Design And Analysis Of Deployment Mechanism For Space Telescope

Abstract

Telescopes are widely used for space based remote sensing applications. With the present need of increased resolution of space telescope the size of the system increases. The payload fairing of the launch vehicle accommodates the telescope. There is a constraint on the telescope size due to payload fairing volume limitation. Thus a deployable telescope can be used to satisfy this need. A deployable telescope is a concept where the telescope shall remain stowed in the payload fairing in the launch vehicle and be deployed in orbit to its nal form. A deployment mechanism for a 1m resolution space based telescope is being developed under a Technology Development Program (TDP) at Space Applications Center, ISRO. An initial concept demonstration model of the mechanism was developed as a part of rst phase of the project. Phase - 2 of the project is aimed at developing a mechanism for 100 micron deployment accuracy in separation. Scope of the present work is related to Phase - 2 of the project. Two models were made as a part of phase -2. Design of elements of deployment mechanism and its characterization was done. Assembly and separation characterization is carried out for both models of phase-2 deployment mechanism. Dynamic analysis of Deployment Mechanism is carried out to estimate desired value of sti ness of torsion spring for complete deployment and damping factor of damper to avoid shock at the end of deployment. Actual two link rigid model and

exible model are prepared using MSC ADAMS tool. Dynamic analysis for the above two models were carried out to estimate Deployment Time, joint angle and Angular acceleration for link-1 and link-2. Details regarding the design of mechanism elements, analysis, realization and characterization are covered in this Dissertation.