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The Design and Analysis of the Hexagon Space Deployable Structure

Author: ZhangTongMing
Tutor: LiuHePing
School: Harbin Engineering University
Course: Mechanical Design and Theory
Keywords: hexagon deployable structure finite element analysis analysis of dynamics 3-Dmodeling surface precision
CLC: V414
Type: Master's thesis
Year: 2012
Downloads: 26
Quote: 0
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Recently, the requirement of the ability which is used to transmit information on thesatellites is increasing with the developing of the aerospace and the increasing demand of theinformation. It is an important program in aerospace to design a space deployable structurewith large scale, high precision, high ingathering rate, light weight and high reliability. Thereare many research on the field of topology analysis, analysis of reliability, measure andexperience, thermal analysis, dynamic analysis have been done by many scientific researchinstitution in many countries, and many kinds of deployable structure which is used on thesatellite successfully.In this paper, a deployable hexagon solid structure used in space is researched in design,simulation, analysis and experiment, the deployable hexagon solid structure used in space hasa higher ingathering rate, it is wildly used on the antenna on satellite, space telescope, andsolar array. a deployable hexagon solid structure used in space whose diameter is1.5m isdesigned.Foremost, the transmission mechanism which is made up by crank, connecting rod,slider and cam is designed contract with the deployable program of the hexagon deployablestructure, all the deployable units is driven by one electromotor, the length of the crank isdesigned at the process of the analysis of the surface precision, and the cam is designedcontract to the reliability of the structure, the structure of girder construction of the hexagonplate is chosen by the aim of reducing its weight, a structure which has the highest stiffness inthe same weight is chosen by the method of finite elements, The3-D model of the deployablehexagon structure is established and simulated, the feasibility of the structure is proved.Secondly, the deployable program is optimized, a different deployable order is used for thesake of developing the balance of the structure, the lord of the position and orientationadjustment system is reduced to25%, the influence of between the gravity and acceleration tothe precision is analyzed, and the scale factor between the acceleration and the precision iscalculated, and it can be concluded that the stiffness of the reflector is the main factor to thereflector precision. Finally the solid model of some key component of the structure is made toused on the feasibility experiment, the kinetic uncertainty of the parallel four-bar linkage isdiscovered and solved in the experiment, the dead center point position of the crank-connecting rod is measured, and the device which is used to overcome the dead centerpoint is design by the measured data.

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CLC: > Aviation, aerospace > Aerospace ( Astronauts ) > Basic theory and experiments > Spacecraft structural mechanics
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