火星进入条件下圆球激波脱体距离弹道靶实验测量和数值研究

发布时间：2018-01-04 16:39

本文关键词：火星进入条件下圆球激波脱体距离弹道靶实验测量和数值研究　出处：《中国空气动力研究与发展中心》2016年硕士论文　论文类型：学位论文

【摘要】：随着火星探测重要性日益提升,火星大气CO_2条件下探测器进入过程中面对的高温气体动力学问题愈发成为高超声速空气动力学理论分析、数值研究和实验研究的热点之一,CO_2条件下的圆球激波脱体距离测量数据能够为相关理论和数值研究提供有效验证。以往的圆球激波脱体距离的弹道靶实验主要在空气条件下进行,模型飞行速度集中在2.5km/s～4.0km/s范围,缺乏更高飞行速度的数据,圆球激波脱体距离的工程和数值计算方法也有待进一步改进和验证。为验证高超声速圆球激波脱体距离弹道靶实验测量方法可靠性,获得准确的实验数据供圆球激波脱体距离工程算法改进和数值计算验证,本文开展了空气和CO_2条件下的高超声速圆球激波脱体距离弹道靶实验,获得了空气条件下飞行速度5km/s以上和CO_2条件下、模拟火星进入弹道速度和ρR状态的圆球激波脱体距离实验数据,改进了圆球激波脱体距离的工程算法,验证了 Park双温度模型对空气条件下飞行速度5km/s以上和模拟火星进入速度和ρR状态CO_2条件下圆球激波脱体距离计算的准确性,全文共分为六章。第一章为引言。主要介绍了国内外火星探测的基本情况,综述了高超声速圆球激波脱体距离的理论、数值和实验研究现状,对目前研究存在的问题进行了总结,提出了本文的主要研究工作。第二章为高超声速圆球激波脱体距离弹道靶实验方法。介绍了本文使用的中国空气动力研究与发展中心超高速弹道靶设备的工作原理、实验设备布置、技术指标和实验测量方法。第三章为空气条件下高超声速圆球激波脱体距离的弹道靶实验。基于参考文献的速度和ρR状态设计了空气条件下的实验状态,得到模型飞行速度5km/s以上有效实验数据14个,环境压力1.500kPa～6.310kPa,模型飞行速度5.080km/s～6.490km/s;得到模型飞行速度2.5km/s～4.0km/s实验数据1个,环境压力4.200kPa,模型飞行速度2.690km/s。实验结果表明:本文实验测量方法可靠,实验结果与不同实验设备获取的数据具有可比性,阴影成像更易于判读激波位置。根据计算结果推测,本文空气条件下飞行速度5km/s以上的圆球驻点附近流动主要为非平衡状态,随ρR升高逐渐接近冻结状态。5km/s以上圆球激波脱体距离随ρR升高而增大,与2.5km/s～4km/s圆球激波脱体距离随ρR变化规律不同,推测ρR对速度不同的圆球驻点附近流动状态的影响程度不同。基于实验数据对圆球激波脱体距离工程算法进行了改进,改进算法的预测结果相对实验数据偏差在±20%以内,而原算法无法预测本文实验结果。第四章为CO_2条件下高超声速圆球激波脱体距离的弹道靶实验。参考火星典型进入弹道25km、30km、35km和40km高度的速度和ρR状态设计了CO_2条件下的实验状态,建立了靶室CO_2气体置换方法与技术,得到CO_2条件下模拟火星典型进入弹道25km、30km、35km和40km高度的实验数据各1个,靶室压力 2.420kPa～12.300kPa,模型飞行速度 2.122km/s～4.220km/s。同时开展了空气条件下相同速度、压力的脱体激波距离测量实验以提供对比数据。实验结果表明:通过阴影成像能够获取本文C02条件下激波脱体数据。速度、压力基本相同时,CO_2条件下高温气体效应较空气条件更显著,同时两者间实验数据可能存在一定关联关系。根据计算结果推测,本文CO_2条件下圆球驻点附近流动基本为非平衡状态。基于实验数据建立的圆球激波脱体距离工程算法基本能够吻合实验数据。不同ρR状态对激波脱体距离的影响有待进一步研究。第五章为高超声速圆球激波脱体距离数值计算分析。介绍了空气和CO_2条件下实验流场的完全、平衡、冻结和Park双温度非平衡模型计算方法。对比了计算结果与第二、三章实验数据和文献数据,分析了双温度非平衡模型计算空气条件下飞行速度5km/s以上和CO_2条件下圆球激波脱体距离的准确性,表明采用双温度非平衡模型能够较准确地预测实验结果。根据计算结果推测,本文空气条件下飞行速度5km/s以上的圆球驻点附近流动主要为非平衡状态,从圆球头部到下游远离头部区域,流动逐渐接近平衡流动;本文CO_2条件下从圆球头部到下游远离头部区域流动主要为非平衡状态。第六章为结束语,主要对本文主要工作和研究结论进行了总结,并提出了值得进一步深入研究的三个问题。
[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.

【学位授予单位】：中国空气动力研究与发展中心
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：P185.3

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