Robustness Evaluation of Theta-D Technique for Spacecraft Attitude Control Subject to Reaction Wheel Failures

Lam, Quang M.; Xin, Ming; Introduction, I.

doi:10.2514/6.2010-8302

Cited by 17 publications

(6 citation statements)

References 5 publications

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“…The satellite attitude pointing and control system is re-used from the study conducted by Lam and Xin (2010). For convenience, we re-describe the SDRE design of a GEO satellite with four reaction wheels mounted in a pyramid configuration.…”

Section: A Sdre Based Controller Formulationmentioning

confidence: 99%

A View of SDRE Control Methods as One Branch of Indirect Adaptive Control

Lam

Xin

Cloutier

2012

Infotech@Aerospace 2012

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Current popular State Dependent Riccati Equation (SDRE) control methods, which have recently received a lot of attention in the control community, have been perceived as one branch of adaptive control. Their ability to re-compute the controller gain in real time based on the State Dependent Coefficient (SDC) matrix pair [A(x(t)), B(x(t))] can be viewed as an equivalent approach to the indirect adaptive control design paradigm. The SDC pair captures new knowledge of the vehicle's dynamics from the dynamic state vector signatures without explicitly relying on an onboard parameter estimator. This paper presents such a view with a detailed comparison using an architecture-based functional block diagram to justify that observation. The premise that SDRE control methods can be viewed as an equivalent Indirect Adaptive Control DesignMethodology (i.e., self tuning regulator (STR) with an onboard parameter estimator) is supported by the following statement. SDRE design methods adaptively compute the gain matrix via an approximation to the Hamilton Jacobi Bellman (HJB) based optimization process (i.e., self tuning aspect) using an implicit on-board parameter estimator. This is virtually achieved by having the SDRE actual state vector x(t) driving the SDC pair [A(x(t)), B(x(t))] as the provider of new knowledge which is supplied to the controller tuning process. A satellite attitude pointing and control system is used to illustrate the comparison of both architectures and simulation assessments. The results from this example lead to the conclusion that the SDRE method is truly one branch of Indirect Adaptive Control. Discussion of the SDRE control performance as an indirect adaptive controller is provided to facilitate practitioners use of this design methodology for problems requiring adaptive control and to facilitate theorists to further solidify this thinking.

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Section: A Sdre Based Controller Formulationmentioning

confidence: 99%

A View of SDRE Control Methods as One Branch of Indirect Adaptive Control

Lam

Xin

Cloutier

2012

Infotech@Aerospace 2012

Self Cite

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“…The under-actuated control application of SDRE design was also explored by Lam and Xin (2010) for a commercial GEO satellite pointing control evaluation. The study is not yet completed; however, the early results are very encouraging.…”

Section: Sdre Applicability To Actuator Failures and Under-actuatementioning

confidence: 99%

SDRE Control Stability Criteria and Convergence Issues: Where Are We Today Addressing Practitioners' Concerns?

Lam

Xin

Cloutier

2012

Infotech@Aerospace 2012

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This paper has three purposes: 1) to provide a survey on the State-Dependent Riccati Equation (SDRE) stability analysis methodologies developed to date; these stability analysis techniques produce either a guarantee or a high degree of confidence that the closed-loop system is asymptotically stable over a domain of interest, 2) to present an argument that practical rules of thumb can be just as important as theoretical stability proofs with regard to real world implementation, and 3) to justify support of the above argument using some forms of actual implementation. The paper neither favors any particular stability analysis technique nor introduces a new stability analysis framework. Rather it presents a view of stability reasoned judgment and practical justification for actual implementation. The reasoned judgment and justification are mainly based on the space access vehicle control and the satellite attitude control examples whose performance becomes unstable in the presence of high gain magnitude conditions. The fundamental argument of this new view (i.e., reasoned judgment and justification) is that for even linear and static gain controllers such as the Linear Quadratic Regulator (LQR), stability of the system depends on the operational domain under practical implementation with nonlinear limiters in the loop. Therefore, for a variable gain or nonlinear controller like the SDRE method, the task of determining a region of stability either practically or theoretically is much more difficult as compared to a linear LQRbased approach. The SDRE designs of a space access vehicle control, a helicopter flight control, and a satellite attitude control are presented with a set of practical rules defined and applied to it as a practical design benchmark problem on how to pass the SDRE stability concern gate. The paper concludes with the recommendation of some practical design rules of thumb for practitioners

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“…However, it is not easy to establish an accurate mathematical model of RLV and the controller design for RLV is challenging, as there are enormous amounts of model parameter uncertainties and external disturbances in which atmospheric disturbances is a significant component. [1][2][3] Several approaches for the controller design of RLV have been conducted over a period of time, for example, gain scheduling, 4 dynamic inversion technique, [5][6][7] back-stepping control, [8][9][10] theta-D, [11][12][13] statedependent Riccati equation strategy, 14,15 and trajectory linearization control. [16][17][18][19][20] However, these research works mentioned above have not taken atmospheric disturbances into account, which cannot be ignored both in theory and practice.…”

Section: Introductionmentioning

confidence: 99%

Nonsingular terminal sliding mode control for reusable launch vehicle with atmospheric disturbances

You

Zong

Tian

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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The controller design for reusable launch vehicles is challenging due to enormous amounts of model parameter uncertainties and atmospheric disturbances. This paper first derives six-degree-of-freedom model of a reusable launch vehicle with atmospheric disturbances. Next, four kinds of atmospheric disturbances are introduced and wind models are established respectively. For attitude control of the reusable launch vehicle, a nonsingular terminal sliding mode controller is designed with stability guaranteed. Finally, simulation results show a satisfactory performance for the attitude tracking of the reusable launch vehicle with atmospheric disturbances.

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Robustness Evaluation of Theta-D Technique for Spacecraft Attitude Control Subject to Reaction Wheel Failures

Cited by 17 publications

References 5 publications

A View of SDRE Control Methods as One Branch of Indirect Adaptive Control

A View of SDRE Control Methods as One Branch of Indirect Adaptive Control

SDRE Control Stability Criteria and Convergence Issues: Where Are We Today Addressing Practitioners' Concerns?

Nonsingular terminal sliding mode control for reusable launch vehicle with atmospheric disturbances

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