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Petal-type Deployable Antenna Design and Experimental Study

Author: LiYang
Tutor: LuoANi
School: Harbin Engineering University
Course: Mechanical Design and Theory
Keywords: solid interface deployable structure speed acceleration
CLC: V443.4
Type: Master's thesis
Year: 2012
Downloads: 13
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 ofthe information, and the antenna diameter getting larger size will be a inevitable demand.Larger size is good for bandwidth improvement, signal gain, and ground receiving devicewill be simplified. Because the interior of launch vehicle is limited, there is no extra spaceto carry large satellite antenna. Deployable structure has been widely used in spaceindustry. At the same time solid interface structure has the advantages of surface highaccuracy, structural stability and the force-driven actuator, etc. So solid interfacedeployable structure has been applied in structural design of satellite antenna.So far, study on solid interface deployable antenna has fully developed in abroad andthere are successful cases. However, such research is still at the start exploration stage indomestic. And the study of solid interface deployable antenna in primarily focused onanalyzing various parameters which includes reliability analysis, topological analyses,thermal analysis, dynamics analysis, measure experiment, etc. This paper discusses theblock form in detail and analyses the kinematics based on petal solid interface deployableantenna. Then this paper will put forward feasible proposals for acceleration regulation ofsuch antenna.According to the characteristics of petal satellite antenna, with Degree of freedomformula as a guideline, by choice of different dynamic system, we can get the amount ofsuch antenna’s stiffness board. The standard is minimum volume after antenna contracted,and we can get the amount of such antenna’s sailboard. Then we can turn out the blockcriterion of the antenna.According to the characteristics of petal deployable space mechanism, usingcoordinate transformation, building a deployment motion analysis model which isuniversal, analysing the targets of sailboard when expanded, by calculation to find out thegeometric relationship between input shaft and output one. Applying the software ofPro/Engineer, adopted Virtual prototype technology, come to discrete measurementvalues of the targets, taking least square method and getting curve fitting to the discretedata,by the fitting equation, getting more objective information about speed and acceleration of rotation axis, we can understand how antenna works. Applying thesoftware of ADAMS, I got further study on kinematics of such antenna. At last I madeexperimental model and made experiments to verify and prove materials from previousassignments.At last the block form of petal satellite antenna has been established: the number ofrigidity superconductive plate is3、4、5on each panel. When the number of panel is6,theantenna has the best receive volume. After the forward analysis of antenna structureposition, the functional relation between output angle and input angle has be established.By means of kinematic analysis and by the method of fitting equation, we can fit thefunctional relation between output angle and input angle. With the derivation of them, theangular velocity and the angular acceleration of output angle are further analyzed. We canget with extending antenna’s motion time, the angular acceleration of all output anglesbecomes less. This can make the mechanism move stability during expanding and closing.

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CLC: > Aviation, aerospace > Aerospace ( Astronauts ) > Space instrument,spacecraft devices,spacecraft guidance and control > Electronic equipment > Spacecraft antenna
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