Mathematical Problems in Engineering

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Volume 2020 |Article ID 6285912 | https://doi.org/10.1155/2020/6285912

Meng Duan, Yingmin Jia, "Finite Time Output Feedback Attitude Tracking Control for Rigid Body Based on Extended State Observer", Mathematical Problems in Engineering, vol. 2020, Article ID 6285912, 12 pages, 2020. https://doi.org/10.1155/2020/6285912

Finite Time Output Feedback Attitude Tracking Control for Rigid Body Based on Extended State Observer

Guest Editor: Jing Na
Received07 May 2020
Accepted08 Jun 2020
Published26 Jul 2020

Abstract

In this paper, the attitude tracking control problem of output feedback is investigated. A finite time extended state observer (FTESO) is designed through the homogeneous Lyapunov method to estimate the virtual angular velocity and total disturbances. Based on these estimated states, a finite time attitude tracking controller is developed. The numerical simulations are given to illustrate the effectiveness of the proposed control scheme.

1. Introduction

Recently, the issue of attitude control of rigid body has received more and more attention due to its wide practical applications such as spacecraft, robotics, and maglev planar motor [13]. Also, the complex nonlinearity of the attitude dynamics raises potential value in theory. A great deal of control methods have been proposed to deal with the attitude control problems.

In [3], two time-varying terminal sliding mode attitude control algorithms were designed to deal with the system uncertainties and external disturbances. In [4], an adaptive regulation technique was proposed to reject the disturbances whose frequency is unknown. In [5], another adaptive attitude tracking control was implemented for the stability of a rigid spacecraft with time-varying inertia components. In [6], a backstepping method was used to design the robust attitude control for the agile satellite.

Various attitude control algorithms above need the information of full states including attitudes and angular velocities for controller design. However, in actual engineering applications, due to energy cost, weight, and other factors, an angular velocity sensor cannot be installed in the mechanical systems, or the angular velocity sensors fail to work. Thus, the design of output feedback attitude control in which just attitude measurements are available is required.

Many great research studies have been proposed to deal with the problem of output feedback attitude control. These methods can be divided into two strategies: the passivity-based controller and the observer-based controller. In [7], the passivity of attitude dynamics represented by quaternion was first proved and a passivity-based attitude control was proposed to guarantee the stability of rigid body attitude. This work was further researched in [8]; the passivity of attitude dynamics represented by modified Rodrigues parameters was proven. In [9], an auxiliary dynamical system was derived to compensate the unknown angular velocities. In [10], a passivity filter which adopted attitude Euler angles was introduced; compared to other passivity-based controllers, the proposed output feedback controller can deal with external disturbances.

The examples of observer-based attitude controller can be found in [1114]. In [11], a finite time observer was proposed through geometric homogeneity and Lyapunov methods; a virtual angular velocity is introduced in this method. In [12], a continuous finite time angular velocity observer was designed, but the settling time could not be given. In [13], an observer was designed by adding a power integrator, thus the settling time can be estimated and the disturbances could be rejected by this method. In [14], a continuous terminal sliding mode observer was designed.

However, the u-modeled system dynamics and external disturbances are also the difficulties in the attitude control design. In [1517], the unknown dynamics and external disturbances are addressed by simple structure estimators for nonlinear systems. Extended state observer (ESO) is another method to compensate these problems. The main characteristic of ESO is that all disturbances and uncertainties can be regarded as total disturbances. The linear ESO (LESO) was introduced in [18] and the structure of ESO became more concise and simple, thus ESO is preferred by engineering applications whose plants are too complex [1921].

Inspired by [22, 23], a FTESO is introduced for the attitude control without angular velocity in this paper. The main contributions of this article are listed as follows:Compared with other observer-based controllers, the presented control scheme can estimate angular velocity and disturbances of system simultaneously. The disturbances of the attitude system can be compensated by the outputs of proposed FTESO when the attitude controller is designed.A finite time attitude controller which combined with FTESO is designed; it is an improvement of [11]. Due to the introduction of ESO, the proposed control framework has higher control accuracy and faster response.

This article is organized as follows. In Section 2, system dynamical models, some definitions, and lemmas are shown; the proposed FTESO-based controller is shown in Section 3; simulations are given in Section 4 and Section 5 shows the conclusions and future work.

2. System Models and Preliminaries

2.1. Equations of Attitude Kinematics and Dynamics

In this section, attitude system equations of a rigid body, which include attitude kinematics and dynamics, are presented.

The modified Rodrigues parameters (MRPs) are introduced to express the attitude of the rigid body; the equations of attitude kinematics are given as follows:where is the MRPs which denotes the rotation from the body frame to the inertial frame and is the angular velocity of the rigid body expressed in the body frame. The matrix is defined as follows:where the operator represents the skew symmetric matrix of vector and has the following form:

The attitude dynamics of rigid body is modeled as:where denotes the control torque, denotes the external disturbances applied to the rigid body, and denotes the inertial matrix of the rigid body which is symmetric.

Denote that , , is the first time derivative of the attitude MRPs and is introduced as the virtual angular velocity, then equations (1) and (3) can be transformed to the following equations:where is defined as system function, , , and are the external disturbances in system equation (4).

2.2. Definitions and Lemmas

For simplicity, some definitions about vector are given:where represents the signum function and represents the diagonal matrix.

Lemma 1 (see [24]). For any , .

Lemma 2 (see [25]). For any , , .

Lemma 3 (see [22]). Consider the system like equation (4); assume that a Lyapunov function is defined on a neighbourhood of of the origin, andwhere . Then, the system is locally finite time stable, and the which starts from can arrive at in finite time :where is the starting value of , and denotes the Gaussian hypergeometric function.

3. Main Results

3.1. Finite Time Extended State Observer Design

In this section, only the attitude MRPs is the available information; an ESO which ensures finite time convergence is presented to estimate the virtual angular velocity and the external disturbances .

Designate the external disturbances as an extended state ; the system in equation (4) can be transformed to a new third-order dynamics equation which is shown in the following formulas:where , and the following assumption is given.

Assumption 1. The external disturbances are unknown but continuously differential and bounded; its first time derivative is also unknown and bounded; the following inequalities hold:where and represent the upper bound of and , respectively.
Let , and represent the estimates of , and in equation (7), respectively, then the FTESO is designed as follows:where represents the estimation error of attitude MRPs , , , , , and , and , , and are the parameters to deal with the external disturbances.
Let , , and the error dynamical equations of the proposed FTESO is expressed as:The following compact set is constructed for any constant :This compact set can be easily obtained by designing a proper desired attitude reference trajectory. If the set is established, there will exist a positive constant such that .
The stability properties of the extended state observer is presented in the following theorem.

Theorem 1. Consider the error dynamical system given by equation (10), where , , , ; if the compact set holds, , , , and are sufficiently large, then the estimation errors would converge to a residual region in finite time.

Proof. Consider the error dynamics in equation (10); ignore the terms , , and , so equation (10) can be reduced to the following form:It can be acquired that equation (12) is homogeneous of degree with respect to the weight .
The Lyapunov function is proposed as follows:where , denotes a positive definite symmetric matrix. Make represent the vector field of system equation (12); it can be obtained that and are homogeneous of degrees and with the same weights in system equation (12), respectively.
According to [26, 27], the inequality is obtained as follows:where , , and .
Same as the previous analysis, ignore the terms , , and . The other homogeneous system can be got from equation (10):Similarly, the system of equation (15) is homogeneous of degree with respect to the weight .
Define the same Lyapunov function as equation (13) as follows:where , , denotes a positive definite symmetric matrix. Make represent the vector field of system equation (15); it can be obtained that and are homogeneous of degrees and with the same weights in system equation (15), respectively.
Once again the following inequality is derived according to [26, 27]where , , and .
Considering the error dynamics in equation (10), the following Lyapunov function is chosen aswhere , , denotes a positive definite symmetric matrix same as in equations (13) and (16), then take first time derivative of :Substituting equations (14) and (17) into equation (19), the following formula can be got:where refers to the maximum eigenvalue of matrix .
The following inequality is derived according to Lemma 1:where, and the following result is got:The following inequality is derived according to Lemma 2:The following inequalities can be derived in the same way according to Lemma 2:So, substituting equations (22)–(25) into the inequality equation (20), the following inequality can be got:whereTwo cases are discussed in further analysis.Case 1. .Consider the parameters in equation (26):So, simplify equation (26) to the following formula:where ; select the parameter sufficiently large to ensure ; according to Lemma 3, the Lyapunov function will converge to in finite time .where denotes the initial value of .Case 2.. In this case, equation (26) can be simplified towhere the parameter is selected to ensure that .From inequality equation (30), when , the Lyapunov function will converge to the residual region in finite time :where represents the value of at time . The estimation error can be written asIn next step, the parameters , and will be analyzed to ensure converge to zeros within finite time.
Define the following Lyapunov function:Take time derivative of :According to equation (33), will converge to the bounded region , and then selecting the parameter , the inequality equation (35) can be simplified toSo, can converge to zeros within time :where is the value of at time .
So, is got; according to [28], discontinuous terms include that can be considered as equivalent input; the error dynamical system equation (10) can be reduced toIt can be derived that . Define the Lyapunov function and . Analyze these two Lyapunov functions like we did before; it can be easily obtained that, let and , the estimation errors and will converge to zeros within finite time and , respectively [11]:where denotes the value of at time denotes the value of at time .
At this point, the proof is complete.

3.2. Finite Time Attitude Controller Design Based on FTESO

In this section, inspired by Zou [11], a finite time controller is introduced to stabilize the rigid body to the desired attitude. Because only the attitude measurement is available, the estimation of virtual angular velocity and external disturbances are utilized in the design procedure.

Define and , where , , , and and are positive odd integers.

The proposed finite time attitude controller is shown as follow:

Theorem 2. Consider the system expressed in equation (4); if finite time control torque in equation (40) combined with FTESO in equation (9) is employed, the desired attitude can be tracked within finite time.

Proof. Define the Lyapunov function:where is defined asTaking time derivative of Lyapunov function , the result can be got as follows:In this section, just the terms and need to be derived. After tedious derivation, it could be obtained thatwhere .
Substitute the control torque equation (40) into equation (47). The can be derived as follows:Combining equation (48) with equations (42) and (46),Choose and letwhere is the positive constant. The following inequality is obtained:where .
Notice thatHence, the following inequality is obtained:where .
According to Lemma 2:where .
From equations (45) and (54),According to Theorem 1, would converge to zeros in finite time, so equation (55) becomesBecause , the tracking errors converge to zeros in finite time [11].
The proof is completed.

Remark 1. In practical situations, due to the absence of certain parameters, the system function can not be calculated accurately. To deal with this problem, the system function and external disturbances can be regarded as total disturbances . The control algorithm proposed in this article can be written as

Remark 2. In order to eliminate the chattering issue caused by discontinuous terms in the observer and controller, the signum function can be replaced by the following function:where and are constants which can be designed.

4. Simulation Results

In this section, several numerical simulations are implemented to show the effectiveness of the FTESO-based control scheme proposed in this paper; meanwhile, the control scheme with general LESO and the control scheme without ESO in reference [11] are introduced as comparisons.

The initial states are designed as , , . The desired attitude trajectory is designed as , and the external disturbances . The parameters of the proposed ESO and controller are , , ,