Observer-Based Robust Control for Spacecraft Rendezvous with Thrust Saturation

Wan, Neng; Liu, Ming; Karimi, Hamid Reza

doi:10.1155/2014/710850

Cited by 6 publications

(10 citation statements)

References 41 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Meanwhile, the noncircularity matrix ΔA in model (9) satisfies the matched condition, 18 ΔA=DF(t)E, which will bring us some convenience in controller synthesis. 33,35,46…”

Section: Dynamical Model and Problem Formulationmentioning

confidence: 99%

“…However, some similar procedures for synthesizing a coupled controller can be found in various studies. 33–35,51 With the same parameters assigned in previous sections, the control vector in equation (54b) for coupled control scheme is generated by ucc(t)=-Kccx(t), where the state feedback gain matrix Kcc is …”

Section: Illustrative Examplementioning

confidence: 99%

“…Interested readers can refer to Li et al., 31,32 Yang and Gao, 33 and Wan et al. 34–37 for more results on this topic. Nevertheless, to the best of the authors’ knowledge, most of the existing literatures either neglected the control task of out-of-plane motion or synthesized a coupled rendezvous controller that regulated the in-plane and out-of-plane motions jointly.…”

Section: Introductionmentioning

confidence: 99%

“…Yang et al (2012) considered the spacecraft rendezvous with thrust nonlinearity and sampled-data control. Wan et al (2013) put forward a robust tracking control method for relative position holding and rendezvous with actuator saturation in near-circular orbits; and in another paper of Wan et al (2014), they provided an observer-based control scheme for spacecraft rendezvous.…”

mentioning

confidence: 99%

See 3 more Smart Citations

Partially independent control scheme for spacecraft rendezvous in near-circular orbits

Wan

Yao

Fang

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

View full text Add to dashboard Cite

Due to the complexity and inconstancy of the space environment, accurate mathematical models for spacecraft rendezvous are difficult to obtain, which consequently complicates the control tasks. In this paper, a linearized timevariant plant model with external perturbations is adopted to approximate the real circumstance. To realize the robust stability with optimal performance cost, a partially independent control scheme is proposed, which consists of a robust anti-windup controller for the in-plane motion and a H ∞ controller for the out-of-plane motion. Finally, a rendezvous simulation is given to corroborate the practicality and advantages of the partially independent control scheme over a coupled control scheme.Widely applied to crew exchange, large-scale assembly, spacecraft maintenance, docking, interception, formation flying and other astronautic missions involving more than one spacecraft, autonomous spacecraft rendezvous has been regarded as a crucial operational technology in aerospace engineering. As the autonomous control scheme is a cardinal and decisive issue that determines the success of the rendezvous, it has been and continues to be an engaging area of study.Most of the mathematical models employed in investigating spacecraft rendezvous are derived from the two-body problem. Because of their concise and linearized form, Clohessy-Wiltshire equations (Clohessy and Wiltshire, 1960) were favored by many researchers, though this model was initially developed to describe the rendezvous in circular orbits. The models put forward by De Vries (1963) and Tschauner (1967) extended our knowledge to the rendezvous in elliptical orbits; however, nonlinear terms were involved, which circumscribed their broader implementations in control engineering.Considering the fact that most of the rendezvous missions were conducted in near-circular orbits with small eccentricities, researchers began to search for some eclectic models that are linearized and sufficiently precise. A comprehensive survey on these efforts was given by Carter (1998); nevertheless, all the linearization results introduced in this literature are in terms of either the true or eccentric anomaly of one spacecraft and require the solution of the Kepler problem, which is time and computational consuming. A time-explicit dynamical model overcoming this defect was first introduced by Anthony and Sasaki (1965), and a more recent development on time-explicit models was contributed by Melton (2000). Robust guaranteed cost control was first raised by Chang and Peng (1972) to optimize preassigned cost function, and many of the following literatures were carried out based on their works. Petersen and McFarlane (1994) synthesized a state feedback guaranteed cost controller via a Riccati equation approach. Yu and Chu (1999) designed a guaranteed cost controller for linear uncertain time-delay systems via a linear matrix inequality (LMI) method. Esfahani and Petersen (2000) solved the guaranteed cost output feedback control problem in a matrix substitution ma...

show abstract

“…Meanwhile, the noncircularity matrix ΔA in model (9) satisfies the matched condition, 18 ΔA=DF(t)E, which will bring us some convenience in controller synthesis. 33,35,46…”

Section: Dynamical Model and Problem Formulationmentioning

confidence: 99%

Section: Illustrative Examplementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

See 2 more Smart Citations

Partially independent control scheme for spacecraft rendezvous in near-circular orbits

Wan

Yao

Fang

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

View full text Add to dashboard Cite

show abstract

“…They introduce a new Lyapunov approach, so the controller design problem can be transferred into a convex optimization problem subject to linear matrix inequality (LMI) constraints [11]. Wan et al proposes an observer-based robust guaranteed cost control method for thrust-limited rendezvous in nearcircular orbits [12]. There are also some scholars proposing a dynamic control allocation strategy based on the theory of robust predictive control, in view of the actuator output polyhedron uncertainty problems [13,14].…”

Section: Introductionmentioning

confidence: 99%

Robust Control Allocation among Overactuated Spacecraft Thrusters under Ellipsoidal Uncertainty

Duan

Zhang

Zhao

et al. 2014

Abstract and Applied Analysis

View full text Add to dashboard Cite

Spacecrafts with overactuated and redundant thrusters can work normally once some of them are out of work, which improves the reliability of spacecraft in orbit. In this way, the desired command of controller needs to be dynamically allocated among thrusters. Considering that uncertain factors may appear in forms of dynamics, installation errors, thrust deviations, or failures, this paper proposes a robust control allocation under ellipsoidal uncertainty. This method uses the uncertainty ellipsoid set to describe the uncertainty of the thrusters firstly and establish the thrust allocation robust reference model and then transforms it into a cone optimization model which can be solved as an optimized problem. Finally, this paper adopts the interior-point method for solving the optimization problem. In this way, difficulties of solving the problem caused by parameter uncertainties are avoided effectively. Finally, we take satellite rendezvous and docking as simulation scenarios; it is verified that the cumulative distribution error and maximum error can be reduced by more than 15% when the random error of control efficiency matrix is 5%–20%; also, precision of thruster allocation is improved.

show abstract

Full-and Reduced- Order Compensator for Innosat Attitude Control

2015

View full text Add to dashboard Cite

This paper presents a study on the estimator based on Linear Quadratic Regulator (LQR) control scheme for Innovative Satellite (InnoSAT). By using LQR control scheme, the controller and the estimator has been derived for state space form in all three axes to stabilize the system’s performance. This study starts by converting the transfer functions of attitude control into state space form. Then, the step continues by finding the best value of weighting matrices of LQR in order to obtain the best value of controller gain, K. After that, the best value of L is obtained for the estimator gain. The value of K and L is combined in forming full order compensator and in the same time the reduced order compensator is also formed. Lastly, the performance of full order compensator is compared to reduced order compensator. From the simulation, results indicate that both types of estimators have presented good stability and tracking performance. However, reduced order estimator has simpler equation and faster convergence to zero than the full order estimator. This property is very important in developing a satellite attitude control for real-time implementation.

show abstract

Observer-Based Robust Control for Spacecraft Rendezvous with Thrust Saturation

Cited by 6 publications

References 41 publications

Partially independent control scheme for spacecraft rendezvous in near-circular orbits

Partially independent control scheme for spacecraft rendezvous in near-circular orbits

Robust Control Allocation among Overactuated Spacecraft Thrusters under Ellipsoidal Uncertainty

Full-and Reduced- Order Compensator for Innosat Attitude Control

Contact Info

Product

Resources

About