固体推进剂火箭发动机综合特性预示研究
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摘要
本文以某远程火箭研究工作为背景,为解决固体火箭发动机设计、性能分析、工作过程数值仿真和优选推进剂需要,对固体火箭发动机工作过程中的能量特性、燃烧特性、热物性参数确定和软件平台开发等展开了深入研究,主要内容如下：
1.完整推导了适于固体火箭发动机能量特性预示的Gibbs最小自由能法；分析了固体火箭发动机中各种可能存在的损失,引入实际因素分析法和综合因素归纳法,较好的解决了比冲实测值与理论值存在的较大偏差问题,大大提高了固体火箭发动机能量特性参数的预示精度。
2.针对细粒度AP分散性较差,会产生一定的团聚效应现象,通过引入工艺粒径,建立了适用于含细粒度AP的CMDB推进剂燃速预示公式；提出了催化剂在燃烧表面附近气相中进一步影响自由基团裂解行为的催化机理假说,合理构造了有物理意义的催化影响因子,建立了能够反映催化剂种类、含量的AP-Al-HTPB推进剂催化燃速预示公式,显著提高了燃速预示的精度,拓宽了燃速预示的适用范围。
3.总结研究了适于固体火箭发动机高温高压下多组分混合气体热物性参数的计算方法,最后,采用Lennard-Jones势能法和Svehla多项式法,解决了固体火箭发动机工作过程数值仿真中单组分和多组分混合气体的热物性参数确定问题,为提高固体火箭发动机工作过程数值仿真精度创造了条件。
4.以Microsoft Access数据库为平台,首次完全采用数据库结构建立和完善了涵盖配方、组元、产物组分热输运等庞杂的数据信息库。以Visual C++为开发工具,采用MFC ODBC数据访问接口技术,开发了基于数据库的人机界面友好、实际使用方便、专业性强的固体推进剂火箭发动机综合特性预示软件SRPS,为开展相关研究工作提供了应用平台,提高了理论预示方法的通用性和便捷性。
5.结合SRPS软件平台,成功完成了某远程火箭武器总体方案论证和性能预估工作,将比冲修正误差提高到2.0%以内,为有效减小距离散布提供了合理控制结构参数公差的理论判据,同时,为真实模拟某远程火箭Y-300发动机工作过程提供了准确的热物性参数,大大缩短了某远程火箭武器型号的研制周期,有效的降低了研制成本。
通过本文的研究,在能量特性、燃烧特性和热物性参数确定方面获得了较好的计算模型和处理方法,得到了令人满意的校验结果,结合开发的SRPS软件平台,为从事该领域的研究人员开展基础理论研究和工程应用提供了理论指导和技术支持。
Based on related development work of a certain remote rocket, In order to solve the problems of solid rocket engine design, performance analysis, numerical simulation of working process and optimization propellant, the further research on energy characteristic, combustion characteristic and thermal physical parameters determine in the working process of solid rocket engine and software platform development were carried out in this dissertation, its'main contents were as follows:
1. The Gibbs free energy minimization method for energy characteristic calculation of solid rocket engine was concretely educed. The various possible losses of solid rocket engine s were analyzed, the problem of obvious deviation between measured value and theoretical value for solid rocket engine was solved by introducing actual factor analysis and the induction of comprehensive factor, the prediction precision of performance of solid rocket engine was greatly improved.
2. Some phenomenon of agglomeration would occurred for fine-grained AP has a poor dispersion, so a burning rate prediction model for CMDB propellant with fine-grained AP was established by introducing process particle size; In addition, catalytic mechanism hypothesis was proposed, which the catalyst would further effected the cracking behavior of free radical clusters in the gas phase near the combustion surface, the catalystic impact factors with physical meaning were constructed, a catalystic burning rate prediction model of AP-Al-HTPB propellant which could reflect type and content of the catalyst was also established. Finally, the prediction precision of the burning rate was significantly improved, the prediction scope of the burning rate was also broadened.
3. Summarized the methods for calculating thermal physical parameters of multi-com-ponent gas with high pressure and high temperature in the solid rocket engine. By introducing the methods of Lennard-Jones potential energy and Svehla polynomia, the thermal physical parameters of one-component or multi-component gas in numerical simulation of working process of solid rocket engine were well determined, some conditions were created for improving numerical simulation precision in the working process of solid rocket engine.
4. With the platform of Microsoft Access database, the information database covered with numerous and jumbled data such as formula, component, thermal transport of the product composition was established and improved, which was firstly and fully used the database structure. Choosing Visual C++ as development tools, using MFC ODBC data access interface technology, the software SRPS based on database for synthetical performance prediction of solid propellant rocket engine was developed, which has a friendly interface, convenience in practice and high specialization. The application platform for related development work of solid propellant rocket engine was provided. The generality and convenience of theoretical prediction methods were improved.
5. With the platform of SRPS software, the general scheme demonstration and performance prediction of remote rocket weapon were successfully completed, the correcting errors of specific impulse was increased to 2.0%, a theoretical criterion of rationally controlling structure parameters tolerance for effectively reducing range dispersion was given, at the same time, thermal physical parameters for numerical simulation of working process of remote rocket Y-300 engine were given accurately, finally, the cycle and cost of development was greatly reduced.
Some good calculation models and approaches for energy characteristic, combustion characteristic and thermal physical parameters determine in the working process of solid rocket engine were obtained through this research, the check results were satisfactorily too, combined with the development platform of SRPS software, some theoretical guidance and technical support were provided, which were used fundamental research and engineering application.
1.完整推导了适于固体火箭发动机能量特性预示的Gibbs最小自由能法；分析了固体火箭发动机中各种可能存在的损失,引入实际因素分析法和综合因素归纳法,较好的解决了比冲实测值与理论值存在的较大偏差问题,大大提高了固体火箭发动机能量特性参数的预示精度。
2.针对细粒度AP分散性较差,会产生一定的团聚效应现象,通过引入工艺粒径,建立了适用于含细粒度AP的CMDB推进剂燃速预示公式；提出了催化剂在燃烧表面附近气相中进一步影响自由基团裂解行为的催化机理假说,合理构造了有物理意义的催化影响因子,建立了能够反映催化剂种类、含量的AP-Al-HTPB推进剂催化燃速预示公式,显著提高了燃速预示的精度,拓宽了燃速预示的适用范围。
3.总结研究了适于固体火箭发动机高温高压下多组分混合气体热物性参数的计算方法,最后,采用Lennard-Jones势能法和Svehla多项式法,解决了固体火箭发动机工作过程数值仿真中单组分和多组分混合气体的热物性参数确定问题,为提高固体火箭发动机工作过程数值仿真精度创造了条件。
4.以Microsoft Access数据库为平台,首次完全采用数据库结构建立和完善了涵盖配方、组元、产物组分热输运等庞杂的数据信息库。以Visual C++为开发工具,采用MFC ODBC数据访问接口技术,开发了基于数据库的人机界面友好、实际使用方便、专业性强的固体推进剂火箭发动机综合特性预示软件SRPS,为开展相关研究工作提供了应用平台,提高了理论预示方法的通用性和便捷性。
5.结合SRPS软件平台,成功完成了某远程火箭武器总体方案论证和性能预估工作,将比冲修正误差提高到2.0%以内,为有效减小距离散布提供了合理控制结构参数公差的理论判据,同时,为真实模拟某远程火箭Y-300发动机工作过程提供了准确的热物性参数,大大缩短了某远程火箭武器型号的研制周期,有效的降低了研制成本。
通过本文的研究,在能量特性、燃烧特性和热物性参数确定方面获得了较好的计算模型和处理方法,得到了令人满意的校验结果,结合开发的SRPS软件平台,为从事该领域的研究人员开展基础理论研究和工程应用提供了理论指导和技术支持。
Based on related development work of a certain remote rocket, In order to solve the problems of solid rocket engine design, performance analysis, numerical simulation of working process and optimization propellant, the further research on energy characteristic, combustion characteristic and thermal physical parameters determine in the working process of solid rocket engine and software platform development were carried out in this dissertation, its'main contents were as follows:
1. The Gibbs free energy minimization method for energy characteristic calculation of solid rocket engine was concretely educed. The various possible losses of solid rocket engine s were analyzed, the problem of obvious deviation between measured value and theoretical value for solid rocket engine was solved by introducing actual factor analysis and the induction of comprehensive factor, the prediction precision of performance of solid rocket engine was greatly improved.
2. Some phenomenon of agglomeration would occurred for fine-grained AP has a poor dispersion, so a burning rate prediction model for CMDB propellant with fine-grained AP was established by introducing process particle size; In addition, catalytic mechanism hypothesis was proposed, which the catalyst would further effected the cracking behavior of free radical clusters in the gas phase near the combustion surface, the catalystic impact factors with physical meaning were constructed, a catalystic burning rate prediction model of AP-Al-HTPB propellant which could reflect type and content of the catalyst was also established. Finally, the prediction precision of the burning rate was significantly improved, the prediction scope of the burning rate was also broadened.
3. Summarized the methods for calculating thermal physical parameters of multi-com-ponent gas with high pressure and high temperature in the solid rocket engine. By introducing the methods of Lennard-Jones potential energy and Svehla polynomia, the thermal physical parameters of one-component or multi-component gas in numerical simulation of working process of solid rocket engine were well determined, some conditions were created for improving numerical simulation precision in the working process of solid rocket engine.
4. With the platform of Microsoft Access database, the information database covered with numerous and jumbled data such as formula, component, thermal transport of the product composition was established and improved, which was firstly and fully used the database structure. Choosing Visual C++ as development tools, using MFC ODBC data access interface technology, the software SRPS based on database for synthetical performance prediction of solid propellant rocket engine was developed, which has a friendly interface, convenience in practice and high specialization. The application platform for related development work of solid propellant rocket engine was provided. The generality and convenience of theoretical prediction methods were improved.
5. With the platform of SRPS software, the general scheme demonstration and performance prediction of remote rocket weapon were successfully completed, the correcting errors of specific impulse was increased to 2.0%, a theoretical criterion of rationally controlling structure parameters tolerance for effectively reducing range dispersion was given, at the same time, thermal physical parameters for numerical simulation of working process of remote rocket Y-300 engine were given accurately, finally, the cycle and cost of development was greatly reduced.
Some good calculation models and approaches for energy characteristic, combustion characteristic and thermal physical parameters determine in the working process of solid rocket engine were obtained through this research, the check results were satisfactorily too, combined with the development platform of SRPS software, some theoretical guidance and technical support were provided, which were used fundamental research and engineering application.
引文
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