微尺度下含能材料的燃烧与推进原理研究
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摘要
为了研制高性能的固体化学微推进器,本文主要研究了微尺度下固体含能材料的燃烧特性及机理,微推进器的作功特性及其结构设计。
利用高速摄影技术研究了B/KNO3在微细石英管中燃烧时,燃速随圆管管径、燃烧室压强、圆管壁厚及管壁热传导系数的变化；建立了微细圆管内固体含能材料的燃烧传热模型,分析了圆管管径、壁厚及管壁热传导系数对热损失和燃烧稳定性的影响机理和规律。研究表明：圆管管径越小、燃烧室压强越小、管壁热传导系数越大,燃烧越不稳定；管壁热传导系数较小时,燃速随壁厚增加而增大；管壁热传导系数较大时,燃速随壁厚增加而减小；当壁厚增加到一定值时,壁厚对燃烧影响趋于稳定。
基于单摆原理测试分析了不同推进剂的作功性能随微推进器单元药室直径的变化规律。研究表明：相同药剂时,推力、冲量均随药室直径增加而增大；相同药室直径时,斯蒂酚酸铅类的推力较大、冲量较小,硝酸肼镍类的推力较小、冲量较大。
建立了微推力计算模型,分析了微喷管结构对推进性能的影响。0.1MPa环境压强下,微喷管存在一个最佳的出口扩张比；真空环境中,推力随出口扩张比增加而不断增大。
建立了化学微推进器阵列单元燃烧传热的数学物理模型和热应力有限元模型,计算分析了微推进阵列药室的结构和力学性能。结果表明：药室材料热传导系数越小、药剂燃烧时间越短,阵列集成度越高；药室孔边处热应力及变形量最大,是结构中最薄弱的环节；药室直径越大、药室单元间距越小、燃气温度越高、作用时间越长,阵列结构中热应力及变形量就越大,越易造成结构的破坏。
In order to development high performance solid chemical micro-thruster, characteristics and mechanisms of solid energetic materials combustion in microscale as well as work characteristics and structure design of micro-thruster were investigated by this dissertation.
Change of Burning rate of B/KNO3 varied with tube diameters, combustor pressures, wall thicknesses and wall thermal conductivities in microscale quartz tubes were obtained by the high-speed photography. Based on the mechanisms of combustion and thermal conduction, a model describing the process of combustion and thermal conduction of solid energetic materials burnt in a microtube was established. With the help of this model, effects and mechanisms of micro-tube dimensions, wall thicknesses and wall thermal conductivities on thermal loss and combustion stability were obtained by numerical simulation. Results show the stability was decreased with decreasing tube diameters, combustor pressures, and increased with decreasing wall thermal conductivities. When wall thermal conductivity was smaller, buring rate was increased with increasing wall thicknesses. In contrary, buring rate was decreased with increasing wall thickness. However, when the wall thickness reach a certain value, effects of wall thicknesses on combustion tended to stability.
Change laws of work performance of different propellants varied with different chamber diameters were tested and analyzed by Simple Pendulum Principle. Results show thrust and impulse were increased with increasing chamber diameters in the same propellant. Lead styphnate species had large thrust and impulse, and nickel hydrazine nitrate species had small thrust and impulse in the same chamber diameters.
A model describing thrust of micro-thruster was established, and effects of micro-nozzle structures on performance of micro-thruster were obtained by calculation. Results show micro-nozzle had a optimal exit expansion ratio under 0.1 MPa pressure. Thrust was increased with increasing exit expansion ratio of micro-nozzle in vacuo.
A one-dimensional finite difference model describing the process of combustion and thermal conduction, as well as finite element model of micro-thruster array were established respectively. With the help of these methods, structures and mechanical Properties of micro-thruster cell were analyzed by numerical calculation and simulation. Results show larger heat conductivity, longer combustion time led to less micro-thruster cells on a same area.
The maximum value of equivalent thermal stress and thermal deformation were located on edge of chamber hole, which were the brittle parts on micro-thruster chamber. Due to the thermal stress and thermal deformation, the structure of array are more easily damaged with the increasing combustion gas temperature, action time and chamber diameters, and decreasing cell spacing.
利用高速摄影技术研究了B/KNO3在微细石英管中燃烧时,燃速随圆管管径、燃烧室压强、圆管壁厚及管壁热传导系数的变化；建立了微细圆管内固体含能材料的燃烧传热模型,分析了圆管管径、壁厚及管壁热传导系数对热损失和燃烧稳定性的影响机理和规律。研究表明：圆管管径越小、燃烧室压强越小、管壁热传导系数越大,燃烧越不稳定；管壁热传导系数较小时,燃速随壁厚增加而增大；管壁热传导系数较大时,燃速随壁厚增加而减小；当壁厚增加到一定值时,壁厚对燃烧影响趋于稳定。
基于单摆原理测试分析了不同推进剂的作功性能随微推进器单元药室直径的变化规律。研究表明：相同药剂时,推力、冲量均随药室直径增加而增大；相同药室直径时,斯蒂酚酸铅类的推力较大、冲量较小,硝酸肼镍类的推力较小、冲量较大。
建立了微推力计算模型,分析了微喷管结构对推进性能的影响。0.1MPa环境压强下,微喷管存在一个最佳的出口扩张比；真空环境中,推力随出口扩张比增加而不断增大。
建立了化学微推进器阵列单元燃烧传热的数学物理模型和热应力有限元模型,计算分析了微推进阵列药室的结构和力学性能。结果表明：药室材料热传导系数越小、药剂燃烧时间越短,阵列集成度越高；药室孔边处热应力及变形量最大,是结构中最薄弱的环节；药室直径越大、药室单元间距越小、燃气温度越高、作用时间越长,阵列结构中热应力及变形量就越大,越易造成结构的破坏。
In order to development high performance solid chemical micro-thruster, characteristics and mechanisms of solid energetic materials combustion in microscale as well as work characteristics and structure design of micro-thruster were investigated by this dissertation.
Change of Burning rate of B/KNO3 varied with tube diameters, combustor pressures, wall thicknesses and wall thermal conductivities in microscale quartz tubes were obtained by the high-speed photography. Based on the mechanisms of combustion and thermal conduction, a model describing the process of combustion and thermal conduction of solid energetic materials burnt in a microtube was established. With the help of this model, effects and mechanisms of micro-tube dimensions, wall thicknesses and wall thermal conductivities on thermal loss and combustion stability were obtained by numerical simulation. Results show the stability was decreased with decreasing tube diameters, combustor pressures, and increased with decreasing wall thermal conductivities. When wall thermal conductivity was smaller, buring rate was increased with increasing wall thicknesses. In contrary, buring rate was decreased with increasing wall thickness. However, when the wall thickness reach a certain value, effects of wall thicknesses on combustion tended to stability.
Change laws of work performance of different propellants varied with different chamber diameters were tested and analyzed by Simple Pendulum Principle. Results show thrust and impulse were increased with increasing chamber diameters in the same propellant. Lead styphnate species had large thrust and impulse, and nickel hydrazine nitrate species had small thrust and impulse in the same chamber diameters.
A model describing thrust of micro-thruster was established, and effects of micro-nozzle structures on performance of micro-thruster were obtained by calculation. Results show micro-nozzle had a optimal exit expansion ratio under 0.1 MPa pressure. Thrust was increased with increasing exit expansion ratio of micro-nozzle in vacuo.
A one-dimensional finite difference model describing the process of combustion and thermal conduction, as well as finite element model of micro-thruster array were established respectively. With the help of these methods, structures and mechanical Properties of micro-thruster cell were analyzed by numerical calculation and simulation. Results show larger heat conductivity, longer combustion time led to less micro-thruster cells on a same area.
The maximum value of equivalent thermal stress and thermal deformation were located on edge of chamber hole, which were the brittle parts on micro-thruster chamber. Due to the thermal stress and thermal deformation, the structure of array are more easily damaged with the increasing combustion gas temperature, action time and chamber diameters, and decreasing cell spacing.
引文
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[6]Yang W M, Chou S K, Shu C 1, et al. Microscale combustion research for application to microthermo-photovoltaic systems [J]. Energy Conversion and Management,2003,44(16): 2625～2634
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[9]Kelvin Fu. Design and fabrication of a silicon based MEMS rotary engine[C]. Proceedings of 2001 ASME International Mechanical Engineering Congress and Exposition, New York, NY,2001:11～16
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