固体火箭发动机羽焰真温测量技术研究

发布时间：2018-12-29 11:53

【摘要】：固体火箭发动机的羽焰属于一种特殊火焰,呈现高温、高速和气固两相非平衡流的动态特征。羽焰温度是研究推进剂的燃烧过程、了解发动机的性能和优化发动机的特性的重要参数。羽焰流场非常复杂,固体火箭发动机地面试车时的测量环境十分恶劣,因此测量难度大。随着能源、国防以及宇航事业的发展,固体火箭发动机羽焰温度的测量越来越受重视。固体火箭羽焰真温测量技术的研究具有重要的科学价值与现实意义。多波长测温法是一种非接触法,其原理为在某一时刻对被测目标的多个波长下的亮度温度进行同时测量,进而求解目标真温。该方法对被测目标没有特殊要求,特别适合于高温、甚高温目标的真温测量。本文采用多波长测温法对固体火箭羽焰真温进行测量,旨在:探索发射率样本选择的理论依据,在此基础上研究真温构建的新方法;研制用于固体火箭羽焰真温测量的宽量程光纤式多波长高温计,解决现有多波长高温计无法获得1173K以下羽焰真温的问题;研究一种新的有效波长标定方法,解决传统标定方法因信号太弱而无法用于光纤式多波长高温计有效波长标定的问题。基于以上目的,本文开展了固体火箭发动机羽焰真温测量技术的研究工作。本文的主要研究内容如下:(1)针对传统多波长真温求解方法中发射率样本选择缺少理论依据的问题,提出了一种基于模型约束的多波长真温构建方法。概述了传统多波长真温求解方法,分析了传统方法存在的主要问题。在亮度温度模型的基础上,通过理论推导发现了亮度温度变化和发射率变化之间的内在关系,提出了具有普适性的发射率模型约束条件。基于该约束条件,建立了带约束的多模型真温构建方法。仿真结果表明,相比二次测量法,该方法的计算速度最大可提升81.3%。该发射率模型约束条件可以有效筛选发射率样本,为发射率样本的选择提供了理论基础。(2)为解决在1173K以下采用单一黑体辐射源不能实现现有高温计的宽量程标定而无法测量羽焰真温的问题,研制了一种用于固体火箭羽焰真温测量的宽量程光纤式多波长高温计。分析了固体火箭羽焰的辐射特性和羽焰测温的实际需求,设计了高温计的光学系统、电路系统和应用程序。光学系统采用分离结构和光纤远传技术,提高了高温计的瞄准性能和工作可靠性。电路系统采用并联光电探测器阵列相邻像元的方法和前置放大电路自动切换量程的方法,并针对900K~1173K温区的温度标定提出了基于对数函数的标定新方法,使高温计的测温下限达到了900K,将高温计的温度测量范围拓宽至900K~2700K。(3)针对传统有效波长标定方法标定光纤式多波长高温计存在的实际问题,提出了一种基于温度标定的有效波长标定新方法。分析了高温计的传统有效波长标定方法。结合实际温度标定数据,研究了高温计温度标定数据的内在规律。基于普朗克定律,建立了不同标定温度点标定数据与有效波长之间的关系模型,提出了由温度标定数据直接确定有效波长的求解方法。该方法不仅提供了一种快速获取有效波长的新思路,而且避免了复杂耗时的标定过程。分别采用仿真和实验对该方法进行了验证。仿真结果显示,温度标定值加入±1%的随机误差后,新方法得到的波长值与理论值之间的相对误差小于4.7%,此时所得真温的计算值与理论值之间的相对误差的最大绝对值为0.7%。实验结果表明,相比传统标定方法,新方法所得波长值的相对误差的最大绝对值为1.9%,此时所得真温值的绝对误差的最大值为2.4K,表明该方法可行。(4)对高温计的实验结果和不确定度进行了分析。采用本文所研制的高温计在实验室进行了卤钨灯灯丝温度和黑体辐射源温度的测量实验,结果表明了高温计的正确性与合理性。测量了某固体火箭发动机地面试车时的羽焰真温变化全过程,并对实验结果进行了分析。利用该实验数据,进一步验证了基于模型约束的多波长真温构建方法的有效性。分析了该高温计的测量不确定度,得出其合成不确定度为2.07%。
[Abstract]:The plume of solid rocket engine belongs to a kind of special flame, and presents the dynamic characteristics of high-temperature, high-speed and gas-solid two-phase non-equilibrium flow. The temperature of plume is an important parameter to study the combustion process of the propellant, to understand the performance of the engine and to optimize the characteristics of the engine. The flow field of the plume is very complex, and the measurement environment during the ground test run of the solid rocket engine is very bad, so it is difficult to measure. With the development of energy, national defense and space, the measurement of the plume temperature of solid rocket engine is becoming more and more important. The research of solid rocket plume true temperature measurement technology is of great scientific value and practical significance. The multi-wavelength temperature measurement method is a non-contact method, the principle of which is to simultaneously measure the brightness temperature at a plurality of wavelengths of the target to be measured at a certain time, so as to solve the target true temperature. The method has no special requirements for the target to be tested, and is particularly suitable for the true temperature measurement of the high-temperature and very high-temperature target. In this paper, a multi-wavelength temperature measurement method is used to measure the true temperature of the solid rocket plume. The aim of this paper is to study the theoretical basis of the selection of the emissivity samples, and to study the new method of the true temperature construction. The wide-range fiber-type multi-wavelength pyrometer for measuring the true temperature of the solid rocket plume is developed. The invention solves the problem that the existing multi-wavelength pyrometer can not obtain the true temperature of the plume below 1173K, and a new effective wavelength calibration method is researched, and the problem that the traditional calibration method cannot be used for the effective wavelength calibration of an optical fiber type multi-wavelength pyrometer due to the weak signal is solved. Based on the above object, this paper has carried out the research work of the solid rocket engine feather-flame real-temperature measurement technology. The main contents of this paper are as follows: (1) A method for constructing a multi-wavelength true temperature based on a model constraint is proposed for the problem of the lack of theoretical basis for the selection of the emissivity samples in the conventional multi-wavelength true-temperature solution method. In this paper, the traditional multi-wavelength true-temperature solution method is introduced, and the main problems in the traditional method are analyzed. On the basis of the brightness temperature model, the intrinsic relation between the change of the brightness temperature and the change of the emissivity is found by the theory, and the constraint of the emissivity model with universality is put forward. Based on this constraint, a multi-model true-temperature construction method with constraint is established. The simulation results show that the calculation speed of the method can be improved by 81.3%. The model of the emissivity model can effectively screen the emissivity samples and provide a theoretical basis for the selection of the emissivity samples. (2) In order to solve the problem that a single blackbody radiation source cannot be used to measure the true temperature of the plume under 1173K, a wide-range fiber-type multi-wavelength pyrometer for real-temperature measurement of solid rocket plume is developed. The radiation characteristics of the solid rocket plume and the actual demand of the plume temperature measurement are analyzed, and the optical system, the circuit system and the application program of the pyrometer are designed. the optical system adopts the separation structure and the optical fiber far-transmitting technology, so that the aiming performance and the working reliability of the pyrometer are improved. The circuit system adopts the method of parallel photoelectric detector array adjacent image element and the method of automatic switching range of the pre-amplifier circuit, and the calibration method based on the logarithmic function is proposed for the temperature calibration of the 900K-1173K temperature zone, so that the lower limit of the temperature measurement of the pyrometer reaches 900K, The temperature measurement range of the pyrometer is widened to 900K ~ 2700K. (3) To calibrate the actual problem of the optical fiber multi-wavelength pyrometer for the traditional effective wavelength calibration method, a new method of effective wavelength calibration based on temperature calibration is proposed. The traditional effective wavelength calibration method for pyrometer is analyzed. According to the actual temperature calibration data, the internal law of the temperature calibration data of the pyrometer is studied. Based on the Planck's law, the relation model between the calibration data and the effective wavelength of different calibration temperature points is established, and a method for directly determining the effective wavelength by the temperature calibration data is proposed. The method not only provides a new method for rapidly acquiring the effective wavelength, but also avoids the complex time-consuming calibration process. The method was validated by simulation and experiment, respectively. The simulation results show that the relative error between the wavelength value and the theoretical value obtained by the new method is less than 4.7% after the temperature calibration value is added to the random error of 1%, and the maximum absolute value of the relative error between the calculated value of the obtained true temperature and the theoretical value is 0.7%. The experimental results show that the maximum absolute value of the relative error of the wavelength value obtained by the new method is 1. 9% compared with the traditional calibration method, and the maximum value of the absolute error of the obtained true temperature value is 2.4K, which shows that the method is feasible. (4) The experimental results and the uncertainty of the pyrometer were analyzed. The temperature of the halogen tungsten lamp filament and the temperature of the blackbody radiation source are measured in the laboratory by the pyrometer developed in this paper. The results show the correctness and rationality of the pyrometer. The whole process of the true temperature change of the plume in the ground test run of a solid rocket engine is measured, and the experimental results are analyzed. The validity of the multi-wavelength true-temperature construction method based on the model constraint is further verified by using the experimental data. The measurement uncertainty of the pyrometer was analyzed, and the uncertainty of its synthesis was 2.07%.
【学位授予单位】：哈尔滨工业大学
【学位级别】：博士
【学位授予年份】：2017
【分类号】：V435

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