Optimal control of stretching process of flexible solar arrays on spacecraft based on a hybrid optimization strategy

Yao, Qijia; Ge, Xinsheng

doi:10.1016/j.taml.2017.05.002

Cited by 5 publications

(1 citation statement)

References 20 publications

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“…Figure 14c shows that Figure 15. Spacecraft, deploying solar arrays (17) . The method presented above can be extended to the actuation of all masses, including m x and m y .…”

Section: Suggestions On Some Practical Implementation Of the Inertialmentioning

confidence: 99%

Enhancement of the attitude dynamics capabilities of the spinning spacecraft using inertial morphing

Trivailo

Kojima

2019

Aeronaut. j.

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ABSTRACTIn the previous works by the authors, an efficient method of control of the inversion of the spinning spacecraft was proposed. This method was prompted by the Dzhanibekov’s Effect or Tennis Racket Theorem, which are often seen by many as odd or even mysterious. For the spacecraft, initially undergoing periodic flipping motion, proposed method allows to completely stop these flips by transferring the unstable motion into the regular stable spin. Similarly, the method allows activation of the flipping motion of the spacecraft, which is initially undergoing its stable spin. In this paper, spacecraft designs, which have inertial morphing capabilities, are considered and their advantages are further investigated. For general formulation, the ability of the spacecraft to change its inertial properties, associated with all three principal axes of inertia, are assumed. For simulation of these types of spacecraft systems, extended Euler’s equations are used and peculiar dynamics of the spacecraft is illustrated with a several study cases. Complex spacecraft attitude dynamics manoeuvres, using geometric interpretation, employing angular momentum spheres and kinetic energy ellipsoids, are considered in detail. Contributions of the inertial morphing to the changes of the shape of the kinetic energy ellipsoid are demonstrated and are related to the resultant various feature manoeuvres, including inversion and re-orientation. A method of reduction of the compound rotation of the spacecraft into a single stable predominant rotation around one of the body axes was proposed. This is achieved via multi-stage morphing and employing proposed instalment into separatrices. Implementation of the morphing control capabilities are discussed. For the periodic inversion motions, calculation of the periods of the flipping motion, based on the complete elliptic integral of the first kind, is performed. Flipping periods for various combinations of inertial properties of the spacecraft are presented in a systematic way. This paper discusses strategies to the increase or reduction the flipping and/or wobbling motions. A discovered asymmetric ridge of high periods for peculiar combinations of the inertial properties is discussed in detail. Numerous examples are illustrated with animations in virtual reality, facilitating explanation of the analysis and control methodologies to a wide audience, including specialists, industry and students.

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“…Figure 14c shows that Figure 15. Spacecraft, deploying solar arrays (17) . The method presented above can be extended to the actuation of all masses, including m x and m y .…”

Section: Suggestions On Some Practical Implementation Of the Inertialmentioning

confidence: 99%

Enhancement of the attitude dynamics capabilities of the spinning spacecraft using inertial morphing

Trivailo

Kojima

2019

Aeronaut. j.

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Control strategy of optimal deployment for spacecraft solar array system with initial state uncertainty

Chen

Yao

2018

Appl. Math. Mech.-Engl. Ed.

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Dynamic modeling of spacecraft solar panels deployment with Lie group variational integrator

Bai

2018

Theoretical and Applied Mechanics Letters

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Optimal control of stretching process of flexible solar arrays on spacecraft based on a hybrid optimization strategy

Cited by 5 publications

References 20 publications

Enhancement of the attitude dynamics capabilities of the spinning spacecraft using inertial morphing

Enhancement of the attitude dynamics capabilities of the spinning spacecraft using inertial morphing

Control strategy of optimal deployment for spacecraft solar array system with initial state uncertainty

Dynamic modeling of spacecraft solar panels deployment with Lie group variational integrator

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