Unloading angular momentum for inertial actuators of a spacecraft in the pitch channel

Bogachev, Alexey; Vorob'Eva, E. A.; Зубов, Н. Е.; Микрин, Е. А.; Мисриханов, М. Ш.; Ryabchenko, V. N.; Тимаков, С. Н.

doi:10.1134/s1064230711030075

Cited by 12 publications

(7 citation statements)

References 3 publications

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“…[ 1,1]  . We have to notice that for every real root from this segment there are four solutions (at the interval [0,2 )  ) of the system (22).…”

Section: Solutions In Permissible Regionmentioning

confidence: 99%

“…For example, in [1] the algorithm of angular motion synthesis for RW desaturation using gravitational torque is investigated, but the suggested technique is essentially differs from the one we describe here. In papers [2,3] another algorithm of RW desaturation using gravitational torque was suggested, but it requires unconstrained SC angular motion, while we consider solar pointed SC. There are also papers that suggest to use magnetic [4,5] and reactive [6] attitude control systems for RW desaturation.…”

Section: Introductionmentioning

confidence: 99%

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Reference angular motion synthesis for reaction wheels desaturation

Mashtakov

Tkachev

2017

KIAM Prepr.

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(Online) Mashtakov Y.V., Tkachev S.S. Reference angular motion synthesis for reaction wheels desaturationRecommended form of bibliographic references: Mashtakov Y.V., Tkachev S.S. Reference angular motion synthesis for reaction wheels desaturation // Keldysh Institute Preprints. 2017. No. 78. 28 p. doi:10.20948/prepr-2017 Y.V. Mashtakov, S.S. TkachevПостроение опорного углового движения для обеспечения разгрузки маховиков В работе рассматривается задача бестопливной разгрузки маховичной системы управления в режиме солнечной ориентации. Показано, что всегда можно подобрать такую ориентацию спутника, чтобы происходила разгрузка маховиков как при использовании момента сил давления солнечного излучения, так и при использовании гравитационного момента. Получены точные выражения для нахождения ориентации КА, обеспечивающей оптимальную разгрузку маховиков, а также приведены более простые формулы для построения близкой к оптимальной ориентации Ключевые слова: маховик, разгрузка, момент сил солнечного давления, гравитационный момент, ляпуновское управление Yaroslav Mashtakov, Stepan Tkachev Reference angular motion synthesis for reaction wheels desaturation The paper considers the problem of fuelless reaction wheels desaturation for a satellite in solar acquisition mode. It is shown that there is always angular motion in the vicinity of required one when reaction wheels can be desaturated either with the aid of solar pressure torque or gravitational one. Optimal desaturation attitude is found in close form. Additionally, near optimal simplified expressions for desaturation attitude are also presented.

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“…[ 1,1]  . We have to notice that for every real root from this segment there are four solutions (at the interval [0,2 )  ) of the system (22).…”

Section: Solutions In Permissible Regionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Reference angular motion synthesis for reaction wheels desaturation

Mashtakov

Tkachev

2017

KIAM Prepr.

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“…An approach to the synthesis of the attitude stabilization control laws in the roll-yaw channels pro posed in [2] and the application of the method presented in [3] for these coupled channels does not make it possible to synthesize decoupling control laws for attitude stabilization, which is important in control theory because the cross coupling of the channels is eliminated in this case. This study is devoted to the synthesis of decoupling laws for a spacecraft attitude stabilization.…”

Section: Introductionmentioning

confidence: 99%

“…This study is devoted to the synthesis of decoupling laws for a spacecraft attitude stabilization. Similarly to [2,3], the decoupling con trol laws must ensure the asymptotic stability and the prescribed stability margin.…”

Section: Introductionmentioning

confidence: 99%

“…In [2,3], the modal control laws for the attitude stabilization ensuring the asymptotic stability, a certain stability margin, and the gain explicitly dependent on the orbit parameters and mass-inertia characteris tics of the spacecraft were first obtained. For the coupled roll and yaw channels, this dependence is not explicit but is represented in terms of a functional relation between the gains in these control channels.…”

Section: Introductionmentioning

confidence: 99%

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