Arbitrary large-angle satellite attitude maneuvers using an optimal reaction wheel power criterion

Skaar, Steven B.; Kraige, L. G.

doi:10.2514/6.1982-1470

Cited by 7 publications

(6 citation statements)

References 2 publications

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“…6a, is undesirable for any practical application, even though the resulting control torque is unaffected. Not only would this create unnecessary mechanical stresses, but such oscillations would be more likely to excite undesirable elastic modes in the spacecraft [4]. Note that the wheels oscillate between the saturated torques at 1 Nm.…”

Section: B Numerical Implementationmentioning

confidence: 96%

“…Some strategies achieve the minimum power usage goal by working directly to minimize the integral of the wheel motor power over the course of a maneuver. By applying variational methods, the optimal wheel torque trajectory is determined numerically given a priori information about the initial and final states required by the maneuver [4]. In contrast, the present work is not considering maneuver-wide power-optimal solutions, as these require a priori knowledge of initial and final attitude states.…”

Section: Introductionmentioning

confidence: 98%

“…When considering small spacecraft with limited resources, an important performance objective is the optimization of the attitude control system load on the power system. These power-optimal controls generally focus on minimizing the energy used over the course of an entire maneuver [4][5][6], although some aim to instantaneously minimize the power consumption [7]. There has been considerable interest (dating to the 1960s) in incorporation of energy storage capability into commonly used attitude control systems, since the reaction wheels and controlmoment gyroscopes are ideal for use as flywheels.…”

Section: Introductionmentioning

confidence: 99%

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Regenerative Power-Optimal Reaction Wheel Attitude Control

Blenden

2012

Journal of Guidance, Control, and Dynamics

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This paper develops an analytical instantaneous power-optimal attitude control for a spacecraft using an integrated reaction wheel-flywheel system allowing for energy storage and return. The control is formulated in a general manner to use an arbitrarily large number of reaction wheels. It is applicable to systems with redundant wheels spanning three-dimensional space, which are controlled by a general attitude control law. The instantaneous power usage is minimized by modifying the wheel control torques using the wheel torque null motion. In this study, reducing the wheel speed results in negative power usage with perfect energy recuperation. Applying the maximum available wheel torque constraints, the null torque solution space is reduced to a hyperdimensional vector geometry problem, and the power-optimal wheel control torques are uniquely determined. The control modifications are applied to both attitude regulation and tracking control laws, demonstrating its performance for a variety of initial spacecraft states. Not only does the new control maximize the energy extraction from the reaction wheels, it also maintains the smallest flywheel spin rates, which helps reduce the maneuver-wide power usage.

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Section: B Numerical Implementationmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

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Regenerative Power-Optimal Reaction Wheel Attitude Control

Blenden

2012

Journal of Guidance, Control, and Dynamics

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“…Many open-loop control strategies have been developed for large angle maneuvers 1 ' 2 . However these open-loop schemes are generally sensitive to spacecraft parameter uncertainties, unexpected disturbances and initial attitude rates.…”

Section: Introductionmentioning

confidence: 99%

Adaptive Asymptotic Tracking of Spacecraft Attitude Motion with Inertia Matrix Identification

Ahmed

Coppola

Bernstein

1998

Journal of Guidance, Control, and Dynamics

319

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The problem of a spacecraft tracking a desired trajectory is defined and addressed using adaptive feedback control. The control law, which has the form of a sixth-order dynamic compensator, does not require knowledge of the inertia of the spacecraft. A Lyapunov argument is used to show that tracking is achieved globally. A simple spin about the intermediate principal axis and a coning motion are commanded to illustrate the control algorithm. Finally, periodic commands are used to identify the inertia matrix of the spacecraft.

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“…Several articles (Windeknecht, 19631 Kumar, 1965, 19661 Dixon et al, 19701 BourdacheSiguerdidjane, 19911 Scrivener andThomson, 19941 Skaar andKraige, 1984) have been published on the de-tumbling of a rigid spacecraft. In these works, only the dynamic equations are considered, and the objective is to reduce the angular velocity vector of the spacecraft to zero.…”

Section: Introductionmentioning

confidence: 99%

Time-Optimal De-tumbling Control of a Rigid Spacecraft

Chao

2008

Journal of Vibration and Control

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Abstract:The problem of time-optimal de-tumbling control (TODTC) of a rigid spacecraft moving between two attitudes is studied in this article. Unlike conventional approaches, which involve solving a set of differential equations, a novel numerical method is introduced. In the proposed method, by fixing the count of control steps and treating the sampling period as a variable, the TODTC problem is formulated as a nonlinear programming (NLP) problem by utilizing an iterative procedure. Generating initial feasible solutions systematically is also discussed, since these are usually needed in solving a NLP problem. In this manner, the optimization process of the NLP problem can be started from many different points when searching for the optimal solution. Simulation results are included, to show the feasibility of the proposed method.

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Arbitrary large-angle satellite attitude maneuvers using an optimal reaction wheel power criterion

Cited by 7 publications

References 2 publications

Regenerative Power-Optimal Reaction Wheel Attitude Control

Regenerative Power-Optimal Reaction Wheel Attitude Control

Adaptive Asymptotic Tracking of Spacecraft Attitude Motion with Inertia Matrix Identification

Time-Optimal De-tumbling Control of a Rigid Spacecraft

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