Spacecraft dynamics with regard to elastic gravitational stabilizer deployment

Dranovskii, V. I.; Khoroshylov, V.S.; Zakrzhevskii, A. E.

doi:10.1016/j.actaastro.2008.10.004

Cited by 4 publications

(4 citation statements)

References 14 publications

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“…12. Изменение углов отклонения гиродемпферов рой описано в работе [14]. Здесь было получено асимптотическое совпадение результатов.…”

Section: моделированиеunclassified

“…Работа [24] демонстрирует построение общей математической модели КА в процессе развертывания жесткого гравитационного стабилизатора по заданной программе. Динамика космического аппарата при развертывании упругого гравитационного стабилизатора изучена в работе [14].…”

Section: Introductionunclassified

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The dynamics of the spacecraft with gyro-gravity stabilization in the deployment of a flexible ring antenna

Zakrzhevskii¹,

Khoroshylov²

2011

Kosm. nauka tehnol.

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Section: моделированиеunclassified

Section: Introductionunclassified

The dynamics of the spacecraft with gyro-gravity stabilization in the deployment of a flexible ring antenna

Zakrzhevskii¹,

Khoroshylov²

2011

Kosm. nauka tehnol.

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“…The boom was deployed from a canister in the horizontal plane and was supported by a bungee cord tied with the slider at the ceiling of the building in order to compensate the gravitation. Dranovskii et al [18] stop at the development of general mathematical model of the SC during the deployment of the flexible gravitation stabilizer according to the specified programme.…”

Section: Introductionmentioning

confidence: 99%

Modelling of Spacecraft Dynamics at Deployment of Large Elastic Structure

Khoroshilov

Zakrzhevskii

2012

Modelling and Simulation in Engineering

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In this paper, a new approach to the modelling of the deployment dynamics of a flexible multi-body system with the time dependent configurations is demonstrated in the frame of the study the dynamics of a spacecraft with the gyro-gravitational system of stabilization. Primarily the gravitational stabilizer that is made as a pantograph structure is in a compact form. The deployment of a flexible pantograph structure is performed after placing the spacecraft into orbit and completion of the preliminary damping by a special jet-propelled system, and after uncaging the gyros. After its deployment, the pantograph turns into an elongated structure that serves as a gravitational stabilizer and carrier of solar batteries. The objective of the study is the creation of the generalized mathematical model and the conducting of the computational modelling of the spacecraft dynamics. The equations of motion are derived with the use of the Eulerian-LaGrangian formalism and symbolic computing. Numerical simulations of the typical operational mode of the system are conducted taking into account various control profiles for the deployment. Numerical results indicate that the system used for attitude stabilization ensures the shape of the deployed design and prescribed accuracy of the orientation.

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“…A general mathematical model of a spacecraft with a gravity-gradient boom that is being deployed in a programmed manner has been constructed in [2]. The dynamics of a spacecraft during the deployment of an elastic gravity-gradient boom was studied in [16]. The dynamics of a…”

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confidence: 99%

Dynamics of an Unstabilized Spacecraft During the Deployment of an Elastic Pantograph Structure

Zakrzhevskii

Khoroshilov

2014

Int Appl Mech

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An unstabilized spacecraft with a pantograph structure deployed in orbit to carry solar batteries is the subject of study. The objective of the study is to construct a mathematical model of this system taking into account the elastic properties of elements of the pantograph in longitudinal and transverse directions. This model is based on the Lagrangian formalism as applied to a mechanical system with rheonomic constraints. The expressions for the coefficients of the equations of motions are obtained using Mathematica 5 © . A Fortran application software package is used for numerical simulation of dynamic processes. This package can be adapted, if necessary, to study other structures. The behavior of the spacecraft during the deployment of the pantograph is numerically analyzed using different values of spacecraft parameters and the parameters of the deployment process in the gravity field.Introduction. The dynamics of reconfigurable systems is one of the promising and important research areas in mechanics [9,[11][12][13]23]. Modern spacecraft incorporate various components that are deployed in orbit (solar batteries (SB), gravity-gradient booms, antennas, etc.). Such mechanical systems are delivered to orbit compactly packaged and then are deployed there. There is literature on the deployment of elastic elements from a fixed base and from a spinning spacecraft [9,[11][12][13]23], including the deployment of a gravity-gradient boom [15,19]. In these studies, the maximum bending moments, deflections of booms, and optimal deployment time were assessed using various simplifying assumptions. Cherchas [14] studied the dynamics of spin-stabilized satellites during the extension of long flexible booms. He has determined the maximum nutation and precession angles after the deployment of the boom and its maximum bending moments and deflections, derived the equations of motion using Lagrange's equations, and discretized the elastic degrees of freedom by a modal analysis. In [20,21,24], the dynamics of deployable elastic elements is also described in terms a modal analysis with time-dependent natural modes.Banerjee and Kane [7] present a new method for simulating the motion of a beam that is being extruded from, or retracted into a rotating rigid body. In essence, the method consists of modeling the beam as a series of elastically connected rigid links and then working with equations of motion linearized in the modal coordinates for the links outside the rigid body. In [6,8], the analysis was extended to large deflections and used an order-n formulation for a variable number of bodies. The modeling has revealed that the tip deflections are very sensitive to the extrusion/retraction rate, the retraction process is less stable than the extrusion process, and the behavior of the beam is strongly dependent on the angular rate of the body.The deployment of such elements is a substantial perturbation to the motion of the spacecraft around its center of mass. It is impossible to model such perturbations within the framework of the...

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Spacecraft dynamics with regard to elastic gravitational stabilizer deployment

Cited by 4 publications

References 14 publications

The dynamics of the spacecraft with gyro-gravity stabilization in the deployment of a flexible ring antenna

The dynamics of the spacecraft with gyro-gravity stabilization in the deployment of a flexible ring antenna

Modelling of Spacecraft Dynamics at Deployment of Large Elastic Structure

Dynamics of an Unstabilized Spacecraft During the Deployment of an Elastic Pantograph Structure

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