Interior Evolution of Mercury

The interior evolution of Mercury—the innermost planet in the solar system, with its exceptional high density—is poorly known. Our current knowledge of Mercury is based on observations from Mariner 10’s three flybys. That knowledge includes the important discoveries of a weak, active magnetic field and a system of lobate scarps that suggests limited radial contraction of the planet during the last 4 billion years. We review existing models of Mercury’s interior evolution and further present new 2D and 3D convection models that consider both a strongly temperature-dependent viscosity and core cooling. These studies provide a framework for understanding the basic characteristics of the planet’s internal evolution as well as the role of the amount and distribution of radiogenic heat production, mantle viscosity, and sulfur content of the core have had on the history of Mercury’s interior. The existence of a dynamo-generated magnetic field suggests a growing inner core, as model calculations show that a thermally driven dynamo for Mercury is unlikely. Thermal evolution models suggest a range of possible upper limits for the sulfur content in the core. For large sulfur contents the model cores would be entirely fluid. The observation of limited planetary contraction (∼1–2 km)—if confirmed by future missions—may provide a lower limit for the core sulfur content. For smaller sulfur contents, the planetary contraction obtained after the end of the heavy bombardment due to inner core growth is larger than the observed value. Due to the present poor knowledge of various parameters, for example, the mantle rheology, the thermal conductivity of mantle and crust, and the amount and distribution of radiogenic heat production, it is not possible to constrain the core sulfur content nor the present state of the mantle. Therefore, it is difficult to robustly predict whether or not the mantle is conductive or in the convective regime. For instance, in the case of very inefficient planetary cooling—for example, as a consequence of a strong thermal insulation by a low conductivity crust and a stiff Newtonian mantle rheology—the predicted sulfur content can be as low as 1 wt% to match current estimates of planetary contraction, making deep mantle convection likely. Efficient cooling—for example, caused by the growth of a crust strongly in enriched in radiogenic elements—requires more than 6.5 wt% S. These latter models also predict a transition from a convective to a conductive mantle during the planet’s history. Data from future missions to Mercury will aid considerably our understanding of the evolution of its interior.     

重复使用飞行器金属热防护系统的有限元分析与设计

金属基热防护系统具有轻质、耐用、可操作性、成本高效等特点,是实现降低重复使用飞行器费用的一个关键技术。通过比较分析超耐热合金防热板和改进型防热板,给出了金属热防护系统的各个部分的设计准则。建立了蜂窝夹芯板和纤维隔热毡的有效热导率的数值预报模型,算例研究表明本文给出的数值预报方法正确。使用二维热分析模型和三维承载分析模型,实现了传热和承载分析的迭代计算,算例表明迭代方法有效、可行,可用于可重复使用飞行器金属热防护系统的分析与评价。     

Oxidation resistance and self-sealing property of ceramic coatings for C/C composites

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耐高温芳杂环聚吡咙的合成与性能

利用主链含有吡啶环的新型四胺单体,2,6-双(3,’4’-二氨基苯基)-4-氟苯基吡啶(FP-PA)与几种芳香族四酸二酐单体,2,2-双[4-(3,’4’-二羧基苯氧基)苯基]丙烷二酐(BPADA)、3,3,’4,4’-二苯醚四羧酸二酐(ODPA)、3,3,’4,4’-二苯甲酮四羧酸二酐(BTDA)或4,4’-(六氟异丙基)双邻苯二甲酸二酐(6FDA)通过热缩聚、热环化反应成功制备了一系列具有半梯形主链结构的芳杂环聚合物-聚吡咙(PPy)。结果表明:所制备的聚吡咙具有优异的耐热稳定性;其玻璃化转变温度达到367℃,在氮气氛围中的起始热分解温度超过500℃,10%失重温度超过560℃,750℃时的殘重率超过60%。另外,聚吡咙薄膜表现出优良的耐碱水解性能,在10%NaOH水溶液中浸泡7d后仍具有优良的柔韧性和耐热性。     

整流罩用隔热材料的研制

以改性有机硅树脂基体和无纺纤维毡为原料,经喷涂定型工艺制备了低密度阻燃隔热材料.材料密度和热导率分别为0.27～0.36g/cm3和0.032～0.036 W/(m·K).测试分析了基体拉伸强度以及材料密度和厚度对隔热效果的影响.结果表明,隔热性能可满足直升机发动机整流罩的热防护要求.     

飞机腐蚀与防护

飞机腐蚀是每个航空公司都必须面对的问题。随着飞机服役时间的增加,有效地检查出飞机结构上存在的各种腐蚀,并进行去除,更是成为延长飞机使用寿命的关键。本文详细分析了飞机腐蚀的种类,根据腐蚀的特点及表现形式,介绍了相应的检查方法及去除方法。最后有针对性地提出了各种防护措施。     

镁合金等离子体氧化时火花变化规律的研究

研究Magoxid工艺中镁合金等离子体氧化的过程,此过程分为三个阶段:普通阳极氧化、微弧氧化以及弧光氧化.随着氧化的进行,施加的电压不断升高,火花由微弧向弧光过渡.而微弧和弧光开始均主要集中于样品的边缘,然后均匀分布于整个样品表面.与微弧氧化阶段相比,弧光氧化阶段火花的数量明显减少,尺寸增大,并且持续的时间延长.与火花变化过程相对应,氧化膜表面孔数量减少,直径逐渐增大.氧化时间超过10min后,氧化膜表面呈现不明显的多孔结构.     

单组元肼推力器温度场仿真及试验

针对5N单组元肼推力器，建立了在轨运行过程中推力室热控组件的传热模型；应用有限元方法进行了热分析和仿真计算；并对计算结果进行地面热真空试验验证。对于进一步开发、研制具有新型结构和热控性能的姿控推力器和具有相似结构的多种推力器具有一定的借鉴和指导意义。     

碳化温度对C/C复合材料微观结构及热性能的影响

采用CVI PIC工艺制备了四种碳毡增强碳基复合材料(C/C), 其中对三种样品A、B、C在2 500℃进行了一次石墨化处理,样品D未进行石墨化处理。为与900℃碳化对比,研究了1 500℃碳化对复合材料微观结构及热性能的影响。结果表明:碳化温度由900℃提高到1 500℃后,样品A的开孔率下降11. 6% ~13. 5%, 1 000℃的xy向线膨胀系数由1. 75×10-6 /K增大到2. 17×10-6 /K; xy向和z向的800℃热导率分别由65. 07W/(m·K)、45. 98W/(m·K)增大到75. 44W/(m·K)、54. 86W/(m·K);xy向和z向的比热容分别由1. 70kJ/(kg·K)、1. 43kJ/(kg·K)增大到1. 79kJ/(kg·K)、2. 19kJ/(kg·K)。样品B和样品C也表现出基本相同的趋势;随着碳化温度由900℃提高到1 500℃,样品D中微晶尺寸由2nm增大到4nm。     

树脂基复合材料长时间烧蚀防热的应用研究

介绍了不同再入飞行器热防护材料的特点，指出长时间飞行器对防热层的要求。通过纤维织物改性和树脂基体改性研制了新型防隔热材料，并进行了性能测试和研究。结果表明：新型改性纤维／酚醛复合材料比传统的树脂基防热材料具有更好的隔热性能和抗烧蚀剥蚀性能，能够满足中低焓值、较低热流、烧蚀时间较长（300～700s）防热部件的防隔热要求。