state-dependent algebraic Riccati equation (SDARE) given by

The SDRE estimator has shown to be effective in many applications [10] and its matrix is calculated in every step after estimating the states and calculating and . The conjunction of the SDRE and SDRE filter techniques is quite adequate for onboard computer implementations. However, here the SDRE filter is only implemented in the normal mode of operation where the sensor noise can affect the fine pointing accuracy.

#### 3. SimulatorModel

Figure 1 shows the INPE 3D simulator which has a disk-shaped platform, supported on a plane with a spherical air bearing. Considering that the simulator is not complete build, one assumes that there are three reaction wheels and the gas jets configuration set capable of performing maneuver around the three axes and that there are three angular velocities sensor, like gyros. Apart from the difficulty of reproducing zero gravity and torque free condition, modeling a 3-D simulator, basically, follows the same step of the modeling of a rigid satellite with rotation in three axes free in space.

The orientation of the platform is given by the body reference system with respect to inertial reference system considering the principal axes of inertia and using the Euler angles in the sequence 3-2-1, to guarantee that there is no singularity in the simulator attitude rotation. The equations of motions are obtained using Euler’s angular moment theorem given by where and are the torque and the angular moment of the system, which is given by where is the system matrix inertia moment, is the angular velocity of the platform, is the reaction wheel matrix inertia moment and are the reaction wheel angular velocity.

Differentiating (24) and considering that the angular velocity of is and that the external torque is equal to zero, one has

Substituting (24) into (25), the angular velocity of the system is

The simulator attitude as function of the angular velocity is

In order to design the attitude control system based on reaction wheels and gas jets actuators of performing a large angle maneuver, it is important to have in mind that each control algorithm is designed based on in two different sets of equations of motions. In other words, the gas jets are applied to reduce the high angular velocity and the reaction wheel is used to control in the fine pointing accuracy mode. As a result, for each operation mode one has different matrices and the respective matrix associated with it. The matrix, although depend on the sensor type is assumed unity for simplicity.

In the fine pointing mode where the reaction wheel is the actuator, the state’s are , and the control are , the matrices and are given by

One knows that the reaction wheel generates internal torques and the attitude control is performed by exchange of angular moment between the reaction wheel and the satellite. On the other hand, gas jets generate external torque given by where is the torque generated around the “” axis due to the force applied at distance from the rotation axis.

In the angular reduction mode using gas jets the reaction wheel is locked, therefore, its acceleration and angular velocity are zero and the satellite angular velocity is given by The states are and the control are , therefore, the matrices and are given by

#### 4. Criterion for Changing the Actuator

The implementation of the SDRE algorithm in real time has becomes more realistic because of the commercial microprocessor is getting faster [11]. Here, the control system has to deal with two operation modes where the first one is the reduction of high angular velocity using gas jets and the second one is the control in three axes with fine pointing accuracy using reaction wheel. As a result, it is necessary to establish a criterion to change from one actuator to another. This criterion of course is function of the satellite space mission and the control system equipments. For example, from the angular velocity reduction mode to the normal mode of operation the criterion could be associated with the amount of energy that the reaction wheel can support before being saturated or with the minimum and maximum values of the gas jets capacity. The criterion used here is based on the total potential and kinetic energy of the system, which means that when the system reaches a certain level of energy the control algorithm change the type of actuator.

The potential energy associated with the angular displacement is where is a constant and represent the angular displacement of the simulators.

The simulator kinetic energy is given by where is a constant and is the angular velocity of the simulator. It is important to say that the constants and must be such to maintain the total system energy compatibles. Besides, the level of energy can be changed according to the kind of control system to be evaluated. Here one assumes certain level of energy just for simulation purpose.

#### 5. Simulation Results

The superiority of the SDRE method to perform a regulation and tracking large angle manoeuvre over the LQR method has been demonstrated in [10]. Here, the simulation is to demonstrate the ability of the SDRE plus SDRE filter techniques to control a nonlinear plant based on switching control algorithm using the previous criterion of energy to change from the gas jets to reaction wheel action. The simulator platform can accommodate various satellites components like sensors, actuators, computers and its respective interface, and electronics. Therefore, the inertia moments of the simulator depend on the equipment’s distribution over it. Here, one assumes and uses the following typical inertia moment for the simulator: Kgm^{2} and Kgm^{2} and for the reaction wheel 0.0018 Kgm^{2}. The maximum and minimum gas jet torque used is 10 Nm and the total amount of system energy to change from gas jets to reaction wheel is 0.5 J. In the fine pointing mode the typical sensor noises used are theta = 0.2 (deg) and rate theta = 0.1 (deg/s).

To demonstrate the performance of the SRRE controller one imposes a severe large angle maneuver which begins on 0° and in the end it has to track an angular reference of (100, 50, 70) deg. The controller performance requirements are small overshoot and quick time of response. The controller robustness is associated with its ability to perform big tracking maneuver apart from the perturbations due to sensor noise and plant nonlinear terns. Besides, it is important to say that this performance is a function of the weighting matrices of the SDRE controllers. After some trial and error one gets the following values for matrices diag [0.0001 0 0;0 0.0001 0;0 0 0.0001] and diag [1 0 0 0 0 0;0 1 0 0 0 0;0 0 1 0 0 0;0 0 0 100 0 0;0 0 0 0 100 0;0 0 0 0 0 100].

Figures 2 and 3 show the angular displacement and angular velocity when the SDRE controller performs the simulator large maneuver from 0° and it has to tracking the previous angular reference. One observes that at the maneuver end the nonlinear terms of the plant are more relevant. The SDRE controller is able to get the reference in about 250 s.

Figures 4 and 5 show the SDRE controller in the transition phase of the previously maneuver where the torque is only due to the gas jets and the torque is only due to the reaction wheel, respectively.

Figure 6 shows how the switching control algorithm works. That is, the gas jets stop acting and the reaction wheel started acting when the criterion for changing actuators is achieves, system total energy equals to 0.5 J.

From simulations one observes that at the beginning of the maneuver the level of energy is high, because the simulator is far from the final attitude to be follow. As a result, the switching control algorithm selects as actuators the thrusters in order to deal with high angular velocities reduction. On the other hands, when the simulator reaches the reference attitude, the total energy decreases rapidly and the switching control algorithm selects as actuators the reaction wheels, in order to perform fine pointing adjustment of the simulator.

Finally, it is important to say that the criterion for changing the actuated based on the energy value defined in the program was established just to provide a good visualization of the torques from the two actuators during the simulation. However, further study of this actuated change can be done based in other criterion of optimization like minimum time maneuver or fuel, reaction wheel speed, and pointing accuracy.

#### 6. Conclusions

In this paper one develops a general 3D simulator nonlinear model, once it only depends on the inertia moment of the system. The MATLAB/simulink model is used to investigate large angle tracking maneuver in order to design a control algorithm based on the gas jet and reaction wheel, where the first actuator is used to reduce high angular velocity and the second one to perform fine pointing control. The switching control algorithm used to change from gas jet to reaction wheel action is based on the potential plus the kinetic energy of the system. Therefore, the transition between modes of operation occurs when the system reaches a certain level of energy. The nonlinear controller design uses the conjunction of the SDRE (State Dependent Riccati Equation) and SDRE filter methods to deal with high nonlinear simulator plant and system noise. Simulations have demonstrated the good performance and robustness of the SDRE controller to perform large angle tracking maneuver considering as project trade-off the settling time and fuel consumption. The investigation has also shown that SDRE control algorithm can be implemented in satellite onboard computer. The next step of this work is to compare the SDRE technique here developed with other nonlinear control methodology.

#### References

- L. C. G. Souza, “Robust control design for a flexible space system with mixed uncertain model,”
*Journal of the Brazilian Society of Mechanical Sciences and Engineering*, vol. 16, pp. 116–123, 1994. View at Google Scholar - C. D. Hall, P. Tsiotras, and H. Shen, “Tracking rigid body motion using thrusters and momentum wheels,”
*Journal of the Astronautical Sciences*, vol. 50, no. 3, pp. 311–323, 2002. View at Google Scholar · View at Scopus - I. Mainenti-Lopes, L. C. G. Souza, F. L. Sousa, and A. P. C. Cuco, “Multi-objective Generalized Extremal Optimization with real codification and its application in satellite attitude control,” in
*Proceedings of 19th International Congress of Mechanical Engineering (COBEM '09)*, Gramado, Brasil, 2009. - G. T. Conti and L. C. G. Souza, “Satellite attitude control system simulator,”
*Journal of Sound and Vibration*, vol. 15, no. 3-4, pp. 392–395, 2008. View at Google Scholar · View at Scopus - A. Y. Lee and J. A. Wertz, “In-flight estimation of the Cassini spacecraft's inertia tensor,”
*Journal of Spacecraft and Rockets*, vol. 39, no. 1, pp. 153–155, 2002. View at Google Scholar · View at Scopus - L. C. G. Souza, “Inertia parameters estimation of a satellite simulator,”
*Advances in Astronautical Sciences*, no. 1304, pp. 969–979, 2008. View at Google Scholar - X. C. M. Cubillos and L. C. G. Souza, “Using of H-infinity control method in attitude control system of rigid-flexible satellite,”
*Mathematical Problems in Engineering*, no. 1, pp. 1–10, 2009. View at Publisher · View at Google Scholar · View at Scopus - L. C. G. Souza, “Design of satellite control system using optimal nonlinear theory,”
*Mechanics Based Design of Structures and Machines*, vol. 34, no. 4, pp. 351–364, 2006. View at Publisher · View at Google Scholar · View at Scopus - T. D. Donald and R. J. Coultier, “Position and attitude control of a spacecrafts using the State-dependent riccati equation technique,” in
*Proceedings of the American Control Conference*, Chicago, Ill, USA, 2000. - G. R. Guidoni and L. C. G. Souza, “Application of the SDRE method to design an attitude control system simulator,”
*Advances in Astronautical Sciences*, no. 134, pp. 2251–2258, 2009. View at Google Scholar - P. K. Menon, T. Lam, L. S. Crawford, and V. H. L. Cheng, “Real-time computational methods for SDRE nonlinear control of missiles,” in
*Proceedings of the American Control Conference*, pp. 232–237, Anchorage, Alaska, USA, May 2002. View at Scopus - D. K. Parrish and D. B. Ridgely, “Attitude control of a satellite using the SDRE method,” in
*Proceedings of the American Control Conference*, Albuquerque, NM, USA, June 1997. View at Scopus - A. Isidori,
*Nonlinear Control Systems*, Springer, New York, NY, USA, 1995. - J. S. Shamma and M. Athans, “Analysis of gain scheduled control for nonlinear plants,”
*IEEE Transactions on Automatic Control*, vol. 35, no. 8, pp. 898–907, 1990. View at Publisher · View at Google Scholar · View at Scopus - J.-J. E. Slotine,
*Applied Nonlinear Control*, Prentice Hall, Englewood Cliffs, NJ, USA, 1991. - K. Zhou, J. Doyle, and K. Glover,
*Robust and Optimal Control*, Prentice Hall, Englewood Cliffs, NJ, USA, 1996. - J. R. Cloutier, C. N. D'Souza, and C. P. Mracek, “Nonlinear regulation and nonlinear H-infinity control via the state-dependent riccati equation technique: part 1. Theory,” in
*Proceedings of the 1st International Conference on Nonlinear Problems in Aviation and Aerospace*, Daytona Beach, Fla, USA, 1996. - J. R. Cloutier, “State-dependent Riccati equation techniques: an overview,” in
*Proceedings of the American Control Conference. Part 3 (of 6)*, Albuquerque, NM, USA, June 1997. View at Scopus