一种新型发射药燃烧性能测试和内弹道数值计算方法研究
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摘要
本文针对现有发射药燃烧性能测试和数据处理方法、内弹道数值计算方法的不足之处,研究了发射药燃烧性能测试中采集数据的滤波、试验热散失的修正和数据处理结果表征的新方法,同时对膛内热散失和基于发射药燃气生成规律的内弹道数值计算方法进行了研究。
针对密闭爆发器试验采集信号中的噪声会掩盖发射药燃烧局部特征的状况,对基于有限冲激响应(FIR)低通滤波器和最小二乘回归滤波器的组合数字滤波器(FI-LS)进行研究,提出了基于FI-LS滤波器的密闭爆发器p-t数据滤波方法,并给出了该方法的基本步骤；分析了密闭爆发器试验过程中发射药燃气与其内壁传热的特点,针对密闭爆发器试验过程中压力变化迅速的现象,提出了考虑压力变化因素的热流密度方程,推导出试验过程中的传热表达式,建立了考虑压力因素的密闭爆发器试验一维半无限大传热模型；在FI-LS滤波和修正热散失的基础上,提出了能够表征发射药燃速压力指数随压力变化关系的n～p曲线方法,编制了可视化的发射药燃烧性能测试软件；对多孔发射药的燃烧特性进行了研究,分析了多孔发射药燃烧时孔径变化对燃速、燃速压力指数测试结果的影响,并对不同药长多孔发射药的燃烧特性进行研究,提出了更接近较短药长多孔发射药燃烧特性的不同时燃烧理论；针对发射药装药内弹道性能预估时膛内热散失修正程度难以确定的问题,提出了基于密闭爆发器试验的火炮膛内传热计算方法,根据试验测得的压力与时间信号和发射药燃气在密闭环境中作功能力与压力之间的关系,提出发射药燃气与膛壁的传热方程,结合内弹道方程组,建立了考虑火炮膛内热散失的内弹道模型；通过发射药中止燃烧试验和密闭爆发器试验,研究了多孔发射药的燃烧特性,提出利用ψ,Tt的关系表征多孔发射药燃气生成规律的方法,结合提出的发射药燃气与膛壁的传热方程,建立了考虑膛内热散失的基于多孔发射药实测燃气生成规律的内弹道模型,编制相应的内弹道程序。
研究结果对于提高装药设计研究者了解装药的实际燃烧特性,促进装药技术的发展具有重要的意义。
In this paper, new methods of the digital filter, heat loss modification and the expression of data processing in propellant burning performance tests were studied in order to improve the deficiency of the existing method of testing, data processing and calculation method. Meanwhile, heat loss in the gun barrel and the calculation method of the interior ballistics based on the propellant burning gases generation rules were researched.
In order to slake the noises from pressure signal obtained from the closed bomb tests and express the burning property of propellant more actually, a FI-LS digital filter which combines with FIR lowpass filter and least squares filter was researched, and a new p-t digital filter method was proposed. Analyzing the characteristic of heat transfer between the propellants burning gases and the inner wall, and focusing on the phenomenon of rapid pressure change in closed bomb tests, a heat flux equation considering the pressure change as a factor was raised. The heat transfer function in the test was deduced, and a one-dimensional semi-infinite heat transfer model in the closed bomb test was established. Based on the FI-LS digital filter and the heat loss modification, an n～p curve method were proposed in order to describe the relationship between the propellants burning rate pressure exponent and the pressure, and a visual basic software for propellants combustion performance test was compiled. This paper also studied the combustion characteristics of the multi-perforation propellants. The effect of the aperture change on the propellant burning rate and burning rate pressure exponent was analyzed when propellants were burning, and the burning performance of different length multi-perforation propellants were studied, a asynchronous combustion theory which was closer to the burning characteristics of short multi-perforation propellants was proposed. As it's difficult to determine the heat loss modification degree when calculating the interior ballistics performance of propellants charge, a heat transfer calculation method in the gun chamber were proposed based on the closed bomb test. According to the pressure and time signals, and the relationship between the pressure and work capability of propellants burning gases in a closed environment, an equation of heat transfer between the propellant burning gases and the chamber wall was given. Based on the interior ballistics equations and heat transfer equation, an interior ballistics simulation model which considered the heat loss in the gun chamber was established. The burning performances of the multi-perforation propellants were studied through the interrupted combustion test and the closed bomb text. A method was raised to characterize multi-perforation propellants burning gases generation rule by using the relationship betweenΨand It, and according to the equation of heat transfer between the propellants burning gases and the chamber wall, a new interior ballistics model which considering the heat loss and burning gases generation rule was built, and the corresponding interior ballistics simulation program was also compiled.
The study productions are significant to improve the understanding for actual burning performance of propellant and promote the development of propellant charge technology.
针对密闭爆发器试验采集信号中的噪声会掩盖发射药燃烧局部特征的状况,对基于有限冲激响应(FIR)低通滤波器和最小二乘回归滤波器的组合数字滤波器(FI-LS)进行研究,提出了基于FI-LS滤波器的密闭爆发器p-t数据滤波方法,并给出了该方法的基本步骤；分析了密闭爆发器试验过程中发射药燃气与其内壁传热的特点,针对密闭爆发器试验过程中压力变化迅速的现象,提出了考虑压力变化因素的热流密度方程,推导出试验过程中的传热表达式,建立了考虑压力因素的密闭爆发器试验一维半无限大传热模型；在FI-LS滤波和修正热散失的基础上,提出了能够表征发射药燃速压力指数随压力变化关系的n～p曲线方法,编制了可视化的发射药燃烧性能测试软件；对多孔发射药的燃烧特性进行了研究,分析了多孔发射药燃烧时孔径变化对燃速、燃速压力指数测试结果的影响,并对不同药长多孔发射药的燃烧特性进行研究,提出了更接近较短药长多孔发射药燃烧特性的不同时燃烧理论；针对发射药装药内弹道性能预估时膛内热散失修正程度难以确定的问题,提出了基于密闭爆发器试验的火炮膛内传热计算方法,根据试验测得的压力与时间信号和发射药燃气在密闭环境中作功能力与压力之间的关系,提出发射药燃气与膛壁的传热方程,结合内弹道方程组,建立了考虑火炮膛内热散失的内弹道模型；通过发射药中止燃烧试验和密闭爆发器试验,研究了多孔发射药的燃烧特性,提出利用ψ,Tt的关系表征多孔发射药燃气生成规律的方法,结合提出的发射药燃气与膛壁的传热方程,建立了考虑膛内热散失的基于多孔发射药实测燃气生成规律的内弹道模型,编制相应的内弹道程序。
研究结果对于提高装药设计研究者了解装药的实际燃烧特性,促进装药技术的发展具有重要的意义。
In this paper, new methods of the digital filter, heat loss modification and the expression of data processing in propellant burning performance tests were studied in order to improve the deficiency of the existing method of testing, data processing and calculation method. Meanwhile, heat loss in the gun barrel and the calculation method of the interior ballistics based on the propellant burning gases generation rules were researched.
In order to slake the noises from pressure signal obtained from the closed bomb tests and express the burning property of propellant more actually, a FI-LS digital filter which combines with FIR lowpass filter and least squares filter was researched, and a new p-t digital filter method was proposed. Analyzing the characteristic of heat transfer between the propellants burning gases and the inner wall, and focusing on the phenomenon of rapid pressure change in closed bomb tests, a heat flux equation considering the pressure change as a factor was raised. The heat transfer function in the test was deduced, and a one-dimensional semi-infinite heat transfer model in the closed bomb test was established. Based on the FI-LS digital filter and the heat loss modification, an n～p curve method were proposed in order to describe the relationship between the propellants burning rate pressure exponent and the pressure, and a visual basic software for propellants combustion performance test was compiled. This paper also studied the combustion characteristics of the multi-perforation propellants. The effect of the aperture change on the propellant burning rate and burning rate pressure exponent was analyzed when propellants were burning, and the burning performance of different length multi-perforation propellants were studied, a asynchronous combustion theory which was closer to the burning characteristics of short multi-perforation propellants was proposed. As it's difficult to determine the heat loss modification degree when calculating the interior ballistics performance of propellants charge, a heat transfer calculation method in the gun chamber were proposed based on the closed bomb test. According to the pressure and time signals, and the relationship between the pressure and work capability of propellants burning gases in a closed environment, an equation of heat transfer between the propellant burning gases and the chamber wall was given. Based on the interior ballistics equations and heat transfer equation, an interior ballistics simulation model which considered the heat loss in the gun chamber was established. The burning performances of the multi-perforation propellants were studied through the interrupted combustion test and the closed bomb text. A method was raised to characterize multi-perforation propellants burning gases generation rule by using the relationship betweenΨand It, and according to the equation of heat transfer between the propellants burning gases and the chamber wall, a new interior ballistics model which considering the heat loss and burning gases generation rule was built, and the corresponding interior ballistics simulation program was also compiled.
The study productions are significant to improve the understanding for actual burning performance of propellant and promote the development of propellant charge technology.
引文
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