Optimal nonlinear feedback control for spacecraft attitude maneuvers

Carrington, Connie; Junkins, John L.

doi:10.2514/3.20073

Cited by 73 publications

(49 citation statements)

References 14 publications

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“…In Ref [8], we show several examples wherein 5th and 6th order expansions were routinely computed; analytical perturbation solutions above third order are very rare.…”

Section: The Pedestrian Expansionmentioning

confidence: 99%

“…(10)(11)(12) are dependent only upon the preceeding i-I expansion variables. Therefore, the nonhomogeneous term in each equation constitutes a known function of time and Eqs.…”

Section: T O I Tf 14)mentioning

confidence: 99%

“…7,8) and have found it to be most effective for a large family of nonlinear problems, including large degree of freedom systems.…”

Section: Casementioning

confidence: 99%

“…After determining the modal matrices, M and K" can be obtained from Eqs. I (10) elements of p) is requkred. Typically, the initial design point…”

Section: M) = [77 T M (1t) 7ti(t)] (61)mentioning

confidence: 99%

“…Thus, the present family of algorithms are designed to begin with the typical output of a conventional . (12)(13)(14). Attractive algebraic equations have been derived that explicitly determine these derivatives as "side where the conventional normalizations for the eigenvectors calculations" at much less computational expense than the are adopted as solution of the eigenvalue problem itself.…”

Section: B =B(c) H =H (B) G=g (G)mentioning

confidence: 99%

See 4 more Smart Citations

Optimization of Closed Loop Eigenvalues: Maneuvering, Vibration Control, and Structure/Control Design Iteration for Flexible Spacecraft.

Junkins¹

1986

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“…In Ref [8], we show several examples wherein 5th and 6th order expansions were routinely computed; analytical perturbation solutions above third order are very rare.…”

Section: The Pedestrian Expansionmentioning

confidence: 99%

“…(10)(11)(12) are dependent only upon the preceeding i-I expansion variables. Therefore, the nonhomogeneous term in each equation constitutes a known function of time and Eqs.…”

Section: T O I Tf 14)mentioning

confidence: 99%

“…7,8) and have found it to be most effective for a large family of nonlinear problems, including large degree of freedom systems.…”

Section: Casementioning

confidence: 99%

“…After determining the modal matrices, M and K" can be obtained from Eqs. I (10) elements of p) is requkred. Typically, the initial design point…”

Section: M) = [77 T M (1t) 7ti(t)] (61)mentioning

confidence: 99%

Section: B =B(c) H =H (B) G=g (G)mentioning

confidence: 99%

See 3 more Smart Citations

Optimization of Closed Loop Eigenvalues: Maneuvering, Vibration Control, and Structure/Control Design Iteration for Flexible Spacecraft.

Junkins¹

1986

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Spacecraft Anti‐Unwinding Attitude Control Using Second‐Order Sliding Mode

Tiwari

Janardhanan

un-Nabi

2017

Asian Journal of Control

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This paper presents an anti-unwinding control method for the attitude stabilization of a rigid spacecraft. Quaternion has double stable equilibrium and this may cause unwinding problems in spacecraft attitude control if both the equilibria are not considered in control design. Here, the initial condition of scalar quaternion is included in sliding surface and an anti-unwinding control method is formulated in second-order sliding mode. The presented second-order sliding mode controller can alleviate chattering and ensure a smooth control for actuator. Further, to eliminate the need of advance information about bounds of uncertainty and external disturbance, adaptive laws are applied to estimate the controller gains. The closed-loop stability is proved using the Lyapunov stability theory. In conclusion, a simulation is conducted in the presence of inertia uncertainty and external disturbances and it is found that the presented control method is efficient to negate the effect of inertia uncertainty and external disturbances, alleviate chattering, eliminate unwinding, and ensure high accuracy and steady state precision. P. M. Tiwari received his M.Tech and PhD in Control Engineering from Aligarh Muslim University Aligarh and Indian Institute of Technology Delhi in 2005 and 2016, respectively. Currently, he is a faculty with the Department of Electrical Engineering, Amity University Uttar Pradesh Noida. His research interests include sliding mode control, adaptive control, attitude control, and process control. S. Janardhanan received his M.Tech and PhD in Systems and Control Engineering from Indian Institute of Technology Bombay in 2002 and 2006, respectively. Currently, he is a faculty with the Department of Electrical Engineering, Indian Institute of Technology Delhi. He has over 100 publications in journals and conferences of international repute to his credit. His research interests include discrete-time systems, model order reduction, sliding mode control and robotics. M. Un-Nabi received his M.Tech and PhD in Control Engineering from Indian Institute of Technology Kanpur and Indian Institute of Technology Mumbai in 2003 and 2005, respectively. Currently, he is a faculty with the Department of Electrical Engineering, Indian Institute of Technology Delhi. He has around 60 publications in journals and conferences of international repute to his credit. His research interests include model order reduction, guidance and control, and sliding mode control.

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Global set stabilization of the spacecraft attitude control problem based on quaternion

Ding

2009

Intl J Robust & Nonlinear

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In this paper, we develop a global set stabilization method for the attitude control problem of spacecraft system based on quaternion. The control law that uses both optimal control and finite‐time control techniques can globally stabilize the attitude of spacecraft system to a set of equilibria. First, for the kinematic subsystem, we design a virtual optimal angular velocity. To obtain the global minimum of the performance index, this optimal angular velocity is only discontinuous in initial values. It can be regarded as a combination of open loop control and closed loop control. Then for the dynamic subsystem, we design a finite‐time control law that can force the angular velocity to track the virtual optimal angular velocity. It is proved that the closed loop system satisfies global set stability in the absence of disturbances. In the presence of disturbances, the system trajectory will converge to a neighborhood of the equilibrium set. Rigorous analysis shows that by introducing finite‐time control techniques, the closed loop system possesses a better disturbance rejection property. The control method is more natural and energy‐efficient. The effectiveness of the proposed method is demonstrated by simulation results. Copyright © 2009 John Wiley & Sons, Ltd.

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Optimal nonlinear feedback control for spacecraft attitude maneuvers

Cited by 73 publications

References 14 publications

Optimization of Closed Loop Eigenvalues: Maneuvering, Vibration Control, and Structure/Control Design Iteration for Flexible Spacecraft.

Optimization of Closed Loop Eigenvalues: Maneuvering, Vibration Control, and Structure/Control Design Iteration for Flexible Spacecraft.

Spacecraft Anti‐Unwinding Attitude Control Using Second‐Order Sliding Mode

Global set stabilization of the spacecraft attitude control problem based on quaternion

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