固體火箭發(fā)動機羽焰真溫測量技術(shù)研究
發(fā)布時間：2018-12-29 11:53
【摘要】：固體火箭發(fā)動機的羽焰屬于一種特殊火焰,呈現(xiàn)高溫、高速和氣固兩相非平衡流的動態(tài)特征。羽焰溫度是研究推進(jìn)劑的燃燒過程、了解發(fā)動機的性能和優(yōu)化發(fā)動機的特性的重要參數(shù)。羽焰流場非常復(fù)雜,固體火箭發(fā)動機地面試車時的測量環(huán)境十分惡劣,因此測量難度大。隨著能源、國防以及宇航事業(yè)的發(fā)展,固體火箭發(fā)動機羽焰溫度的測量越來越受重視。固體火箭羽焰真溫測量技術(shù)的研究具有重要的科學(xué)價值與現(xiàn)實意義。多波長測溫法是一種非接觸法,其原理為在某一時刻對被測目標(biāo)的多個波長下的亮度溫度進(jìn)行同時測量,進(jìn)而求解目標(biāo)真溫。該方法對被測目標(biāo)沒有特殊要求,特別適合于高溫、甚高溫目標(biāo)的真溫測量。本文采用多波長測溫法對固體火箭羽焰真溫進(jìn)行測量,旨在:探索發(fā)射率樣本選擇的理論依據(jù),在此基礎(chǔ)上研究真溫構(gòu)建的新方法;研制用于固體火箭羽焰真溫測量的寬量程光纖式多波長高溫計,解決現(xiàn)有多波長高溫計無法獲得1173K以下羽焰真溫的問題;研究一種新的有效波長標(biāo)定方法,解決傳統(tǒng)標(biāo)定方法因信號太弱而無法用于光纖式多波長高溫計有效波長標(biāo)定的問題。基于以上目的,本文開展了固體火箭發(fā)動機羽焰真溫測量技術(shù)的研究工作。本文的主要研究內(nèi)容如下:(1)針對傳統(tǒng)多波長真溫求解方法中發(fā)射率樣本選擇缺少理論依據(jù)的問題,提出了一種基于模型約束的多波長真溫構(gòu)建方法。概述了傳統(tǒng)多波長真溫求解方法,分析了傳統(tǒng)方法存在的主要問題。在亮度溫度模型的基礎(chǔ)上,通過理論推導(dǎo)發(fā)現(xiàn)了亮度溫度變化和發(fā)射率變化之間的內(nèi)在關(guān)系,提出了具有普適性的發(fā)射率模型約束條件�；谠摷s束條件,建立了帶約束的多模型真溫構(gòu)建方法。仿真結(jié)果表明,相比二次測量法,該方法的計算速度最大可提升81.3%。該發(fā)射率模型約束條件可以有效篩選發(fā)射率樣本,為發(fā)射率樣本的選擇提供了理論基礎(chǔ)。(2)為解決在1173K以下采用單一黑體輻射源不能實現(xiàn)現(xiàn)有高溫計的寬量程標(biāo)定而無法測量羽焰真溫的問題,研制了一種用于固體火箭羽焰真溫測量的寬量程光纖式多波長高溫計。分析了固體火箭羽焰的輻射特性和羽焰測溫的實際需求,設(shè)計了高溫計的光學(xué)系統(tǒng)、電路系統(tǒng)和應(yīng)用程序。光學(xué)系統(tǒng)采用分離結(jié)構(gòu)和光纖遠(yuǎn)傳技術(shù),提高了高溫計的瞄準(zhǔn)性能和工作可靠性。電路系統(tǒng)采用并聯(lián)光電探測器陣列相鄰像元的方法和前置放大電路自動切換量程的方法,并針對900K~1173K溫區(qū)的溫度標(biāo)定提出了基于對數(shù)函數(shù)的標(biāo)定新方法,使高溫計的測溫下限達(dá)到了900K,將高溫計的溫度測量范圍拓寬至900K~2700K。(3)針對傳統(tǒng)有效波長標(biāo)定方法標(biāo)定光纖式多波長高溫計存在的實際問題,提出了一種基于溫度標(biāo)定的有效波長標(biāo)定新方法。分析了高溫計的傳統(tǒng)有效波長標(biāo)定方法。結(jié)合實際溫度標(biāo)定數(shù)據(jù),研究了高溫計溫度標(biāo)定數(shù)據(jù)的內(nèi)在規(guī)律�；谄绽士硕�,建立了不同標(biāo)定溫度點標(biāo)定數(shù)據(jù)與有效波長之間的關(guān)系模型,提出了由溫度標(biāo)定數(shù)據(jù)直接確定有效波長的求解方法。該方法不僅提供了一種快速獲取有效波長的新思路,而且避免了復(fù)雜耗時的標(biāo)定過程。分別采用仿真和實驗對該方法進(jìn)行了驗證。仿真結(jié)果顯示,溫度標(biāo)定值加入±1%的隨機誤差后,新方法得到的波長值與理論值之間的相對誤差小于4.7%,此時所得真溫的計算值與理論值之間的相對誤差的最大絕對值為0.7%。實驗結(jié)果表明,相比傳統(tǒng)標(biāo)定方法,新方法所得波長值的相對誤差的最大絕對值為1.9%,此時所得真溫值的絕對誤差的最大值為2.4K,表明該方法可行。(4)對高溫計的實驗結(jié)果和不確定度進(jìn)行了分析。采用本文所研制的高溫計在實驗室進(jìn)行了鹵鎢燈燈絲溫度和黑體輻射源溫度的測量實驗,結(jié)果表明了高溫計的正確性與合理性。測量了某固體火箭發(fā)動機地面試車時的羽焰真溫變化全過程,并對實驗結(jié)果進(jìn)行了分析。利用該實驗數(shù)據(jù),進(jìn)一步驗證了基于模型約束的多波長真溫構(gòu)建方法的有效性。分析了該高溫計的測量不確定度,得出其合成不確定度為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%.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：博士
【學(xué)位授予年份】：2017
【分類號】：V435
本文編號：2394790
[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%.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：博士
【學(xué)位授予年份】：2017
【分類號】：V435
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