The theory is developed by considering space structures having a branched configuration near the centre of which are located attitude sensors and actuators collocated with an orthogonal control axis set to be orientated.
It is well known that the complete set of space structures comprises two subsets, o. Other papers in this volume. Registered in England as a limited company No. Connect with WIT Press:. Toggle navigation. My Basket. Search Papers Books.
Large Space Structures: Dynamics and Control by S.N. Atluri, Paperback | Barnes & Noble®
All Papers Books Advanced. Paper DOI. Author s V. We have developed algorithms for wavefront correction of a single mirror which will be tested on this hardware. Figure 1. Exploded view of 10 cm deformable mirror. We are developing thermally and mechanically stable thin film mirrors which can be placed on the same type of actuating layers developed in i. These thermally stable films are based on a tessellation of Al and Ti regions with specific geometries that allow us to tailor the coefficient of thermal expansion of the lattice.
We have developed a technique for separating the mirror from the Si substrate on which it is initially formed by a process involving vapor deposition and deep reactive ion etching, Figure 2.
We have studied the mechanical properties of the constituent materials of the mirror Al and Ti by means of nanoindentation experiments. We have developed computer models that predict the response of a thin film mirror to actuation and other loading schemes using finite element simulations.
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We have set up a simulation model for a seven-spacecraft system using rigid body and propulsion models of available hardware. We have used this model to derive and verify an optimal control strategy for reconfiguration. We have developed strategies for electromagnetic docking and verified the feasibility of magnetic-only docking within half a meter separation, based on electromagnetic rods arranged near the four corners of a face of the docking spacecraft, Figure 3.
Figure 3. Nanosatellite with four electromagnetic docking rods; simulation of maximum stress during latching. We have constructed a laboratory testbed using a frictionless air table and overhead visual telemetry system; it includes a propulsion base for validating the control laws and for simulating orbital disturbances, Figure 4.
We are currently developing an inter-spacecraft machine vision system for relative telemetry and integrating the visual processing, control, and docking algorithms with hardware that will be provided by the University of Surrey. We are studying the dynamics of docking, latching, and assembly of multiple small satellites into a single aperture.
Catalog Record: EVA assembly of a large space structure element | HathiTrust Digital Library
To this end, we have developed a toolkit that allows us to robustly and efficiently model non-smooth, non-convex , and multiple contact situations in stiff systems. This includes a novel collision detection algorithm that can be stated as a linear program for non-smooth bodies, and hence can model collisions between satellites with complex shapes. We have successfully adapted an explicit simplectic energy and momentum conserving integrator to treat systems of rigid bodies with collisions. We have also implemented the new collision detection as a contact potential in several finite element models to test its robustness and ability to model latching between two spacecraft.
We are in the beginning stages of applying uncertainty quantification UQ to certify latching systems and control algorithms. Figure 5. Two snapshots from dynamic docking simulation based on elastic latching elements.
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