Deployment of a flexible beam from an oscillating base

Creamer, N. Glenn

doi:10.2514/3.20868

Cited by 9 publications

(10 citation statements)

References 8 publications

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“…, and all their derivatives with respect to time and generalized co-ordinates, which appear in the expressions for coefficients of the governing equations (5) and (7).…”

Section: Mathematical Model Of Systemmentioning

confidence: 99%

“…Having substituted the obtained expressions in (5) and (7) after completing them with suitable kinematic equations, one can formulate the Cauchy problem for study the of dynamics of the system under consideration during its deployment.…”

Section: Mathematical Model Of Systemmentioning

confidence: 99%

“…There is a large number of studies in the literature dedicated to the deployment of elastic appendages from the fixed basis as well as from the rotating SC [1][2][3][4][5][6], including the deployment of the gravity-gradient boom [7,8]. The maximum bending moments and the deflection of the booms at different simplifying hypothesis were evaluated in these papers; the optimization of the boom deployment timing was also fulfilled.…”

Section: Introductionmentioning

confidence: 99%

“…Zakrzhevskii and Khoroshilov [17] studied the dynamics of the orbital deployment of an elastic ring-shaped antenna taking into account dynamics of actuating drive. Creamer [7] studied the transverse motion of the truss boom deployed along an axis, in order to compare the theory and experiment. 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.…”

Section: Introductionmentioning

confidence: 99%

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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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“…, and all their derivatives with respect to time and generalized co-ordinates, which appear in the expressions for coefficients of the governing equations (5) and (7).…”

Section: Mathematical Model Of Systemmentioning

confidence: 99%

Section: Mathematical Model Of Systemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Modelling of Spacecraft Dynamics at Deployment of Large Elastic Structure

Khoroshilov

Zakrzhevskii

2012

Modelling and Simulation in Engineering

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“…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.…”

mentioning

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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