[PDF] Dynamics And Control Of Multi Body Tethered Satellite Systems Microform eBook

Author : Mehdi Keshmiri
Publisher :
Page : 428 pages
File Size : 38,83 MB
Release : 1995
Category :
ISBN :

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"Among the external forces, the aerodynamic forces and their effects on the dynamics and stability of the system are given more attention. The free molecular flow model is used to calculate the aerodynamic forces resulting from the material damping of the tethers are considered in this investigation. These forces, which are very difficult to model accurately, are modelled using a viscous damping model." --

Author : Vladimir Aslanov
Publisher : Elsevier
Page : 356 pages
File Size : 32,95 MB
Release : 2012-10-16
Category : Science
ISBN : 0857096001

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Aimed at engineering students and professionals working in the field of mechanics of space flight, this book examines space tether systems – one of the most forward-thinking directions of modern astronautics. The main advantage of this technology is the simplicity, profitability and ecological compatibility: space tethers allow the execution of various manoeuvers in orbit without costs of jet fuel due to the use of gravitational and electromagnetic fields of the Earth. This book will acquaint the reader with the modern state of the space tether’s dynamics, with specific attention on the research projects of the nearest decades. This book presents the most effective mathematical models and the methods used for the analysis and prediction of space tether systems’ motion; attention is also given to the influence of the tether on spacecraft’s motion, to emergencies and chaotic modes. Written by highly qualified experts with practical experience in both the fields of mechanics of space flight, and in the teaching Contains detailed descriptions of mathematical models and methods, and their features, that allow the application of the material of the book to the decision of concrete practical tasks New approaches to the decision of problems of space flight mechanics are offered, and new problems are posed

Author : Nasrollah Monshi
Publisher :
Page : 260 pages
File Size : 13,2 MB
Release : 1992
Category :
ISBN :

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"The first analytical method that is used for the development of reel rate laws is the Liapunov's second method. In this work it is shown that the Hamiltonian can be used as a Liapunov function. A reel rate law is devised that stabilizes the in-plane and out-of-plane librations at the same time, for two-body systems. However, since the resulting motion has some deficiencies, this reel rate law is not extended to multi-body systems." --

Author : Panfeng Huang
Publisher : Springer Nature
Page : 288 pages
File Size : 17,49 MB
Release : 2019-11-18
Category : Technology & Engineering
ISBN : 9811503877

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This book offers a comprehensive overview of recently developed space multi-tethers, such as maneuverable space tethered nets and space tethered formation. For each application, it provides detailed derivatives to describe and analyze the mathematical model of the system, and then discusses the design and proof of different control schemes for various problems. The dynamics modeling presented is based on Newton and Lagrangian mechanics, and the book also introduces Hamilton mechanics and Poincaré surface of section for dynamics analysis, and employs both centralized and distributed controllers to derive the formation question of the multi-tethered system. In addition to the equations and text, it includes 3D design drawings, schematic diagrams, control scheme blocks and tables to make it easy to understand. This book is intended for researchers and graduate students in the fields of astronautics, control science, and engineering.

Author : Gangqiang Li
Publisher :
Page : 0 pages
File Size : 40,50 MB
Release : 2019
Category :
ISBN :

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This doctoral research conducts high-fidelity multiphysics modeling for tethered spacecraft systems, such as electrodynamic tether systems, electric solar wind sail systems, and tether transportation systems with climbers. Two models are developed based on nodal position finite element method. The first model deals with the tethered spacecraft system with fixed length tether, while the second model deals with the tethered spacecraft system with variable tether length using an arbitrary Lagrangian-Eulerian description. First, the nodal position finite element method is applied to model the orbital motion of tethered spacecraft systems with fixed tether length over a prolonged period. A Symplectic integration scheme is employed to attenuate the accumulation of error in the numerical analysis due to the long-term integration for tethered spacecraft systems, such as the space debris deorbit by electrodynamic tethers. A high fidelity multiphysics model is developed for electrodynamic tether systems by considering elastic, thermal, and electrical coupling effects of the tether. Most importantly, the calculation of electron collection by the electrodynamic tether is coupled with the tether libration and flexible deformation, where the orbital motion limited theory for electron collection is discretized simultaneously by the same finite element mesh used for the elastodynamic analysis of tether. The model is then used to investigate dynamics and libration stability of bare electrodynamic tethers in deorbiting end-of-mission spacecraft. Second, the model of tethered spacecraft system with fixed tether length is extended for the modeling of electric solar wind sail systems. The coupling effect of orbital and self-spinning motions of electric solar wind sail systems is investigated together with the interaction between the axial/transverse elastic motion of tether and Coulomb force. A modified throttling control algorithm is implemented in the finite element scheme to control the attitude motion of electric solar wind sail systems through the electric voltage modulation of main tethers. Third, the model of tethered spacecraft with variable tether length is applied to handle the tether length variation in tether transportation systems. The tether length variation results from the climber moving along tether and deployment and retrieval of tether at end spacecraft. The dynamic behavior of tether transportation systems with single or multiple climbers in characterized and the effectiveness of libration suppression scheme is tested by the high-fidelity model.

Author : Amit Sanyal
Publisher : LAP Lambert Academic Publishing
Page : 204 pages
File Size : 48,30 MB
Release : 2011-09
Category :
ISBN : 9783846502921

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Multibody spacecraft are used in a wide range of applications in near-Earth space, from manned space stations to unmanned space telescopes. Such systems cannot be modeled as point mass particles. Their dynamics are quite complex, being characterized by linear and nonlinear coupling between different degrees of freedom. This work explores how such dynamical coupling can be used to make changes in orbit and attitude using internal motions in a controlled manner. The methods outlined here lead to control maneuvers for multibody spacecraft without using chemical fuel. With increasing risks to space assets in Earth orbits from space debris, such control methods are both timely and valuable.

Author : Hans Troger
Publisher : CRC Press
Page : 247 pages
File Size : 15,6 MB
Release : 2010-04-29
Category : Technology & Engineering
ISBN : 1439836868

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During many of the earliest American and Russian space missions, experiments were performed using cables to connect people and objects to spacecraft in orbit. These attempts generated considerable information about the formation of tethered systems and basic problems with tether orientation and gravity-gradient stabilization. During the 1970s, inte

Author : Royce L. Abel
Publisher :
Page : 200 pages
File Size : 34,93 MB
Release : 2005
Category : Astronautics
ISBN :

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"Tethered Satellite Systems (TSS) has been an ongoing project around the world for many decades. This study examined the dynamics an dcontrols of tethered satellites. The equations of motion were developed and simulated with no control and small eccentric orbits. A control law was derived by associating the Hamiltonian of the system to a Lyapunov Funciton. This control law was then simulated to demonstrate ability and robustness. The tethered system can be retrieved and deployed in a small number of orbits, and return from a perturbation quickly. Examination of a non thruster controlled system resulted in asymptotic convergence in retrieval and station keeping, but the inplane angle, orbital plane, converged during deployment. Time to complete the phases was similar to out of plane thruster controlled. The maximum eccentricities were found for retrieval and deployment when the system started at the perihelion of the orbit with a 100Km tether. Drag was added to the model because it effects the dynamics when the subsatellite is very close to earth. Most of the effects are seen in the inplane angle. At fully deployed the inplane angle was small. A Lyapunov controller for tether satellites works very well under ideal conditions. Once aerodynamics are included into the model, offsets and oscillations occur because of the new forces that unbalance the system compared to the model without drag"--Abstract.