【摘要】：摘要：基于微機(jī)電系統(tǒng)技術(shù)的固體微推進(jìn)器由于其成本低、可靠性高等優(yōu)點(diǎn)受到了越來(lái)越多的重視。針對(duì)目前對(duì)固體微推進(jìn)器的數(shù)值模擬研究中尚沒(méi)有既考慮固體推進(jìn)劑的燃面退移過(guò)程又考慮推進(jìn)劑氣相產(chǎn)物相互作用的研究,本文提出了利用燃速公式和化學(xué)反應(yīng)動(dòng)力學(xué)機(jī)理相結(jié)合的方法來(lái)模擬固體推進(jìn)劑的瞬態(tài)燃燒過(guò)程。本文主要研究對(duì)象是某型號(hào)固體微推進(jìn)器,推進(jìn)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(duì)固體推進(jìn)劑的燃燒過(guò)程和燃?xì)饬鲃?dòng)、傳熱等過(guò)程進(jìn)行仿真研究。 利用FLUENT軟件對(duì)固體微推進(jìn)器的工作過(guò)程進(jìn)行仿真研究,通過(guò)對(duì)燃速公式的求解、AP/HTPB推進(jìn)劑化學(xué)反應(yīng)動(dòng)力學(xué)模型以及熱流固耦合模型的建立,完成固體微推進(jìn)器工作過(guò)程仿真模型的建立。之后對(duì)固體微推進(jìn)器的瞬態(tài)工作過(guò)程進(jìn)行了仿真研究,得到了固體推進(jìn)劑燃燒過(guò)程中燃燒溫度,燃燒室壓力,各組分質(zhì)量濃度在微推進(jìn)器內(nèi)的分布,燃?xì)饬鲃?dòng)速度、馬赫數(shù)以及推力等隨時(shí)間的變化規(guī)律,以此來(lái)分析推進(jìn)劑的燃燒情況以及微推進(jìn)器性能。 本文首先對(duì)AP/HTPB推進(jìn)劑質(zhì)量配比進(jìn)行了研究,分析了不同配比情況下推進(jìn)劑的燃燒溫度、組分濃度分布等規(guī)律,研究不同質(zhì)量配比下推進(jìn)劑氣相組分間的作用機(jī)理；然后又研究了固體微推進(jìn)器壁面條件(壁面材料和壁面厚度)和結(jié)構(gòu)參數(shù)(燃燒室直徑和噴管擴(kuò)張半角)對(duì)推進(jìn)劑的燃燒情況和微推進(jìn)器性能的影響規(guī)律,深入分析并解釋了固體微推進(jìn)器工作過(guò)程中的各種現(xiàn)象以及各參數(shù)對(duì)固體微推進(jìn)器工作過(guò)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(xué)位授予單位】：北京交通大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：V43

【參考文獻(xiàn)】

相關(guān)期刊論文 前10條

1 陳旭鵬,李勇,周兆英;微小型化學(xué)能推進(jìn)器的研究[J];微納電子技術(shù);2003年Z1期

2 徐超;李兆澤;萬(wàn)紅;吳學(xué)忠;;MEMS固體微推進(jìn)器中Cr薄膜點(diǎn)火電阻的研究[J];傳感技術(shù)學(xué)報(bào);2006年05期

3 楊海威;朱衛(wèi)兵;趙陽(yáng);;微型推進(jìn)器流場(chǎng)數(shù)值模擬[J];導(dǎo)彈與航天運(yùn)載技術(shù);2009年05期

4 王志健;杜佳佳;;動(dòng)網(wǎng)格在固體火箭發(fā)動(dòng)機(jī)非穩(wěn)態(tài)工作過(guò)程中的應(yīng)用[J];固體火箭技術(shù);2008年04期

5 尤政,張高飛,林楊,任大海;MEMS固體化學(xué)推進(jìn)器設(shè)計(jì)與建模研究[J];光學(xué)精密工程;2005年02期

6 沈瑞琪,葉迎華,戴實(shí)之;數(shù)字化火工技術(shù)的概念和應(yīng)用[J];火工品;2000年02期

7 張高飛,尤政,胡松啟,李葆萱,王伯雄;基于MEMS的固體推進(jìn)器陣列[J];清華大學(xué)學(xué)報(bào)(自然科學(xué)版);2004年11期

8 José A.Morí濼igo;José Hermida-Quesada;;Multiphysics Simulation of a Novel Concept of MEMS-based Solid Propellant Thruster for Space Propulsion[J];Journal of Thermal Science;2011年06期

9 周海清;張高飛;尤政;;固體微推力器設(shè)計(jì)與數(shù)值分析[J];推進(jìn)技術(shù);2007年03期

10 曹永杰;余永剛;葉銳;;含氣固耦合的AP/HTPB微觀燃燒數(shù)值模擬[J];燃燒科學(xué)與技術(shù);2013年02期

，

本文編號(hào)：2476131