乘波体结构热响应及防护问题研究
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摘要
高超音速飞行器技术因其高度的科技前沿性和巨大的战略应用价值而受到各国青睐。当前,航空、航天重大力学问题已被列入《国家中长期科学和技术发展规划纲要》,使得发展高超音速飞行器的若干技术问题显得更为突出。面对未来航天飞行器普通化与普通飞行器航天化的航空与航天技术的一体化融合趋势,本文依托发展高超音速吸气式飞行器这条主线,选取乘波体为研究对象,围绕乘波体的设计与优化、壁面热流预测、结构气动加热响应及热防护等问题开展了下列研究工作：
首先,基于锥型流场理论,以激波角、半展角、膨胀角、长宽比和底面函数系数为设计控制参数,在30km大气高度、来流马赫数为6条件下设计生成了锥导乘波体构型。在分析各设计控制参数对乘波体构型升阻比、容积效率等性能影响的基础上,引入复合形法,对生成体进行了升力重力匹配、上表面等熵膨胀等优化处理,获得了设计点条件下的乘波体优化外形；
其次,在分析钝体结构热防护效果的基础上,以生成的乘波体构型为研究对象,对气动加热最为严重的前缘锋锐区域进行钝化处理。通过数值试验获取了设计点飞行状态下乘波体构型的绕流流场特性及近壁面处的气动力参数,并结合工程方法,预测了乘波体构型壁面的气动加热热流；
再次,对气动加热最为严重的乘波体前缘区域进行流固耦合分析,研究了乘波体前缘在流动冲击及气动加热作用下的变形响应。通过考察结构温度场和热应力场分布,分析了结构热变形所诱发的热应力问题,初步了解了乘波体前缘结构对流动冲击及气动加热的响应,为结构防热设计和强度设计提供一定的参考；
最后,结合具体试验,对喷流热防护及其工程应用问题展开研究。分析了反向喷流热防护机理及干扰激波波后流场的振荡特性,研究了反向喷流与主流干扰流场的稳定性对热防护效果的影响。对气动加热最为严重的乘波体锋锐前缘区域,采用数值模拟验证了喷流热防护对锋锐前缘结构的热防护效果。
综上所述,本文针对高超音速乘波体,从外形设计、气动加热预测、结构响应及热防护等多个方面开展了较系统的研究,希望能够为工程设计提供一定的参考。
Hypersonic vehicle technology, for its highly scientific and technological frontier nature and great strategic application value, is favored by all. Currently, major mechanical problems of aviation and aerospace have been listed in the Outline of National Long-and Mid-term Science and Technology Development Plan, which makes some technical problems concerning the development of hypersonic vehicle appear more prominent. Facing with the tendency of integration and fusion of aviation and aerospace technology and generalization of aerospace flying vehicle and spacialization of general flying vehicle in the future, this dissertation conducts the following research relying on the masterstroke of the development of hypersonic air-breathing vehicle, selecting waverider as the research object, centering on the issues such as design and optimization of waverider, prediction of wall heating flux, response of structural aerodynamic heating and thermal protection:
Firstly, based on the theory of conical flow field, with shock angle, semi-spanwise angle, expansion angle, length-to-span ratio and function coefficient as design control parameters, cone-derived waverider configuration is generated under conditions of mach number 6 and 30km high atmosphere. On the basis of the analysis of the effect of the design control parameters on the performance of the lift-to-drag ratio of the waverider configuration, volume efficiency and etc., complex method is introduced to optimize and process the matching of lift to weight and top surface isentropic expansion of the generated waverider and the optimized shape of waverider is obtained under the design condition.
Secondly, on the basis of the analysis of the thermal protection effect of blunt body structure, taking the generated waverider configuration as the research object, the sharp leading edge, which is the most serious aerodynamic heating area, is blunted. Through numerical simulation characteristics of flow over waverider configuration and the aerodynamic parameters near the wall under the flying state from the designed points are obtained. In combination with the engineering method, the heating flux caused by aerodynamic heating of the waverider configuration wall is predicted.
Thirdly, the dissertation analyzes the fluid structure interaction of leading edge of the waverider configuration, the most serious aerodynamic heating area, studies the deformation of the leading edge of the waverider in the function of flow impact and aerodynamic heating and analyzes the interaction effect from the structural deformation to the flow field. The distribution of structural temperature field and thermal stress field is also inspected. A preliminary understanding of the response to flow impact and aerodynamic heating response is achieved, providing certain reference for the design of structural thermal protection.
Finally, combined with specific experiment, the dissertation studies the issue of opposing jet thermal protection and its engineering application, analyzes the mechanism of reverse opposing jet thermal protection and the characteristics of the oscillations of the flow field after the interference wave and studies the effect of the stability of reverse opposing jet and the mainstream of flow field on thermal protection. Measures of opposing jet thermal protection are adopted for the sharp leading edge of the waverider, the most serious aerodynamic heating area. The numerical simulation verified the thermal protection effect of opposing jet thermal protection for the sharp leading edge structure.
To sum up, taking hypersonic waverider for example, the dissertation conducts a comparatively systematic research on the appearance design, aerodynamic heating prediction, structural response and thermal protection. However, studies on the various researches on the work are still weak and have many shortcomings. It is expected that the dissertation can provide certain reference for project design problem.
首先,基于锥型流场理论,以激波角、半展角、膨胀角、长宽比和底面函数系数为设计控制参数,在30km大气高度、来流马赫数为6条件下设计生成了锥导乘波体构型。在分析各设计控制参数对乘波体构型升阻比、容积效率等性能影响的基础上,引入复合形法,对生成体进行了升力重力匹配、上表面等熵膨胀等优化处理,获得了设计点条件下的乘波体优化外形；
其次,在分析钝体结构热防护效果的基础上,以生成的乘波体构型为研究对象,对气动加热最为严重的前缘锋锐区域进行钝化处理。通过数值试验获取了设计点飞行状态下乘波体构型的绕流流场特性及近壁面处的气动力参数,并结合工程方法,预测了乘波体构型壁面的气动加热热流；
再次,对气动加热最为严重的乘波体前缘区域进行流固耦合分析,研究了乘波体前缘在流动冲击及气动加热作用下的变形响应。通过考察结构温度场和热应力场分布,分析了结构热变形所诱发的热应力问题,初步了解了乘波体前缘结构对流动冲击及气动加热的响应,为结构防热设计和强度设计提供一定的参考；
最后,结合具体试验,对喷流热防护及其工程应用问题展开研究。分析了反向喷流热防护机理及干扰激波波后流场的振荡特性,研究了反向喷流与主流干扰流场的稳定性对热防护效果的影响。对气动加热最为严重的乘波体锋锐前缘区域,采用数值模拟验证了喷流热防护对锋锐前缘结构的热防护效果。
综上所述,本文针对高超音速乘波体,从外形设计、气动加热预测、结构响应及热防护等多个方面开展了较系统的研究,希望能够为工程设计提供一定的参考。
Hypersonic vehicle technology, for its highly scientific and technological frontier nature and great strategic application value, is favored by all. Currently, major mechanical problems of aviation and aerospace have been listed in the Outline of National Long-and Mid-term Science and Technology Development Plan, which makes some technical problems concerning the development of hypersonic vehicle appear more prominent. Facing with the tendency of integration and fusion of aviation and aerospace technology and generalization of aerospace flying vehicle and spacialization of general flying vehicle in the future, this dissertation conducts the following research relying on the masterstroke of the development of hypersonic air-breathing vehicle, selecting waverider as the research object, centering on the issues such as design and optimization of waverider, prediction of wall heating flux, response of structural aerodynamic heating and thermal protection:
Firstly, based on the theory of conical flow field, with shock angle, semi-spanwise angle, expansion angle, length-to-span ratio and function coefficient as design control parameters, cone-derived waverider configuration is generated under conditions of mach number 6 and 30km high atmosphere. On the basis of the analysis of the effect of the design control parameters on the performance of the lift-to-drag ratio of the waverider configuration, volume efficiency and etc., complex method is introduced to optimize and process the matching of lift to weight and top surface isentropic expansion of the generated waverider and the optimized shape of waverider is obtained under the design condition.
Secondly, on the basis of the analysis of the thermal protection effect of blunt body structure, taking the generated waverider configuration as the research object, the sharp leading edge, which is the most serious aerodynamic heating area, is blunted. Through numerical simulation characteristics of flow over waverider configuration and the aerodynamic parameters near the wall under the flying state from the designed points are obtained. In combination with the engineering method, the heating flux caused by aerodynamic heating of the waverider configuration wall is predicted.
Thirdly, the dissertation analyzes the fluid structure interaction of leading edge of the waverider configuration, the most serious aerodynamic heating area, studies the deformation of the leading edge of the waverider in the function of flow impact and aerodynamic heating and analyzes the interaction effect from the structural deformation to the flow field. The distribution of structural temperature field and thermal stress field is also inspected. A preliminary understanding of the response to flow impact and aerodynamic heating response is achieved, providing certain reference for the design of structural thermal protection.
Finally, combined with specific experiment, the dissertation studies the issue of opposing jet thermal protection and its engineering application, analyzes the mechanism of reverse opposing jet thermal protection and the characteristics of the oscillations of the flow field after the interference wave and studies the effect of the stability of reverse opposing jet and the mainstream of flow field on thermal protection. Measures of opposing jet thermal protection are adopted for the sharp leading edge of the waverider, the most serious aerodynamic heating area. The numerical simulation verified the thermal protection effect of opposing jet thermal protection for the sharp leading edge structure.
To sum up, taking hypersonic waverider for example, the dissertation conducts a comparatively systematic research on the appearance design, aerodynamic heating prediction, structural response and thermal protection. However, studies on the various researches on the work are still weak and have many shortcomings. It is expected that the dissertation can provide certain reference for project design problem.
引文
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