Time filter

Source Type

Li G.,Beijing Institute of Control Engineering | Li G.,Science and Technology on Space Intelligent Control Laboratory | Liu L.,Beijing Institute of Control Engineering
Chinese Journal of Aeronautics | Year: 2012

In this paper, we consider the coordinated attitude control problem of spacecraft formation with communication delays, model and disturbance uncertainties, and propose novel synchronized control schemes. Since the attitude motion is essential in non-Euclidean space, thus, unlike the existing designs which describe the delayed relative attitude via linear algorithm, we treat the attitude error and the local relative attitude on the nonlinear manifold-Lie group, and attempt to obtain coupling attitude information by the natural quaternion multiplication. Our main focus is to address two problems: 1) Propose a coordinated attitude controller to achieve the synchronized attitude maneuver, i.e., synchronize multiple spacecraft attitudes and track a time-varying desired attitude; 2) With known model information, we achieve the synchronized attitude maneuver with disturbances under angular velocity constraints. Especially, if the formation does not have any uncertainties, the designer can simply set the controller via an appropriate choice of control gains to avoid system actuator saturation. Our controllers are proposed based on the Lyapunov-Krasovskii method and simulation of a spacecraft formation is conducted to demonstrate the effectiveness of theoretical results. © 2012 Chinese Journal of Aeronautics.


Huang H.,Beijing Institute of Control Engineering | Huang H.,Science and Technology on Space Intelligent Control Laboratory
Chinese Control Conference, CCC | Year: 2015

The characteristic model-based golden-section adaptive control law (CM-GSAC) has been developed for over 20 years in China with a broad range of applications in various fields. This paper discusses the optimization of the control coefficients /1 and /2 such that the closed-loop system can tolerate the largest parameter estimation error. The Vinnicombe distance is introduced as a metric to evaluate the distance between the true CM and the estimated CM. According to the simulation results, system with CM-GSAC shows better tracking performance than that of the well known model-reference adaptive control and the multiple model adaptive control. © 2015 Technical Committee on Control Theory, Chinese Association of Automation.


Huang H.,Beijing Institute of Control Engineering | Huang H.,Science and Technology on Space Intelligent Control Laboratory
International Journal of Adaptive Control and Signal Processing | Year: 2015

The characteristic model-based golden-section adaptive control (CM-GSAC) law has been developed for over 20 years in China with a broad range of applications in various fields. However, quite a few theoretical problems remain open despite its satisfying performance in practice. This paper revisits the stability of the CM-GSAC from its very beginning and explores the underlying implications of the so-called golden-section parameter l2≈0.618. The closed-loop system, which consists of the CM and the GSAC, is a discrete time-varying system, and its stability is discussed from three perspectives. First, attentions have been paid to select the optimal controller coefficients such that the closed-loop system exhibits the best transient performance in the worst case. Second, efforts are made to improve the robustness in the presence of parameter estimation errors, which provide another choice when designing the adaptive controller. Finally, by measuring the slowly time-varying nature in an explicit inequality form, a bridge is built between the instantaneous stability and the time-varying stability. In order to relax the constraints on the parameter bounds of the CM, the GSAC is further extended to multiple CMs, which shows more satisfying tracking performance than that of the traditional multiple model adaptive control method. © 2014 John Wiley & Sons, Ltd.


Hu J.,Beijing Institute of Control Engineering | Hu J.,Science and Technology on Space Intelligent Control Laboratory | Zhang H.,Beijing Institute of Control Engineering | Zhang H.,Science and Technology on Space Intelligent Control Laboratory
Automatica | Year: 2013

The main contributions of this article are twofold. Firstly, a guidance law based on a nested saturation function combined with the I&I methodology is proposed for controlling VTOL vehicles subject to mass uncertainty and thrust saturation simultaneously. To simplify the calculations, the virtual attitude extracted from the guidance law is propagated through a command filter, the output of which is tracked by the attitude subsystem. The other contribution is that the influence of the command filter's frequency on the closed-loop system is rigorously analyzed. The main difficulty in proving the stability is that the command filter's tracking performance could not be guaranteed when the thrust force encounters the singularity problem. The study avoids this problem by utilizing the properties of nested saturation functions and establishes the semi-global ultimate boundness of the overall closed-loop system. Finally, simulations are presented to show the effectiveness of the proposed control scheme. © 2013 Published by Elsevier Ltd.


Zhang Z.,Beijing Institute of Control Engineering | Zhang Z.,Science and Technology on Space Intelligent Control Laboratory | Hu J.,Beijing Institute of Control Engineering
Science China Information Sciences | Year: 2011

In this work, we propose a pseudo four-degrees-of-freedom (DOF) prediction based guidance algorithm specifically for high-lift reentry vehicles. The algorithm is composed mainly of three parts. First, at the beginning of each guidance cycle, the 4-DOF predictor is called upon to predict the final downrange, crossrange, and heading errors. Then, the magnitude of the bank angle is determined from the downrange error, using the proportional-integral (PI) control method. Finally, two bank angle reversal time points are determined to minimize the crossrange and heading errors. Compared with traditional predictor-corrector guidance, the algorithm proposed does not require iterative procedures which significantly decreases the computational burden for the on-board computer and makes the implementation practical. Simulation results for dispersion tests demonstrated that our algorithm is computationally efficient and robust against uncertainties and disturbances. © 2011 Science China Press and Springer-Verlag Berlin Heidelberg.


Zhang Z.,Beijing Institute of Control Engineering | Zhang Z.,Science and Technology on Space Intelligent Control Laboratory | Hu J.,Beijing Institute of Control Engineering
Science China Information Sciences | Year: 2012

The closed loop attitude stability of a hypersonic vehicle controlled by the characteristic model-based all-coefficient adaptive controller is studied in this paper, and an algorithm based on the computation of induced matrix 1-norm or ∞-norm is proposed. First of all, the Taylor series expansion is applied to discretize the inputoutput description of the attitude dynamics of the vehicle. The obtained difference equations have the same structure as characteristic model; thus the intervals which contain all possible values of certain characteristic model parameters are obtained. When the linear feedback controller is used in the feedback loop, with some conservation, the closed loop system is viewed as a class of interval time-varying systems defined by a number of free time-varying parameters. These free parameters take values from predefined intervals. The sufficient and necessary condition for the stability of this class of system is given. Finally, a sufficient condition for the stability of hypersonic vehicle attitude control loop is proposed and demonstration example is presented. The method proposed checks up the stability of the closed loop system by evaluating a finite number of matrix norms, and overcomes the difficulties brought by the time-varying nature of the characteristic model and parameter estimation. © 2012 Science China Press and Springer-Verlag Berlin Heidelberg.


Jinchang H.,Beijing Institute of Control Engineering | Honghua Z.,Science and Technology on Space Intelligent Control Laboratory
International Journal of Robust and Nonlinear Control | Year: 2016

A simple control framework is proposed for the saturated attitude control of spacecraft subject to bounded disturbances. The framework is composed of three parts, that is, the quaternion part, the saturated angular velocity part, and the bounded anti-disturbance part. The anti-disturbance part can be different depending on the forms of disturbances. Based on a useful lemma, it can be proven that the saturation restriction on the angular velocity part can be removed in finite time, allowing us to analyze the closed-loop stability by means of the Lyapunov theory. Two different saturated controllers are presented to exemplify the applications of the control framework. Finally, simulations are conducted to demonstrate the effectiveness of the proposed controllers. © 2015 John Wiley & Sons, Ltd.


Huang H.,Beijing Institute of Control Engineering | Huang H.,Science and Technology on Space Intelligent Control Laboratory
Journal of Guidance, Control, and Dynamics | Year: 2015

The stability of an reusable launch vehicle (RLV) attitude system is discussed in the presence of reaction control system (RCS) allocation errors. The allowable bound of the RCS allocation error caused by the limited distinct quantization levels is measured by a sector bound in reference to a logarithmic quantizer. This sector bound further provides a guideline to deploy the thrusters upon different priorities. Meanwhile, during the RCS allocation, this stability criterion can also serve as a baseline when making the allocation choice, or when designing the lookup table.


Li G.,Beijing Institute of Control Engineering | Li G.,Science and Technology on Space Intelligent Control Laboratory | Liu L.,Beijing Institute of Control Engineering
Procedia Engineering | Year: 2012

We address the robust adaptive coordinated attitude control problem (CACP) for formation spacecraft with model and disturbance uncertainties, and with unknown constant time delays existing in the information exchanged channels. Here, spacecraft attitude is described via quaternion, and the local relative attitude is obtained in non-convex space, i.e., on the nonlinear manifold-Lie Group. Unlike in existing designs, where constant delays must be explicit and bounded, our novel laws, by injecting a nonlinear term, solve the CACP with disturbances and unknown/large constant communication delays. To overcome model uncertainties, the adaptive method is adopted. The closed-loop systems are investigated based on the Lyapunov-Krasovskii theory and Barbalat Lemma, and a spacecraft formation is conducted to demonstrate the effectiveness of theoretical results. © 2011 Published by Elsevier Ltd.


Wang Y.,Beijing Institute of Control Engineering | Wang Y.,Science and Technology on Space Intelligent Control Laboratory
Yuhang Xuebao/Journal of Astronautics | Year: 2012

In the course of the reentry of hypersonic vehicles, many difficulties such as strong coupling effects, drastic external disturbances, and large uncertainties of aerodynamic parameters make the design of guidance and control system very challenging. In response to that, the original nonlinear dynamics are transformed into the MIMO characteristic model in the form of two-order time-varying difference equations, and a decentralized adaptive attitude controller is designed. At last, the stability is proved and some simulations are presented. Because the closed-loop system is a very complex hybrid system, and a valid stability analysis has been absent in the characteristic modeling theory, the method proposed in this paper is used to absolutely handle the stability problem of MIMO system with a relative degree of two and without internal dynamics.

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