Abstract
This investigation aims to analyze the forward kinematics and deployment path of large scale hexagonal modular mesh deployable space antenna employing analytical procedure. At first a comprehensive review of technical contributions from 1987 to date in this class of antenna is completed and least targeted areas are extracted. Based on shortcomings a new design of modular antenna is proposed that has an aperture diameter of 13 meters and is composed of seven modules. Each module possesses an aperture of more than 6 meters and consists of 6 ribs arranged in radial pattern around the central beam. In order to ensure that the antenna will deploy successfully in space conditions, feasibility of design & its stability during deployment; analytical investigation into kinematics & antenna trajectory is carried out using loop closure equations and homogeneous coordinate transformation method. The concept of virtual link is introduced to develop formulations that will help to determine position, velocity and acceleration of each revolute joint in the rib with any small increment in linear motion of slider from top to bottom of central beam. The proposed solution techniques will help to replace time consuming and costly iterations for design, build more economical structure, reduce antenna manufacture time and reduce weight leading to reduced launch as well as experimentation costs before launch.
Highlights
Space deployable antenna is an essential aerospace equipment to land and space exploration activities [1], [2]
A variety of basic modular units, such as square grid deployable [9]-[11], two types of basic modules with one being able to stow as cylinder & the other to thin plate form [12], [13], quadrilateral ribs with diagonal members for ETS VIII antenna [14]-[33], tri-foldable ribs [34], [35] and tri-foldable with bifurcated rib tips [36] for L-band application, have been proposed to integrate hexagonal reflector with aperture ranging from 1.7m to 30m in diameter
In [27], [29] six different rib schemes based on ETS VIII antenna units are discussed and fuzzy comprehensive evaluation method is applied [29] to determine the optimized configuration
Summary
Space deployable antenna is an essential aerospace equipment to land and space exploration activities [1], [2]. Extensive researches about antenna design have taken place ranging from highly accurate but heavy solid reflectors [3] to extremely light inflatable ones. In between these two extremes are the mesh antenna [4]. With high stiffness, packaging efficiency & high accuracy of observation is one of its subcategories. The shape of this reflector is maintained by mesh surface supported by cable network and deployable truss. Current expedition is to research & apply some cost effective & efficient methods of analysis to minimize the risk of failure and confirm stability of design during launch or in-orbit operation
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