燃气舵气—固两相绕流数值模拟及试验研究
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摘要
燃气舵是垂直发射先进拦截导弹经常采用的推力矢量控制技术之一,广泛应用于地地、地空、舰舰等战术固体导弹。由于燃气舵控制技术具有控制导弹的方位角定向范围大、响应时间快、弹道最高点低等优点,近年来,许多国家的空空导弹也开始采用这种推力矢量控制技术。但是,与其它类型燃气舵控制的导弹相比,空空导弹能够提供的安装燃气舵的空间非常狭小,安装燃气舵后,发动机喷口的流场更加复杂,又由于燃气流是高温高压且含有多种固体颗粒的气-固两相流,对燃气舵的烧蚀严重。因此,开展燃气舵气-固两相绕流及相应条件下的气动特性研究,就显得非常有意义。本文以某空空导弹燃气舵为研究对象,采用数值模拟与试验相结合的手段,对燃气舵纯气相绕流流场和气-固两相流绕流流场及燃气舵气动特性进行了研究。主要研究内容为:
1.建立了燃气舵纯气相绕流流场的物理模型,采用含k-ε双方程模型的湍流时均方程组,给定方程组的边界条件,对燃气舵纯气相绕流流场进行了数值模拟。详细分析了舵偏角和舵间组合对燃气舵绕流流场结构的影响,给出了燃气舵力学性能随舵偏角的变化规律,为进一步研究气-固两相流中颗粒相对燃气舵气动特性和绕流流场结构的影响提供理论依据。
2.建立了燃气舵气-固两相绕流流场的物理模型,提出了针对该模型的燃气舵绕流流场计算处理方法和定解条件。通过数值计算,得到燃气舵和耳片的气动特性,分析讨论了影响燃气舵绕流流场结构和固体颗粒在燃气舵表面沉积特性的主要因素及其影响规律,研究了燃气舵升力、燃气舵阻力和耳片阻力随舵偏角的变化关系。
3.借助六分力试验系统,对某空空导弹燃气舵进行了台架试验,获得了部分舵偏角对应的升力和阻力等试验数据,通过与数值模拟结果的对比发现,二者吻合较好,验证了本文数值模拟结果的可靠性;通过进一步分析台架试验后的燃气舵烧蚀形貌、断口形貌、截面组织结构和不同位置的化学成分等,对燃气舵烧蚀机理进行了初探。
通过本文研究,得到了燃气舵的气动力特性,以及舵偏角、固体颗粒分布及壁面属性等对燃气舵绕流流场的影响规律。本文研究成果已成功应用于某型号空空导弹研究中,效果良好。实践表明,本文研究工作对某型号类空空导弹燃气舵的设计和应用具有指导意义,同时为后续开展该类燃气舵的烧蚀机理研究提供了参考依据。
As one kind of thrust vector control (TVC)technologies, the jet vane is often used to defending missiles, especially in vertically launched tactical solid missiles, such as GGM(ground to ground missiles), GAM(ground to air missiles), SSM(ship to ship missiles) and so on. Because of its advantages, including the big missile directional scopes produced by jet vanes' azimuth, the short response times and the lower ballistic path highest points, this kind of TVC technology has been gradually used in AAM(air to air missiles) in many countries recently. However, after installing jet vanes in the narrow space near the AAM motor nozzle, the gas flow field changes extremely complex. In the meantime, the gas-flow with high temperature and high pressure contains some solid particles, and it will ablate and erode the jet vane badly. Therefore, it is very important and necessary to specially research the gas-solid two phase flow properties, the jet vane geometric structure design and its aerodynamic properties. Aiming at above problems, in this thesis, the pure gas phase flow and the gas-solid two phase flow around the jet vane and the aerodynamic properties of jet vane are studied by using the numerical simulation method and tests. The main researches are as follows:
1. Based on k-s two equations, the physical model of pure gas phase flow fields around the jet vane is established and the relevant boundary conditions and numerical method are given. By the numerical simulation, the flow field structures around the jet vane and aerodynamic properties of the jet vane are obtained under the different rotation angles. These data is helpful for the researching on the gas-solid two phase flow properties.
2. Establishing the physical model of the gas-solid two phase flow around the jet vane, the corresponding boundary conditions of the flow fields are proposed and the numerical simulation is carried out. The aerodynamic properties of jet vanes and bases are obtained. The main influence factors on the flow field structure and the particle deposition on jet vane surfaces and the relations between those factors are analyzed. The lift forces and resistance forces of jet vanes and bases at different rotational angles are given.
3. With the aid of the six component force test equipment, the bench test of the jet vane controlled missile is carried on. For the concerned lift forces and resistance forces at different rotational angles, their test and calculated data are in better accordance. It is proved that the numerical simulation and mathematical model in this paper are accurate and credible, and they can be effectively used for the aerodynamics properties design of jet vane. Additionally, the ablation images, fracture images, cross section microstructures and EDS chemical constituents at different positions of the jet vane after the bench test are analyzed, and the ablation mechanism is primarily studied.
This paper researches the aerodynamic properties of the jet vane and the influence laws of the jet vane rotation angles, the distribution of solid particles and the wall property on the flow fields around the jet vane. These results are significant to the design and application of AAM, and supply a fundament to the theory research of ablation mechanism of this kind of jet vanes.
1.建立了燃气舵纯气相绕流流场的物理模型,采用含k-ε双方程模型的湍流时均方程组,给定方程组的边界条件,对燃气舵纯气相绕流流场进行了数值模拟。详细分析了舵偏角和舵间组合对燃气舵绕流流场结构的影响,给出了燃气舵力学性能随舵偏角的变化规律,为进一步研究气-固两相流中颗粒相对燃气舵气动特性和绕流流场结构的影响提供理论依据。
2.建立了燃气舵气-固两相绕流流场的物理模型,提出了针对该模型的燃气舵绕流流场计算处理方法和定解条件。通过数值计算,得到燃气舵和耳片的气动特性,分析讨论了影响燃气舵绕流流场结构和固体颗粒在燃气舵表面沉积特性的主要因素及其影响规律,研究了燃气舵升力、燃气舵阻力和耳片阻力随舵偏角的变化关系。
3.借助六分力试验系统,对某空空导弹燃气舵进行了台架试验,获得了部分舵偏角对应的升力和阻力等试验数据,通过与数值模拟结果的对比发现,二者吻合较好,验证了本文数值模拟结果的可靠性;通过进一步分析台架试验后的燃气舵烧蚀形貌、断口形貌、截面组织结构和不同位置的化学成分等,对燃气舵烧蚀机理进行了初探。
通过本文研究,得到了燃气舵的气动力特性,以及舵偏角、固体颗粒分布及壁面属性等对燃气舵绕流流场的影响规律。本文研究成果已成功应用于某型号空空导弹研究中,效果良好。实践表明,本文研究工作对某型号类空空导弹燃气舵的设计和应用具有指导意义,同时为后续开展该类燃气舵的烧蚀机理研究提供了参考依据。
As one kind of thrust vector control (TVC)technologies, the jet vane is often used to defending missiles, especially in vertically launched tactical solid missiles, such as GGM(ground to ground missiles), GAM(ground to air missiles), SSM(ship to ship missiles) and so on. Because of its advantages, including the big missile directional scopes produced by jet vanes' azimuth, the short response times and the lower ballistic path highest points, this kind of TVC technology has been gradually used in AAM(air to air missiles) in many countries recently. However, after installing jet vanes in the narrow space near the AAM motor nozzle, the gas flow field changes extremely complex. In the meantime, the gas-flow with high temperature and high pressure contains some solid particles, and it will ablate and erode the jet vane badly. Therefore, it is very important and necessary to specially research the gas-solid two phase flow properties, the jet vane geometric structure design and its aerodynamic properties. Aiming at above problems, in this thesis, the pure gas phase flow and the gas-solid two phase flow around the jet vane and the aerodynamic properties of jet vane are studied by using the numerical simulation method and tests. The main researches are as follows:
1. Based on k-s two equations, the physical model of pure gas phase flow fields around the jet vane is established and the relevant boundary conditions and numerical method are given. By the numerical simulation, the flow field structures around the jet vane and aerodynamic properties of the jet vane are obtained under the different rotation angles. These data is helpful for the researching on the gas-solid two phase flow properties.
2. Establishing the physical model of the gas-solid two phase flow around the jet vane, the corresponding boundary conditions of the flow fields are proposed and the numerical simulation is carried out. The aerodynamic properties of jet vanes and bases are obtained. The main influence factors on the flow field structure and the particle deposition on jet vane surfaces and the relations between those factors are analyzed. The lift forces and resistance forces of jet vanes and bases at different rotational angles are given.
3. With the aid of the six component force test equipment, the bench test of the jet vane controlled missile is carried on. For the concerned lift forces and resistance forces at different rotational angles, their test and calculated data are in better accordance. It is proved that the numerical simulation and mathematical model in this paper are accurate and credible, and they can be effectively used for the aerodynamics properties design of jet vane. Additionally, the ablation images, fracture images, cross section microstructures and EDS chemical constituents at different positions of the jet vane after the bench test are analyzed, and the ablation mechanism is primarily studied.
This paper researches the aerodynamic properties of the jet vane and the influence laws of the jet vane rotation angles, the distribution of solid particles and the wall property on the flow fields around the jet vane. These results are significant to the design and application of AAM, and supply a fundament to the theory research of ablation mechanism of this kind of jet vanes.
引文
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