An approach to dynamics and control of orbiting flexible structures

Modi, V. J.; Suleman, Afzal; Ng, Alfred; Morita, Yasuhiro

doi:10.1002/nme.1620320813

Cited by 37 publications

(2 citation statements)

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“…Then Ness and Farrenkopf [2] and Ho and Gluck [3] introduced the effects of the non-linearity. Later various, different approaches were presented by several authors (Modi and Suleman [4], Pascal and Silya [5], but also Kane, Meirovitch (perturbation technique), and Ho again), each of them with own advantages and drawbacks. Generally, two ways could be followed (Eulerian and Lagrangian approaches) to write down the dynamic model of a multibody (Santini and Gasbarri [6]).…”

Section: Introductionmentioning

confidence: 99%

Determination of kinematic state of an orbiting multibody using GNSS signals

2009

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Section: Introductionmentioning

confidence: 99%

Determination of kinematic state of an orbiting multibody using GNSS signals

2009

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“…The development of vibration suppression attitude control requires a proper dynamical model to accurately represent the dynamics of the spacecraft, of the flexible appendages and of the internal liquids. The dynamics of large flexible spacecrafts was studied since the 1970 with the works of Ho [3] and Modi [4,5] introducing the multibody representation of a spacecraft composed of flexible interconnected bodies forming a tree-type topology. However, a comprehensive theory dealing with the vibrational motion of a generic flexible body attached to a reference frame undergoing an arbitrary translational and rotational motion was missing.…”

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confidence: 99%

Integrated vibration suppression attitude control for flexible spacecrafts with internal liquid sloshing

Colagrossi

Lavagna

2020

Multibody Syst Dyn

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Vibration suppression during attitude control is a fundamental research topic whenever control of the rotational motion of a spacecraft with flexible appendages and internal liquid sloshing is of interest. The proposed method is based on an attitude control system with centralized sensors and actuators, without the usage of collocated devices for vibration management. In this way, it is possible to develop and implement a computationally efficient real-time control system that is suitable for any kind of spacecraft, even with advanced control capabilities. An integrated vibration suppression attitude control is designed and analyzed, exploiting also a numerical simulation verification procedure based on validated code. The developed attitude control system applies two fundamental control schemes: classical proportional-derivative (PD) control, with nonadaptive band-stop filters, and wave-based control. The proposed wave-based control implementation allows managing three-dimensional attitude dynamics in steady state pointing, without cross-coupling between the separate body axes. To overcome this limitation, the paper presents the integration of the wave-based control with the filtered PD control scheme, allowing us to have a complete three-dimensional real-time MIMO controller, with vibration suppression capabilities and robustness to system uncertainties. The paper also presents the development of an accurate dynamical model of a generic flexible spacecraft with internal liquid sloshing based on a multibody formulation. Keywords Flexible spacecrafts • Internal liquid sloshing • Vibration suppression • PD attitude control • Wave-based attitude control 1 Introduction Vibration suppression during attitude control of flexible spacecrafts with internal liquid sloshing is an active research topic intriguing the space engineering community for many B A. Colagrossi

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Implementation of the Boundary Element Method in the Dynamics of Flexible Bodies

Amirouche

1996

Int. J. Numer. Meth. Engng.

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SUMMARYThis paper presents the implementation of the Boundary Element Method in the dynamics of flexible multibody systems. Kane's equations are used to formulate the governing boundary initial value problem for an arbitrary three-dimensional elastic body subjected to large overall base motion. Using continuum mechanics principles, direct boundary element incremental formulations are derived. The Galerkin approach was employed to generate the weighted residual statement which serves as a transitory point between continuum mechanics and boundary integral equations. By adapting the updated Langrangian formulation for large displacements analysis and using the Maxwell-Betti reciprocal theorem, integral representations for geometric stiffening were also derived. The non-linear terms were found to be functions of the time-variant stresses associated with the inertial forces at the reference configuration. The domain integrals arising from body forces (such as gravitational loads, inertia loads and thermal loads, etc.) are presented as DRM integrals (Dual-Reciprocity Method). Using the substructuring technique the elastic body is divided into several regions leading to a system of equations whose matrices are sparse (block-banded). The linearized equations of motion were discretized along the boundary of the body, and an algorithm for the integration involving the Houbolt method was used to establish an algebraic system of pseudo-static equilibrium equations. A Newton-Raphson-type iteration scheme was used to solve these discretized balance equations. To take advantage of the sparsity of the matrices, special routines were used to decompose and solve the resulting linear system of equations.An illustrative example is presented to demonstrate the validity of the method as well as how the effects of geometric stiffening effects are captured. The example consists of spin-up manoeuvre of a tapered beam attached to a moving base. The beam was modelled as two-dimensional plane strain problem divided into a number of substructures. Numerical simulation results show how the phenomenon of dynamic stiffening is captured by the present approach.

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An approach to dynamics and control of orbiting flexible structures

Cited by 37 publications

References 14 publications

Determination of kinematic state of an orbiting multibody using GNSS signals

Determination of kinematic state of an orbiting multibody using GNSS signals

Integrated vibration suppression attitude control for flexible spacecrafts with internal liquid sloshing

Implementation of the Boundary Element Method in the Dynamics of Flexible Bodies

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