液体火箭发动机响应特性研究及稳定性的非线性分析
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摘要
动态特性包括响应特性和稳定性,本文采用理论分析、数值仿真和试验研究等手段对目前这两方面研究的不足及存在的难题开展了深入的研究工作。设计了用于液氧流量调节的低温可调汽蚀文氏管;建立了低温可调汽蚀文氏管汽蚀状态和非汽蚀状态下统一的动力学模型;对低温流量控制系统进行了大量冷态、热态试验,得到了流量系数、压力恢复系数随文氏管入口压力及调节针锥位移的变化规律,并成功实现了多级流量调节和工况转换。
建立了两位五通常开式电动气阀、杠杆式气动液阀的动力学模型;分析了控制气体压力、最大气隙以及工作电压等因素对电动过程的影响;分析了控制气体压力、控制腔容腔半径、与电动气阀之间连接管长度以及工质腔入口压力等因素对气动液阀启动过程的影响;对电动气阀和气动液阀联立时的工作特性进行了大量试验研究。
建立了三组元工况和两组元工况下统一的燃烧室模型;对三组元发动机地面试验系统的常温和低温推进剂充填过程、起动时序、转工况时序以及动态响应过程进行了深入的仿真研究,提出了用液体体积分数来直观描述容腔的充填过程;进行了大量地面热态试验,验证仿真分析的结果。
首次将基于相空间重构的非线性时间序列分析方法用于液体火箭发动机稳定性分析中,从一个全新的视角来研究复杂的液体火箭发动机系统的稳定性,得到发动机工作的稳定性极限,揭示出系统的动力学本质,为解决系统稳定性和燃烧过程稳定性这一理论和工程上的难题提供新的思路和手段。
非线性时间序列分析的基础是干净、真实的时间序列数据,本文对现有小波去噪方法进行改进,提出了一种基于小波变换模极大值与阈值决策相融合的去噪方法。该方法融合了小波变换模极大值去噪法和阈值去噪法的优点,克服了将非模极大值点的小波系数全部置为0,从而舍弃部分有用信息的缺陷,也克服了对阈值简单设置的不足,针对不同尺度下模极大值的情况,进行合理的阈值设置;利用经典的Lorenz非线性动力系统对改进方法进行验证,结果表明改进方法具有精度高、算法简单、计算效率高的优点;利用改进方法对PCB高频压力传感器测得的试验数据进行去噪处理,既达到了良好的去噪效果,又保留了原始信号的主要特征。
对基于相空间重构的非线性时间序列分析进行了深入的理论研究,开发出重构参数(时间延迟、嵌入维数)、关联维数和最大Lyapunov指数的计算程序;针对三组元发动机地面试验系统,首次计算出正常工况下发动机系统的关联维数在2.9和3.2之间,最大Lyapunov指数在0.0006和0.001之间。且利用两种非线性特征量的突变,可以检测出发动机的故障以及看似正常的燃烧室压力脉动曲线对应的参数稳定性边界。
对三组元发动机地面试验系统的客观试验数据进行了基于相空间重构的非线性时间序列分析,定量计算出:氢含量的稳定性边界是12%左右,氢温度的稳定性边界是112K左右,氢喷注压降的稳定性边界为室压的16%左右,一旦低于这些边界,系统就容易激发不稳定;余氧系数的稳定性裕度较宽,在0.6~1的范围内发动机都可以正常工作,这利于工况设定。
Dynamic characteristic includes response characteristic and stability. The shortcoming and problems of these two parts are resolved in the thesis by means of theoretical analysis, numerical simulation, and experiment research.
The cryogenic throttling venturi is designed for liquid oxygen in the thesis. Uniform dynamic models of throttling Venturi are established when Venturi is cavitated or not. Large numbers of cold tests and firing tests are taken based on the mass flow control system, which show the system can control the mass flow of liquid oxygen accurately and change the operating conditions successfully. By the tests, the rules of discharge coefficient and pressure recovery factor changing with inlet pressure of Venturi and the displacement of the tapered rod are found.
The dynamic models of the electro-pneumatic valve and the lever pneumatic liquid valve are established. The effects of the pressure of control gas and voltage etc. on the electro motion are analyzed in the thesis. And the effects of the pressure of control gas, radius of the control cavity, the length between the solenoid valve and the pneumatic valve, the inlet pressure of the propellant etc. on the startup of the pneumatic valve are also analyzed in the thesis. Many experiments are taken to study the response characteristic of the electro-pneumatic valve and the lever pneumatic liquid valve.
Uniform dynamic models of the combustion chamber are established for tripropellant mode and twipropellant mode. The dynamic response processes of the ground test system of the tripropellant model engine are studied detailedly, which include the priming process of normal temperature and cryogenic propellants, the timing sequence of startup and mode-transition. The liquid volume fraction is proposed to describe the priming process of the cavity. Large numbers of ground firing tests are taken to validate the simulation results.
Nonlinear time series analysis based on phase space reconstruction is introduced to analyze the stability of liquid rocket engine for the first time, which is a new visual angle to study the stability of complicated engine system. The new method can give the boundary of stability and reveal the dynamics essence of the engine system. It can provide a brand-new method to resolve system dynamic instability and combustion instability, which are difficult problems in theory and engineering.
The foundation of nonlinear time series analysis is clean and real data. A new wavelet-denoising method is proposed in the thesis, which is based on wavelet transform modulus maximum and nonlinear threshold denoising method on wavelet. This method absorbs the advantages and overcomes the disadvantages of traditional methods. Lorenz system is used to validate the improved method, which shows the new method has the advantage of the high precision and the simple arithmetic and the high computing efficiency. And the improved method is used to denoise the test data. The results show it can denoise very well and also keep the important information of the test data.
The in-depth theory study of nonlinear time series analysis based on phase space reconstruction is taken in the thesis. The program is developed to compute the reconstruction parameter including the time delay and the embedding dimension, correlation dimension and maximum Lyapunov exponent. For the ground test system of the tripropellant model engine, it’s the first time to compute correlation dimension between 2.9 and 3.2 and maximum Lyapunov exponent between 0.0006 and 0.001 when the state of engine is normal. The abrupt change of correlation dimension and maximum Lyapunov exponent can detect the fault of the engine and decide the boundary of stability.
Nonlinear time series analysis based on phase space reconstruction is used to analyze the data from experiments of the ground test system of the tripropellant model engine. The results show the stability boundary of hydrogen percentage is about 12% and hydrogen temperature is about 112K and hydrogen injection pressure drop is about 16 percent of the combustion chamber pressure. Once these parameters are under the boundary, instability may be excitated. The range of stability of the oxygen-fuel ratio is broad. Engine can work normally when the oxygen-fuel ratio is between 0.6 and 1, which is advantageous for liquid rocket engine.
建立了两位五通常开式电动气阀、杠杆式气动液阀的动力学模型;分析了控制气体压力、最大气隙以及工作电压等因素对电动过程的影响;分析了控制气体压力、控制腔容腔半径、与电动气阀之间连接管长度以及工质腔入口压力等因素对气动液阀启动过程的影响;对电动气阀和气动液阀联立时的工作特性进行了大量试验研究。
建立了三组元工况和两组元工况下统一的燃烧室模型;对三组元发动机地面试验系统的常温和低温推进剂充填过程、起动时序、转工况时序以及动态响应过程进行了深入的仿真研究,提出了用液体体积分数来直观描述容腔的充填过程;进行了大量地面热态试验,验证仿真分析的结果。
首次将基于相空间重构的非线性时间序列分析方法用于液体火箭发动机稳定性分析中,从一个全新的视角来研究复杂的液体火箭发动机系统的稳定性,得到发动机工作的稳定性极限,揭示出系统的动力学本质,为解决系统稳定性和燃烧过程稳定性这一理论和工程上的难题提供新的思路和手段。
非线性时间序列分析的基础是干净、真实的时间序列数据,本文对现有小波去噪方法进行改进,提出了一种基于小波变换模极大值与阈值决策相融合的去噪方法。该方法融合了小波变换模极大值去噪法和阈值去噪法的优点,克服了将非模极大值点的小波系数全部置为0,从而舍弃部分有用信息的缺陷,也克服了对阈值简单设置的不足,针对不同尺度下模极大值的情况,进行合理的阈值设置;利用经典的Lorenz非线性动力系统对改进方法进行验证,结果表明改进方法具有精度高、算法简单、计算效率高的优点;利用改进方法对PCB高频压力传感器测得的试验数据进行去噪处理,既达到了良好的去噪效果,又保留了原始信号的主要特征。
对基于相空间重构的非线性时间序列分析进行了深入的理论研究,开发出重构参数(时间延迟、嵌入维数)、关联维数和最大Lyapunov指数的计算程序;针对三组元发动机地面试验系统,首次计算出正常工况下发动机系统的关联维数在2.9和3.2之间,最大Lyapunov指数在0.0006和0.001之间。且利用两种非线性特征量的突变,可以检测出发动机的故障以及看似正常的燃烧室压力脉动曲线对应的参数稳定性边界。
对三组元发动机地面试验系统的客观试验数据进行了基于相空间重构的非线性时间序列分析,定量计算出:氢含量的稳定性边界是12%左右,氢温度的稳定性边界是112K左右,氢喷注压降的稳定性边界为室压的16%左右,一旦低于这些边界,系统就容易激发不稳定;余氧系数的稳定性裕度较宽,在0.6~1的范围内发动机都可以正常工作,这利于工况设定。
Dynamic characteristic includes response characteristic and stability. The shortcoming and problems of these two parts are resolved in the thesis by means of theoretical analysis, numerical simulation, and experiment research.
The cryogenic throttling venturi is designed for liquid oxygen in the thesis. Uniform dynamic models of throttling Venturi are established when Venturi is cavitated or not. Large numbers of cold tests and firing tests are taken based on the mass flow control system, which show the system can control the mass flow of liquid oxygen accurately and change the operating conditions successfully. By the tests, the rules of discharge coefficient and pressure recovery factor changing with inlet pressure of Venturi and the displacement of the tapered rod are found.
The dynamic models of the electro-pneumatic valve and the lever pneumatic liquid valve are established. The effects of the pressure of control gas and voltage etc. on the electro motion are analyzed in the thesis. And the effects of the pressure of control gas, radius of the control cavity, the length between the solenoid valve and the pneumatic valve, the inlet pressure of the propellant etc. on the startup of the pneumatic valve are also analyzed in the thesis. Many experiments are taken to study the response characteristic of the electro-pneumatic valve and the lever pneumatic liquid valve.
Uniform dynamic models of the combustion chamber are established for tripropellant mode and twipropellant mode. The dynamic response processes of the ground test system of the tripropellant model engine are studied detailedly, which include the priming process of normal temperature and cryogenic propellants, the timing sequence of startup and mode-transition. The liquid volume fraction is proposed to describe the priming process of the cavity. Large numbers of ground firing tests are taken to validate the simulation results.
Nonlinear time series analysis based on phase space reconstruction is introduced to analyze the stability of liquid rocket engine for the first time, which is a new visual angle to study the stability of complicated engine system. The new method can give the boundary of stability and reveal the dynamics essence of the engine system. It can provide a brand-new method to resolve system dynamic instability and combustion instability, which are difficult problems in theory and engineering.
The foundation of nonlinear time series analysis is clean and real data. A new wavelet-denoising method is proposed in the thesis, which is based on wavelet transform modulus maximum and nonlinear threshold denoising method on wavelet. This method absorbs the advantages and overcomes the disadvantages of traditional methods. Lorenz system is used to validate the improved method, which shows the new method has the advantage of the high precision and the simple arithmetic and the high computing efficiency. And the improved method is used to denoise the test data. The results show it can denoise very well and also keep the important information of the test data.
The in-depth theory study of nonlinear time series analysis based on phase space reconstruction is taken in the thesis. The program is developed to compute the reconstruction parameter including the time delay and the embedding dimension, correlation dimension and maximum Lyapunov exponent. For the ground test system of the tripropellant model engine, it’s the first time to compute correlation dimension between 2.9 and 3.2 and maximum Lyapunov exponent between 0.0006 and 0.001 when the state of engine is normal. The abrupt change of correlation dimension and maximum Lyapunov exponent can detect the fault of the engine and decide the boundary of stability.
Nonlinear time series analysis based on phase space reconstruction is used to analyze the data from experiments of the ground test system of the tripropellant model engine. The results show the stability boundary of hydrogen percentage is about 12% and hydrogen temperature is about 112K and hydrogen injection pressure drop is about 16 percent of the combustion chamber pressure. Once these parameters are under the boundary, instability may be excitated. The range of stability of the oxygen-fuel ratio is broad. Engine can work normally when the oxygen-fuel ratio is between 0.6 and 1, which is advantageous for liquid rocket engine.
引文
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