Feasibility Study of Deployable Prime Focal Antenna Mechanism for Space Applications

Abstract

Space agencies are working on development of large size (3 m or more) antenna systems to satisfy the need of high bandwidth communication which would require antenna deployable mechanisms. Objective of deployable mechanism is to fold the reflector to a compact size and volume which can be accommodated in launch vehicle with payload and later can be deployed to full configuration in space after launch. Mechanism with maximum contraction ratio, minimum power consumption and lesser complexity is today's research areas which need to be explored. With a view to this, an effort has been made in carrying out a feasibility study of deployment process of various versions of prime focal antenna system with merits and demerits of each version over each other. All versions are studied kinematically on common design specifications and compared with the design specifications. Comparison on the base of dynamic simulation with estimation of the requirement of actuation forces is in the purview of this study and is carried out. This comparative study helps to find the best fitting deployable mechanism fitting defined design criterion. This elaborative study will help designers for opting a simple option for the design of deployable version of prime focal antenna reflector.