固体微推进器工作过程的仿真研究

发布时间：2019-05-13 19:31

【摘要】：摘要：基于微机电系统技术的固体微推进器由于其成本低、可靠性高等优点受到了越来越多的重视。针对目前对固体微推进器的数值模拟研究中尚没有既考虑固体推进剂的燃面退移过程又考虑推进剂气相产物相互作用的研究,本文提出了利用燃速公式和化学反应动力学机理相结合的方法来模拟固体推进剂的瞬态燃烧过程。本文主要研究对象是某型号固体微推进器,推进剂采用研究较多的高氯酸铵/端羟基聚二丁烯(AP/HTPB),利用数值模拟的方法对固体推进剂的燃烧过程和燃气流动、传热等过程进行仿真研究。利用FLUENT软件对固体微推进器的工作过程进行仿真研究,通过对燃速公式的求解、AP/HTPB推进剂化学反应动力学模型以及热流固耦合模型的建立,完成固体微推进器工作过程仿真模型的建立。之后对固体微推进器的瞬态工作过程进行了仿真研究,得到了固体推进剂燃烧过程中燃烧温度,燃烧室压力,各组分质量浓度在微推进器内的分布,燃气流动速度、马赫数以及推力等随时间的变化规律,以此来分析推进剂的燃烧情况以及微推进器性能。本文首先对AP/HTPB推进剂质量配比进行了研究,分析了不同配比情况下推进剂的燃烧温度、组分浓度分布等规律,研究不同质量配比下推进剂气相组分间的作用机理；然后又研究了固体微推进器壁面条件(壁面材料和壁面厚度)和结构参数(燃烧室直径和喷管扩张半角)对推进剂的燃烧情况和微推进器性能的影响规律,深入分析并解释了固体微推进器工作过程中的各种现象以及各参数对固体微推进器工作过程的影响规律。
[Abstract]:Absrtact: solid micro thruster based on microelectromechanical system technology has attracted more and more attention because of its low cost and high reliability. In view of the current numerical simulation of solid micro thrusters, there is no consideration of both the fuel surface removal process of solid propellants and the interaction between gas phase products of solid propellants. In this paper, a method combining burning rate formula with chemical reaction kinetics is proposed to simulate the transient combustion process of solid propellants. The main research object of this paper is a certain type of solid micro-thruster. Ammonium perchlorate / hydroxyl-terminated polydibutene (AP/HTPB) is used to simulate the combustion process and gas flow of solid propellants. The heat transfer and other processes are simulated and studied. The working process of solid microthruster is simulated by FLUENT software. The combustion rate formula is solved, and the chemical reaction kinetics model and heat-fluid-solid coupling model of AP/HTPB propellants are established. The simulation model of solid micro thruster working process is established. Then the transient working process of the solid micro thruster is simulated and studied, and the combustion temperature, combustion chamber pressure, mass concentration of each component in the micro thruster and gas flow velocity are obtained. The variation of Mach number and thrust with time is used to analyze the combustion of propellants and the performance of micro propellants. In this paper, the mass ratio of AP/HTPB propellants was studied, the combustion temperature and concentration distribution of propellants under different ratios were analyzed, and the mechanism of interaction between gas phase components of propellants under different mass ratios was studied. Then the effects of wall conditions (wall material and wall thickness) and structural parameters (combustion chamber diameter and nozzle expansion half angle) on the combustion and performance of solid micro propellants are studied. Various phenomena in the working process of solid micro thruster and the influence of each parameter on the working process of solid micro thruster are analyzed and explained in detail.
【学位授予单位】：北京交通大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V43

【参考文献】