固面折展式太阳能聚束器设计与分析
发布时间：2018-08-06 19:37
【摘要】：固面折叠展开式太阳能聚束器是一类新型的空间能源技术,具有形面精度高、刚度高的特点。空间热推进是近年来出现的新型航天器推进技术,该项技术通过聚集太阳直射辐照能,产生高密度的辐射能,将辐射能转化为推进力,主要应用于空间太阳能热推进、飞行器空间调姿等领域。另外,固面折叠展开式太阳能聚束器的折展原理可以用于研制固面折展天线,在星球资源探测、气象预警和军事通信等多个领域,具有很重要的应用价值。首先,本文对固面折展式太阳能聚束器进行了构型设计,即提出了基本可展模块Twin-Bennett机构的几何约束条件,并推导出了Twin-Bennett机构的运动环路方程,证明了该机构的单自由度,并对多单元装配进行研究,不仅证明了装配的单自由度,而且完成了聚束器的构型设计和机构运动简图,还从数值解和仿真两个角度对装配后的机构进行了运动学特性分析。然后,完成了固面折展式太阳能聚束器的参数设计,即基于收拢性能初步确定了曲面切割方案,采用了三段式的方案对其修改,提出了一种基于盘面运动轨迹分析盘面干涉的方法,最终确定盘面边线的方程。另外,本文还对聚束器进行了详细的结构设计,包括铰链、传动机构、机架等部分的结构设计。对于传动机构和聚束器盘面形成的组合机构,在匀速电机约束下,进行了运动学分析,分步求解得到了盘面的运动过程中的参数。最后,完成了无电机限速时聚束器一个单元的动力学分析,完成了动力学建模和动力学方程的推导。同时,完成了聚束器的样机研制,给出了各部分组件的装配顺序,得到了聚束器的收拢状态下的装配体;完成了展开功能试验和型面精度测量试验,验证了聚束器的折展原理与结构设计的正确性,测量展开精度误差,其盘面周向型面精度为0.1mm~0.2mm,径向型面精度误差在5%以内。
[Abstract]:Solid-plane folded and expanded solar buncher is a new type of space energy technology with high shape accuracy and high stiffness. Space thermal propulsion is a new spacecraft propulsion technology in recent years. This technology generates high density radiation energy by concentrating direct solar radiation energy, and converts radiation energy into propulsion force, which is mainly used in space solar thermal propulsion. Aircraft space attitude adjustment and other fields. In addition, the folding principle of the fixed-plane folded and expanded solar buncher can be used to develop the fixed-plane folded antenna, which has important application value in many fields, such as the exploration of planet resources, meteorological early warning and military communication. First of all, the configuration design of the solid plane folded solar buncher is presented, that is, the geometric constraint condition of the basic developable module Twin-Bennett mechanism is proposed, and the motion loop equation of the Twin-Bennett mechanism is derived, and the single degree of freedom of the mechanism is proved. The research on multi-element assembly not only proves the single degree of freedom of assembly, but also completes the configuration design and kinematic diagram of the buncher, and analyzes the kinematics characteristics of the assembled mechanism from the point of view of numerical solution and simulation. Then, the parameter design of the solid-plane folding solar buncher is completed, that is, the surface cutting scheme is preliminarily determined based on the closure performance, and the three-segment scheme is adopted to modify it. In this paper, a method of analyzing the interference of disk surface based on the track of disk surface motion is proposed, and the equation of the edge line of disc surface is determined. In addition, the structure of the buncher is designed in detail, including hinge, transmission mechanism, frame and so on. The kinematics analysis of the combined mechanism formed by the drive mechanism and the buncher disk surface is carried out under the constraint of the uniform speed motor, and the parameters in the motion process of the disk surface are obtained step by step. Finally, the dynamics analysis of a single unit of the buncher without the speed limit of the motor is completed, and the dynamic modeling and the derivation of the dynamic equation are completed. At the same time, the prototype of the buncher is developed, the assembly sequence of each component is given, the assembly of the buncher is obtained, and the expansion function test and the precision measurement test of the shape surface are completed. The principle of beam buncher and the correctness of structural design are verified. The precision error of measurement and expansion is 0.1 mm / 0.2 mm for circumferential surface and 5% for radial shape plane.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V439.6
本文编号：2168777
[Abstract]:Solid-plane folded and expanded solar buncher is a new type of space energy technology with high shape accuracy and high stiffness. Space thermal propulsion is a new spacecraft propulsion technology in recent years. This technology generates high density radiation energy by concentrating direct solar radiation energy, and converts radiation energy into propulsion force, which is mainly used in space solar thermal propulsion. Aircraft space attitude adjustment and other fields. In addition, the folding principle of the fixed-plane folded and expanded solar buncher can be used to develop the fixed-plane folded antenna, which has important application value in many fields, such as the exploration of planet resources, meteorological early warning and military communication. First of all, the configuration design of the solid plane folded solar buncher is presented, that is, the geometric constraint condition of the basic developable module Twin-Bennett mechanism is proposed, and the motion loop equation of the Twin-Bennett mechanism is derived, and the single degree of freedom of the mechanism is proved. The research on multi-element assembly not only proves the single degree of freedom of assembly, but also completes the configuration design and kinematic diagram of the buncher, and analyzes the kinematics characteristics of the assembled mechanism from the point of view of numerical solution and simulation. Then, the parameter design of the solid-plane folding solar buncher is completed, that is, the surface cutting scheme is preliminarily determined based on the closure performance, and the three-segment scheme is adopted to modify it. In this paper, a method of analyzing the interference of disk surface based on the track of disk surface motion is proposed, and the equation of the edge line of disc surface is determined. In addition, the structure of the buncher is designed in detail, including hinge, transmission mechanism, frame and so on. The kinematics analysis of the combined mechanism formed by the drive mechanism and the buncher disk surface is carried out under the constraint of the uniform speed motor, and the parameters in the motion process of the disk surface are obtained step by step. Finally, the dynamics analysis of a single unit of the buncher without the speed limit of the motor is completed, and the dynamic modeling and the derivation of the dynamic equation are completed. At the same time, the prototype of the buncher is developed, the assembly sequence of each component is given, the assembly of the buncher is obtained, and the expansion function test and the precision measurement test of the shape surface are completed. The principle of beam buncher and the correctness of structural design are verified. The precision error of measurement and expansion is 0.1 mm / 0.2 mm for circumferential surface and 5% for radial shape plane.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V439.6
【参考文献】
相关期刊论文 前2条
1 黄真;刘婧芳;曾达幸;;基于约束螺旋理论的机构自由度分析的普遍方法[J];中国科学(E辑:技术科学);2009年01期
2 刘荣强;田大可;邓宗全;;空间可展开天线结构的研究现状与展望[J];机械设计;2010年09期
，本文编号：2168777
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