【摘要】：摘要：基于微機電系統(tǒng)技術的固體微推進器由于其成本低、可靠性高等優(yōu)點受到了越來越多的重視。針對目前對固體微推進器的數(shù)值模擬研究中尚沒有既考慮固體推進劑的燃面退移過程又考慮推進劑氣相產物相互作用的研究,本文提出了利用燃速公式和化學反應動力學機理相結合的方法來模擬固體推進劑的瞬態(tài)燃燒過程。本文主要研究對象是某型號固體微推進器,推進劑采用研究較多的高氯酸銨/端羥基聚二丁烯(AP/HTPB),利用數(shù)值模擬的方法對固體推進劑的燃燒過程和燃氣流動、傳熱等過程進行仿真研究。 利用FLUENT軟件對固體微推進器的工作過程進行仿真研究,通過對燃速公式的求解、AP/HTPB推進劑化學反應動力學模型以及熱流固耦合模型的建立,完成固體微推進器工作過程仿真模型的建立。之后對固體微推進器的瞬態(tài)工作過程進行了仿真研究,得到了固體推進劑燃燒過程中燃燒溫度,燃燒室壓力,各組分質量濃度在微推進器內的分布,燃氣流動速度、馬赫數(shù)以及推力等隨時間的變化規(guī)律,以此來分析推進劑的燃燒情況以及微推進器性能。 本文首先對AP/HTPB推進劑質量配比進行了研究,分析了不同配比情況下推進劑的燃燒溫度、組分濃度分布等規(guī)律,研究不同質量配比下推進劑氣相組分間的作用機理；然后又研究了固體微推進器壁面條件(壁面材料和壁面厚度)和結構參數(shù)(燃燒室直徑和噴管擴張半角)對推進劑的燃燒情況和微推進器性能的影響規(guī)律,深入分析并解釋了固體微推進器工作過程中的各種現(xiàn)象以及各參數(shù)對固體微推進器工作過程的影響規(guī)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.
【學位授予單位】：北京交通大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V43

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