本文關(guān)鍵詞：火星進(jìn)入條件下圓球激波脫體距離彈道靶實(shí)驗(yàn)測(cè)量和數(shù)值研究　出處：《中國(guó)空氣動(dòng)力研究與發(fā)展中心》2016年碩士論文　論文類型：學(xué)位論文

  更多相關(guān)文章： 火星探測(cè) 高超聲速 圓球 激波脫體距離 彈道靶實(shí)驗(yàn) 非平衡流動(dòng)

【摘要】：隨著火星探測(cè)重要性日益提升,火星大氣CO_2條件下探測(cè)器進(jìn)入過(guò)程中面對(duì)的高溫氣體動(dòng)力學(xué)問(wèn)題愈發(fā)成為高超聲速空氣動(dòng)力學(xué)理論分析、數(shù)值研究和實(shí)驗(yàn)研究的熱點(diǎn)之一,CO_2條件下的圓球激波脫體距離測(cè)量數(shù)據(jù)能夠?yàn)橄嚓P(guān)理論和數(shù)值研究提供有效驗(yàn)證。以往的圓球激波脫體距離的彈道靶實(shí)驗(yàn)主要在空氣條件下進(jìn)行,模型飛行速度集中在2.5km/s～4.0km/s范圍,缺乏更高飛行速度的數(shù)據(jù),圓球激波脫體距離的工程和數(shù)值計(jì)算方法也有待進(jìn)一步改進(jìn)和驗(yàn)證。為驗(yàn)證高超聲速圓球激波脫體距離彈道靶實(shí)驗(yàn)測(cè)量方法可靠性,獲得準(zhǔn)確的實(shí)驗(yàn)數(shù)據(jù)供圓球激波脫體距離工程算法改進(jìn)和數(shù)值計(jì)算驗(yàn)證,本文開(kāi)展了空氣和CO_2條件下的高超聲速圓球激波脫體距離彈道靶實(shí)驗(yàn),獲得了空氣條件下飛行速度5km/s以上和CO_2條件下、模擬火星進(jìn)入彈道速度和ρR狀態(tài)的圓球激波脫體距離實(shí)驗(yàn)數(shù)據(jù),改進(jìn)了圓球激波脫體距離的工程算法,驗(yàn)證了 Park雙溫度模型對(duì)空氣條件下飛行速度5km/s以上和模擬火星進(jìn)入速度和ρR狀態(tài)CO_2條件下圓球激波脫體距離計(jì)算的準(zhǔn)確性,全文共分為六章。第一章為引言。主要介紹了國(guó)內(nèi)外火星探測(cè)的基本情況,綜述了高超聲速圓球激波脫體距離的理論、數(shù)值和實(shí)驗(yàn)研究現(xiàn)狀,對(duì)目前研究存在的問(wèn)題進(jìn)行了總結(jié),提出了本文的主要研究工作。第二章為高超聲速圓球激波脫體距離彈道靶實(shí)驗(yàn)方法。介紹了本文使用的中國(guó)空氣動(dòng)力研究與發(fā)展中心超高速?gòu)椀腊性O(shè)備的工作原理、實(shí)驗(yàn)設(shè)備布置、技術(shù)指標(biāo)和實(shí)驗(yàn)測(cè)量方法。第三章為空氣條件下高超聲速圓球激波脫體距離的彈道靶實(shí)驗(yàn)�；趨⒖嘉墨I(xiàn)的速度和ρR狀態(tài)設(shè)計(jì)了空氣條件下的實(shí)驗(yàn)狀態(tài),得到模型飛行速度5km/s以上有效實(shí)驗(yàn)數(shù)據(jù)14個(gè),環(huán)境壓力1.500kPa～6.310kPa,模型飛行速度5.080km/s～6.490km/s;得到模型飛行速度2.5km/s～4.0km/s實(shí)驗(yàn)數(shù)據(jù)1個(gè),環(huán)境壓力4.200kPa,模型飛行速度2.690km/s。實(shí)驗(yàn)結(jié)果表明:本文實(shí)驗(yàn)測(cè)量方法可靠,實(shí)驗(yàn)結(jié)果與不同實(shí)驗(yàn)設(shè)備獲取的數(shù)據(jù)具有可比性,陰影成像更易于判讀激波位置。根據(jù)計(jì)算結(jié)果推測(cè),本文空氣條件下飛行速度5km/s以上的圓球駐點(diǎn)附近流動(dòng)主要為非平衡狀態(tài),隨ρR升高逐漸接近凍結(jié)狀態(tài)。5km/s以上圓球激波脫體距離隨ρR升高而增大,與2.5km/s～4km/s圓球激波脫體距離隨ρR變化規(guī)律不同,推測(cè)ρR對(duì)速度不同的圓球駐點(diǎn)附近流動(dòng)狀態(tài)的影響程度不同�；趯�(shí)驗(yàn)數(shù)據(jù)對(duì)圓球激波脫體距離工程算法進(jìn)行了改進(jìn),改進(jìn)算法的預(yù)測(cè)結(jié)果相對(duì)實(shí)驗(yàn)數(shù)據(jù)偏差在±20%以內(nèi),而原算法無(wú)法預(yù)測(cè)本文實(shí)驗(yàn)結(jié)果。第四章為CO_2條件下高超聲速圓球激波脫體距離的彈道靶實(shí)驗(yàn)。參考火星典型進(jìn)入彈道25km、30km、35km和40km高度的速度和ρR狀態(tài)設(shè)計(jì)了CO_2條件下的實(shí)驗(yàn)狀態(tài),建立了靶室CO_2氣體置換方法與技術(shù),得到CO_2條件下模擬火星典型進(jìn)入彈道25km、30km、35km和40km高度的實(shí)驗(yàn)數(shù)據(jù)各1個(gè),靶室壓力 2.420kPa～12.300kPa,模型飛行速度 2.122km/s～4.220km/s。同時(shí)開(kāi)展了空氣條件下相同速度、壓力的脫體激波距離測(cè)量實(shí)驗(yàn)以提供對(duì)比數(shù)據(jù)。實(shí)驗(yàn)結(jié)果表明:通過(guò)陰影成像能夠獲取本文C02條件下激波脫體數(shù)據(jù)。速度、壓力基本相同時(shí),CO_2條件下高溫氣體效應(yīng)較空氣條件更顯著,同時(shí)兩者間實(shí)驗(yàn)數(shù)據(jù)可能存在一定關(guān)聯(lián)關(guān)系。根據(jù)計(jì)算結(jié)果推測(cè),本文CO_2條件下圓球駐點(diǎn)附近流動(dòng)基本為非平衡狀態(tài)�；趯�(shí)驗(yàn)數(shù)據(jù)建立的圓球激波脫體距離工程算法基本能夠吻合實(shí)驗(yàn)數(shù)據(jù)。不同ρR狀態(tài)對(duì)激波脫體距離的影響有待進(jìn)一步研究。第五章為高超聲速圓球激波脫體距離數(shù)值計(jì)算分析。介紹了空氣和CO_2條件下實(shí)驗(yàn)流場(chǎng)的完全、平衡、凍結(jié)和Park雙溫度非平衡模型計(jì)算方法。對(duì)比了計(jì)算結(jié)果與第二、三章實(shí)驗(yàn)數(shù)據(jù)和文獻(xiàn)數(shù)據(jù),分析了雙溫度非平衡模型計(jì)算空氣條件下飛行速度5km/s以上和CO_2條件下圓球激波脫體距離的準(zhǔn)確性,表明采用雙溫度非平衡模型能夠較準(zhǔn)確地預(yù)測(cè)實(shí)驗(yàn)結(jié)果。根據(jù)計(jì)算結(jié)果推測(cè),本文空氣條件下飛行速度5km/s以上的圓球駐點(diǎn)附近流動(dòng)主要為非平衡狀態(tài),從圓球頭部到下游遠(yuǎn)離頭部區(qū)域,流動(dòng)逐漸接近平衡流動(dòng);本文CO_2條件下從圓球頭部到下游遠(yuǎn)離頭部區(qū)域流動(dòng)主要為非平衡狀態(tài)。第六章為結(jié)束語(yǔ),主要對(duì)本文主要工作和研究結(jié)論進(jìn)行了總結(jié),并提出了值得進(jìn)一步深入研究的三個(gè)問(wèn)題。
[Abstract]:With the increasing importance of Mars, the Mars atmosphere under the condition of CO_2 probe into the problem of high temperature gas dynamics process in the face of increasingly become the analysis of hypersonic aerodynamics theory, one of the hot spots in numerical and experimental research, spherical shock standoff distance measurement data under the condition of CO_2 can provide effective verification for related theoretical and numerical studies. The previous round the shock standoff distance of ballistic target experiments mainly in air condition, model of flight speed from 2.5km/s to 4.0km/s, the lack of higher flight speed data engineering and the numerical calculation method of ball shock standoff distance also needs to be further improved and validated. In order to verify the reliability of high velocity spherical shock standoff distance ballistic measurement method and obtain accurate experimental data for spherical shock standoff distance engineering and numerical algorithm Numerical verification, this paper carried out the experiment of hypersonic spherical shock standoff distance ballistic air and CO_2 conditions, obtained under the condition of air flight speed of more than 5km/s and CO_2 under the condition of experimental data of sphere shock standoff distance simulated Mars enters ballistic velocity and P R state, improved engineering ball shock standoff distance algorithm, verification the accuracy of the Park double temperature model and simulation speed above 5km/s Mars in speed and P R state under the condition of CO_2 spherical shock standoff distance calculation of air flight conditions, this paper is divided into six chapters. The first chapter is the introduction. It mainly introduces the basic situation at home and abroad to Mars, summarizes the hypersonic shock standoff distance sphere the theoretical, numerical and experimental study of the status quo, the problems in current research are summarized, and put forward the main research work in this paper. The second chapter is the high supersonic circle The ball shock standoff distance ballistic experiments. This paper introduces the working principle of the China Aerodynamics Research and development center of ultra high speed ballistic experiment equipment, equipment layout, technical indicators and measurement method. The third chapter is the ballistic experiments of hypersonic spherical shock standoff distance under the condition of air velocity and P R reference state. The experiment is designed based on the state of air condition, get the model of the flight speed above 5km/s effective experimental data of 14, environmental pressure 1.500kPa ~ 6.310kPa, 5.080km/s ~ 6.490km/s flight speed model; model of flight speed of 2.5km/s ~ 4.0km/s experimental data of 1, the environmental pressure of 4.200kPa, the experimental results show that this model of flight speed measurement 2.690km/s. the method is reliable, and the experimental results of different experimental devices to obtain data comparable to the interpretation of the shock wave shadow imaging position The speculation. According to the calculation results, this paper under the condition of air flight speed above 5km/s stagnation point flow mainly for ball equilibrium, gradually close to the freezing state above.5km/s spherical shock standoff distance with P R increases with the increase of P R, 2.5km/s ~ 4km/s of spherical shock standoff distance changes with different P R, that P R on the different speed of flow near the stagnation point ball effect in different degree. The experimental data of Engineering spherical shock standoff distance prediction algorithm based on improved algorithm, the relative deviation was below 20% in the experimental data, and the original algorithm can predict the experimental results. The fourth chapter is the ballistic experiments of hypersonic spherical shock standoff the distance under the condition of CO_2. The typical 25km 30km into Mars trajectory, velocity and P R, state 35km and 40km highly designed experimental state under the condition of CO_2, establish The CO_2 gas replacement method and target chamber technology, CO_2 under the condition of simulated Mars into typical ballistic 25km, 30km, 35km and 40km of the height of the experimental data of the 1, the chamber pressure is 2.420kPa ~ 12.300kPa, 2.122km/s ~ 4.220km/s. model of flight speed and the same speed of the air condition, the detached shock pressure in distance measurement experiment to provide comparative data. The experimental results show that the shadow imaging can obtain the C02 under the condition of bow wave data. Velocity, pressure is basically the same, under the condition of CO_2 high temperature gas air condition effect is more significant, while the experimental data between the two may have the relationship that. According to the calculation results, this paper under the condition of CO_2 sphere stagnation point flow the basic non equilibrium state. Based on the experimental data to establish the spherical shock standoff distance engineering algorithm can basically agree with the experimental data. Different P R. Further study of state influence on the shock standoff distance to be calculated. The fifth chapter is the numerical analysis of hypersonic spherical shock standoff distance. The experimental flow field of air and CO_2 under the condition of complete, balanced, frozen and Park double temperature nonequilibrium model calculation method. Comparing the calculation results with the second, third chapter experimental data and literature data analysis the two temperature non-equilibrium model calculation under the condition of air flight speed of more than 5km/s and CO_2 under the condition of accurate ball shock standoff distance, indicate that the double temperature nonequilibrium model can accurately predict the experimental results. It is suggested that according to the calculation results, this paper under the condition of air flight speed above 5km/s stagnation point flow mainly for non spherical equilibrium state. From the ball head to head away from the downstream region, the flow gradually approaching the equilibrium flow; this paper under the condition of CO_2 from head to head away from the downstream sphere The sixth part is the concluding remarks. The main work and conclusions of this paper are summarized, and three questions worth further study are put forward.

【學(xué)位授予單位】：中國(guó)空氣動(dòng)力研究與發(fā)展中心
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：P185.3

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