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- Table of Contents
Mathematical Problems in Engineering
Volume 2013 (2013), Article ID 902452, 11 pages
Observer-Based Stabilization of Spacecraft Rendezvous with Variable Sampling and Sensor Nonlinearity
1Research Center of Satellite Technology, Harbin Institute of Technology, Harbin 150001, China
2Department of Engineering, Faculty of Technology and Science, University of Agder, 4898 Grimstad, Norway
Received 10 July 2013; Accepted 19 August 2013
Academic Editor: Hongli Dong
Copyright © 2013 Zhuoshi Li et al. 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.
This paper addresses the observer-based control problem of spacecraft rendezvous with nonuniform sampling period. The relative dynamic model is based on the classical Clohessy-Wiltshire equation, and sensor nonlinearity and sampling are considered together in a unified framework. The purpose of this paper is to perform an observer-based controller synthesis by using sampled and saturated output measurements, such that the resulting closed-loop system is exponentially stable. A time-dependent Lyapunov functional is developed which depends on time and the upper bound of the sampling period and also does not grow along the input update times. The controller design problem is solved in terms of the linear matrix inequality method, and the obtained results are less conservative than using the traditional Lyapunov functionals. Finally, a numerical simulation example is built to show the validity of the developed sampled-data control strategy.
Sampled-data systems, involving a continuous-time system and a discrete controller implemented via sample-and-hold elements, have received significant attention from control theorists mostly due to related performance problems which have arisen in practice [1–5]. Over the past few decades, three main approaches have been broadly employed for sampled-data systems [6–8]. The first one is the lifting technique method, wherein the investigated plant is converted into infinite-dimensional discrete system equivalently. The second one is the hybrid approach, where the sample-data plant is described in terms of hybrid discrete/continuous models. In this setting, the solution is derived via differential Riccati equations with jumps . The third one is the input delay approach, wherein the digital control signal is represented as delayed input between two sampling instants [10, 11]. This approach has been extended to deal with nonuniform uncertain sampling [12, 13]. Furthermore, this approach has been improved and incorporated with the impulsive system method to achieve less conservative results for stability analysis and controller/filter design . Based on this approach, recently a new type of discontinuous Lyapunov functionals has been developed in [14, 15] to deal with sampled-data systems. In this approach, the values of the proposed discontinuous Lyapunov functionals are discontinuous at the input update times, but a decrease is guaranteed due to its special and interesting construction.
On the other hand, autonomous rendezvous becomes more and more significant for many future astronautic missions such as intercepting, repairing, saving, docking, large-scale structure assembling, and satellite networking. In the past decades considerable attention has been devoted to autonomous rendezvous, and a few results have been reported [16, 17]. In fact, when the target orbit is approximately circular and the distance between them is much smaller than the orbit radius, the relative motion between two neighboring spacecrafts can be described by C-W equations, which were introduced by Clohessey and Wiltshire [16, 18, 19]. In recent years, based on the C-W equations, a few results have been developed for the control problem of relative motion between two neighboring spacecraft [20, 21]. In particular, the sampled-data control problem of relative position holding has been studied for spacecraft rendezvous with thrust nonlinearity .
In realistic engineering system, sensors and actuators cannot provide unlimited amplitude signal since the physical, safety or, technological constraints always occur and exhibit inevitably [23–26]. Due to the theoretical significance and practical importance of saturation phenomenon, the related problems of saturation filtering and control have been extensively investigated [27, 28]. However, the associated results for sensor saturation have been relatively few which may be due to the technical difficulty [29–33]. On the other hand, in practical autonomous rendezvous, the simultaneous presence of sensor saturations and sampling is quite typical and exhibit frequently and is desired to be investigated for control and filtering problems. Although sampled-data control problem of autonomous rendezvous has begun to draw some research attention, there have been very limited papers that take sensor saturations and sampling phenomenon into account, and the purpose of this paper is therefore to shorten such a gap.
In this paper, we investigate the problem of observer-based guaranteed cost control of spacecraft rendezvous in the presence of nonuniform sampling and sensor saturation. Motivated by the aforementioned discontinuous Lyapunov functionals [12, 15], an improved time-dependent Lyapunov functional approach will be proposed in this paper. Sufficient conditions for the stability analysis of the closed-loop system and the controller design are provided in terms of the new designed Lyapunov functionals approach, which is further shown to have less conservativeness than the traditional approaches.
The remaining part of this paper is organized as follows. In Section 2, the problem of sampled-data control of spacecraft rendezvous is formulated. In Section 3, the sufficient condition for the exponential stability of the closed-loop system is provided, and the sufficient conditions for the existence of the sampled-data guaranteed cost controller are given. Finally, a simulation result is illustrated in Section 4 to show the validity of the developed control strategy.
2. Problem Formulation
In the orbital coordinate frame of chaser and target spacecrafts, it is well known that the origin attaches to the mass center of the target spacecraft; -axis is along the vector from the earth center to the origin; -axis is along the target orbit circumference; -axis completes the right-handed frame; denotes the radius of the target circular orbit; denotes the gravitational parameter of the earth; denotes the angle velocity of the target; and .
Based on Newton’s motion theory, the relative dynamic model of chaser and target spacecrafts can be modeled by the following C-W equations: where , , and are the components of the relative position in corresponding axes and () is the th component of the control input vector. By the talar expansion and linearization approach, the linearized equation around the null solution is given by where is the mass of the chaser and () is the relative motion dynamic. We define the following vector and matrices: then the C-W equation (1) can be described equivalently as follows:
As seen in (5), the specific relative motion of the chaser and target can be prevailed by designing .
It is supposed that the signals are sampled before transmitted to the controller side. Define as a strictly increasing sequence of sampling times in for initial time . We also assume that the sampling internals between any two neighbour sampling instants satisfy where is a known constant. Therefore, the signal received in the observer and controller side is of the form at the sampling instant . The observer dynamics are thus designed as follows: Define the error vector as then we have
During the orbital transfer process, the thrust constraint always satisfies the following: where is the control input thrust along the th axis at the sampling instant and is the maximum allowed thrust along the th axis.
As pointed out in Section 1, a large number of realistic engineering applications will inevitably result in the nonlinear characteristic of sensors. Therefore, in this work, we use to denote the actuator nonlinearity, which belongs to for some given diagonal matrices , with , and . In particular, satisfies the following sector condition: In light of (11), the nonlinear function can be decomposed into a linear and a nonlinear part: and the nonlinearity satisfies , where the set is defined as
Substituting (12) into (5) yields Designing the control scheme as one can obtain As a result, the following overall closed-loop system is obtained: Consider the following performance index function: where and are known matrices with appropriate dimensions.
The objective of this paper now can be formulated as follows.
Problem 1. Design a sampled-data control law , such that the following conditions are met:(1)the closed-loop system (17) is exponentially stable with a given decay rate ; (2)the control input satisfies the given upper bound (10);(3)the performance index function (18) has an upper bound.
3. Main Results
In this Section, we will first perform the stability analysis and control scheme design for system (17). Furthermore, we will present the design scheme of the guaranteed cost controller for system (17). Consider the system (17), we design the state feedback gain and observer gain such that and are Hurwitz. We provide the following Theorem.
Theorem 2. Consider the closed-loop system (17) with and designed previously, given a decay rate ; if there exist positive definite matrices , , , and , and matrices , , , , and such that the following matrices conditions hold: where then system (17) is exponentially stable with the decay rate .
Proof. For system (17), consider the following Lyapunov functional: , where
In formula (4), () and are Lyapunov matrices to be designed, and is the decay date as previous defined. It can be calculated that
Notice that ; thus
Therefore it is derived that
Considering , it is shown that
For , it can be calculated that
As a result, we have
We define the following variable:
and it is derived that
By Jensen’s inequality, it can be shown that
In particular, for , it can be verified that the following holds:
Therefore, it is shown from (30) that
We now insert free-weighting matrices by introducing the following zero terms:
where the free-weighting matrices , , , , , , and are to be designed. Also, from (13) it is known that
Then we have
Define the following new augmented variables:
It is calculated that
We now consider the matrices and defined in (19) and (20). In fact, it can be verified that is obtained from with deleting the th row and the th column, and . Similar to the proof of Theorem 1 of , it can be proved that the system (17) is exponentially stable.
Next, we deal with the input constraint along each axis. We define Then, the thrust along each axis can be described as Therefore, the thrust constraint (10) can be rewritten as which is equivalent to Furthermore, formula (45) is equal to which is further equivalent to On the other hand, based on the previous analysis, it is known that is guaranteed if the matrix conditions (19) and (20) hold. Subsequently, holds for any . It is therefore reasonable to assume that there exists a scalar such that Notice that , and , . Therefore, it is true that which implies that In fact, (50) can be rewritten as It is noted that, if condition (21) holds, then It can be implied from (52) that As a result, the thrust limitation (10) can be guaranteed. This completes the proof.
In Theorem 2, the sufficient condition under which the observer-based controller exists has been established. However, the performance index function (18) has not been considered there. In the following discussion, we will investigate the design problem of guarantee cost controller. We now, in the performance index function (18), notice that ; thus We present the following theorem, which presents a sufficient condition for the existence of the guaranteed cost controller for the closed-loop system (17).
Theorem 3. Consider the closed-loop system (17) with and designed previously, given a decay rate ; if there exist positive definite matrices , , , and and matrices , , , , and , such that the matrix conditions (19), (20), and (21) and the following conditions holdwhere all the symbols are as previously defined, then system (17) is exponentially stable with the decay rate , and the performance index function (18) satisfies
Proof. Consider the term where is defined as in (4). It is known from Theorem 2 that, if conditions (19), (20), and (21) hold, then is guaranteed for . On the other hand, if (55) holds, it is easy to prove that for . Integrating both sides of (57) yields or equivalently Therefore, one can obtain Since , holds. Hence, it can be concluded that for . This completes the proof.
In this section, a simulation example will be shown to illustrate the usefulness and advantage of the proposed sampled-data control approach. We suppose that the mass of the chaser is kg, and the target is moving along a geosynchronous orbit with radius km with an orbital period of h. The angle velocity rad/s. Suppose that , for (the maximum thrust along each axis). The angle velocity rad/s. In the coordinate based on the target frame, assume that the initial state is , and the desired holding position is . The matrices involved with control thrust nonlinearity are chosen as , ; the matrices and related to performance index (18) are chosen as , ; the upper bound of the sampling period is s; the decay rate is chosen as . Design the state feedback gain and observer gain as such that both and are Hurwitz. Suppose that , which means that the first sampling time instant is the initial time. The designed parameter is chosen as . Solving the matrices conditions (19), (20), and (21) in Theorem 2 and (55) in Theorem 3, it is found that there exists feasible solution. Then, it can be derived that . Therefore, the condition (48) () holds in this case, and the obtained solution is correct and feasible. The simulation results are provided in Figures 1, 2, 3, and 4, which show that the trajectory of state vector is asymptotically stable.
In this paper, we have investigated the observer-based sampled-data control problem for spacecraft rendezvous with sensor nonlinearity. The classical Clohessy-Wiltshire equation is used to describe the mathematical model of spacecraft rendezvous. A discontinuous Lyapunov functional approach is presented to pursue a less conservative condition for the stability analysis and controller design. Future work will focus on more complicated cases; for instance, the effects of communication delay, packet losses, and signal sampling are taken into account simultaneously.
This work was partially supported by the National Natural Science Foundation of China 61104101, the Fundamental Research Funds for the Central Universities, the China Postdoctoral Science Foundation funded project (2011M500058), the Special Chinese National Postdoctoral Science Foundation under Grant 2012T50356, and the Heilongjiang Postdoctoral Fund (LBH-Z11144).
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