Optimization Design And Error Analysis Of Deployable Mechanisms For The Despun Antenna

With the rapid development of economic globalization and scientific technology progress,satellite technology research are also faced with a tremendous challenge.With the increase in human activities and spaceflight exploration,spaceflight structure has become more complicated and varied. Because the figure of the spaceflight structure is subject to environment and operational requirements, people were in contradictions when resolving between the structure and means of delivery.In the process of trying to resolve this constradition, many ways were adopted, The most feasible way is to minish the figure of the space, thus triggering the commencement of the'Deployable Space Structures'.That is to say, the spaceflight structure should occupy smaller room.In the lauching phase the structure should furled in limited space, and after the motivity fly they can be ertended to the scheduled space configurations. The issues is raised in this manner, people in this filed has achieved fruitful results. Some large spatial arm, the folding antenna has been studyed abroad for satisfactory harvest.In this paper, the mostly matter is to research the unwind mechanism of the satellitic antenna, the antenna is a small one.At present, the research of small folding mechanism is just starting ,the results are little more at home. On reading of relevant informations and a lot of books about mechanism innovations,this paper drawed up several projects of the deployable mechanism for the antenna,and on the basis, More detailed researches were done for the deployable mechanisms. First, start with two folding mechanisms on optimization design use ADAMS software, and the size of mechanism was fully satisfy the movementrequirements. On the basis, built three-dimensional model for each of two projects in ADAMS, and runed simulation analysis. Second, use the existing mature error algorithm―― matrix method and the loop incremental theory of error analysis to compute the posotions error of the two mechanisms. Also did some error analysis in ADAMS for the length of members and the revolute clearance of the two deployable mechanisms. Through the above analysis, one of the mechanism can be used as the first choice of stent projects.The main content of this article is divided into six parts:Part 1 Introduction.This part introduces the topic's background, significance, and the related concepts of deployable space structures, as well as the classification of deployable space structures by their driven mode. And introduced the contents and methods of this research.Part 2 The overall structure and geometric parameters of antenna.The present chapter describes the functions of the antenna system and conical scanning antenna overall composition. According to the parabolic reflector principles and known geometric size, we calculate the concretely geometric size of the two antenna located in the antenna space, and also lay the foundation of modeling and design work in the future.Part 3 The design of deployable mechanism of the antenna.This chapter developed several project of deployable mechanisms for the two reflector of the Conical Scanning Antenna System,and did kinematic simulation with the ADAMS software. Also several comparative analysis of these projects were done at the last of the chapter.The results show, the latter two delopyable mechanism are more suited to be the support of the big antenna. However, qualitative analysis revealed that both programs have their advantages and disadvantages, hence future analysis and comparison were needed. The comparative analysis for three projects for small antenna found that the third option should be considered as the first choice.Part 4 Optimization design and kinematics analysis of the mechanisms.The present chapter optimized and simulated the two mechanisms. Here all the work was completed at the ADAMS software. According to the different characteristics of the mechanisms, different methods should be taken to build the parametric model, also should take different optimization methods. After optimization, the mechanisms were more responsive to the requirement,and come to the ultimately design parameters. On the basis, three-dimensional model for both of the projects were built and simulation analysis were be done for the antenna system.Part 5 Error analysis of the deployable mechanisms.The error analysis of the two mechanisms which mentioned in the third chapter were maked out. First, used the present mature algorithm――Matrix method and the loop incremental theory to compute the position errors of two mechanisms. second, compute the position errors again use ADAMS software. By calculating we know, the results of the two were consistent, but the sofeware method are more convenience and rapid,and can avoid a lot of computation.Part 6 Conclusion.This part shows the conclusion of this article, pointed out the direction of this research.