Dynamics of Large Flexible Multibody Structures in Space
Dynamics of Large Flexible Multibody Structures in Space
The scope of this work has been the development of an efficient method for the dynamics modelling of structural systems in category II missions in space. Specified by NASA, category II missions will employ large-scale articulated multibody structural systems of complex interconnected flexible and rigid components. Typical examples include space-science laboratories, earth-observation platforms and space-station configurations.
As opposed to the direct application of the finite element method for the dynamics modelling of an entire structure as a single entity, structural systems in this work have been modelled as collections of interacting components. It is required that the method should provide high accuracy, though low order mathematical models, and amongst other critical advantages, should be computationally more efficient than the global finite element approach. A recursive Lagrangian formulation of generalised coordinates was considered the most efficient methodology for the modelling objectives specified. The recursive nature permits the formulation of kinematical expressions relative to the inboard component and results in a minimal set of differential equations of motion. Component linear elastic deformation is approximated using spatial discretisation techniques with a small number of component modes. Several component mode sets, combinations of dynamic and static modes, have been proposed or adapted from the area of component-mode synthesis. Truncation of the system order can be achieved at substructural level, by reducing the number of component modes, resulting in low order mathematical modes.
A number of methods have been developed and thoroughly assessed on the suitability for the dynamics modelling of category II systems. The fittest of the methods, which directly utilises the finite element component matrices, has been shown to be computationally faster than the global finite element approach over a large number of case studies. A network of custom developed programs, based on this method, has been generated and interfaced to a commercial finite element code for modelling complex aerospace structures.
University of Southampton
Mantikas, Nikolaos
c01681ce-143f-47ca-bd7c-baf413eb7aa8
2001
Mantikas, Nikolaos
c01681ce-143f-47ca-bd7c-baf413eb7aa8
Mantikas, Nikolaos
(2001)
Dynamics of Large Flexible Multibody Structures in Space.
University of Southampton, Doctoral Thesis.
Record type:
Thesis
(Doctoral)
Abstract
The scope of this work has been the development of an efficient method for the dynamics modelling of structural systems in category II missions in space. Specified by NASA, category II missions will employ large-scale articulated multibody structural systems of complex interconnected flexible and rigid components. Typical examples include space-science laboratories, earth-observation platforms and space-station configurations.
As opposed to the direct application of the finite element method for the dynamics modelling of an entire structure as a single entity, structural systems in this work have been modelled as collections of interacting components. It is required that the method should provide high accuracy, though low order mathematical models, and amongst other critical advantages, should be computationally more efficient than the global finite element approach. A recursive Lagrangian formulation of generalised coordinates was considered the most efficient methodology for the modelling objectives specified. The recursive nature permits the formulation of kinematical expressions relative to the inboard component and results in a minimal set of differential equations of motion. Component linear elastic deformation is approximated using spatial discretisation techniques with a small number of component modes. Several component mode sets, combinations of dynamic and static modes, have been proposed or adapted from the area of component-mode synthesis. Truncation of the system order can be achieved at substructural level, by reducing the number of component modes, resulting in low order mathematical modes.
A number of methods have been developed and thoroughly assessed on the suitability for the dynamics modelling of category II systems. The fittest of the methods, which directly utilises the finite element component matrices, has been shown to be computationally faster than the global finite element approach over a large number of case studies. A network of custom developed programs, based on this method, has been generated and interfaced to a commercial finite element code for modelling complex aerospace structures.
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Published date: 2001
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Local EPrints ID: 464620
URI: http://eprints.soton.ac.uk/id/eprint/464620
PURE UUID: 086c33b0-4d7b-4da7-8376-14ddadb74551
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Date deposited: 04 Jul 2022 23:51
Last modified: 16 Mar 2024 19:39
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Author:
Nikolaos Mantikas
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