中性水基氧化铝陶瓷料浆的流变学研究

采用流变学的方法在RV 2 0型流变仪上研究了不同条件对中性氧化铝悬浮体流变性的影响。重点研究了固含量、分散剂加入量、球磨工艺对料浆流变性的影响。研究表明 :随临界固含量的降低 ,“剪切增厚”的临界剪切速率呈明显的升高趋势 ,从固含量为 5 6vol%时的 82s-1增加到固含量为 5 0vol%时的 192s-1;分散剂的加入量对料浆的临界剪切速率具有显著的影响 ,当固含量为 5 6vol%时 ,分散剂合适的量为 1 0wt% ;随着球磨时间的延长 ,料浆的“剪切增厚”临界剪切速率增大 ,而且逐渐不再有“剪切变稀”阶段。     

固相含量对Al2O3料浆及瓷体性能的影响

研究了固相浓度对用于凝胶注成型的Al2O3料浆的粘度和流动性能的影响,并分析了由不同浓度的料浆制得的瓷体结构和性能与料浆浓度的关系.结果表明,控制合适的体浓度对于获得适合浇注的高性能料浆是必要的.同时由于料浆浓度会影响球磨效率和坯体密度,因此会对最终瓷体的质量有较大影响.在本文的实验条件下,料浆中固相的最佳含量为50vol%.     

pH值对凝胶注模氧化铝陶瓷料浆性能的影响

重点研究了在低粘度,高固相体积分数氧化铝浓悬浮体制备过程中,料浆的pH值对料浆性能的影响。结果表明:当pH值达到5左右时,Al_2O_3颗粒在水中的Zeta电位等于0,此时,料浆的粘度最大,分散效果最差。当pH值达到9时,Zeta电位的绝对值达到最大,此时料浆的悬浮稳定性最佳。     

凝胶注模氧化铝陶瓷坯体的结构与表征

研究了凝胶注模氧化铝陶瓷坯体的密度、强度、空隙率分布及微观结构等特征。结果表明,影响凝胶注模陶瓷坯片密度的因素主要有:料浆的固含量、单体含量、单体和胶联剂的比值。随着料浆固含量的提高,坯片的抗弯强度呈下降趋势,坯片内部的孔隙率降低,从平均孔隙度为110nm降为90nm,而且均为单峰分布。凝胶注模成型的陶瓷坯片在干燥后,坯片强度优于注射成型、流延成型等传统成型方式。     

复合固体推进剂药浆粘度的预估

本文通过对影响固体推进剂药浆粘度的因素进行分析和相关试验,导得了药浆粘度预估的数学关系式。试验结果表明,对含过氯酸铵推进剂药浆粘度的预估值93％的数据在实验值的±15％内;对含铝粉推进剂药浆粘度的预估值92％的数据在实测值的±20％范围内。     

POE-g-MAH 对PA66 共混体系性能的影响

讨论了POE-g-MAH含量、MAH接枝率对PA66/POE/POE-g-MAH共混物性能的影响.当POE-g-MAH含量为10wt％～15wt％时,PA66/POE-g-MAH共混物发生脆-韧转变;随POE-g-MAH含量增加,共混物的缺口冲击强度、断裂伸长率显著增大,拉伸强度、弯曲强度、弯曲模量、熔体流动速率、吸水率均明显下降.当POE-g-MAH接枝率为0.05wt％～0.2wt％时,PA66/POE/POE-g-MAH共混物发生脆-韧转变;随POE-g-MAH接枝率增加,共混物的缺口冲击强度、断裂伸长率增大,拉伸强度、弯曲强度、弯曲模量、吸水率变化不大,熔体流动速率下降.SEM照片和Molau实验表明,POE-g-MAH对PA66具有显著的增容增韧效果.     

有序多孔氧化铝陶瓷微观结构研究

利用扫描电镜(SEM)对模板法制备的有序多孔氧化铝陶瓷的微观结构特征、孔隙结构和晶粒生长进行了研究.结果表明:通过模板法制备的多孔氧化铝陶瓷孔结构均匀、排列有序,孔洞内部相互连通;随着料氧化铝浆固相体积的增加,多孔陶瓷的孔隙率相应降低;孔洞边缘没有出现晶粒的异常生长,与发泡法制备的多孔陶瓷相比,烧结致密度更高.     

关于复合固体推进剂批次间性能差异的研究(报告之二:药浆的粘度分析)

复合固体推进剂药浆是固体粒子含量很高的粘性流体。影响其粘度的除了粘结剂的度粘外,主要还有固体粒子的容积百分比和尺寸匹配。文中介绍了计算药浆粘度公式,还就粒子形状、尺寸、表面性质对有粒子悬浮的浆液粘性影响作简要回顾。文中还指出,由于药浆的固体粒子含量高,用不同测试方法测得的药浆粘度可能会差距甚大以及粒子容积含量的少量不均匀性可能会导致粘度值差很多。     

纳米MoS2对芳纶纤维织物/酚醛树脂复合材料摩擦学性能的影响

采用溶液浸渍和模压成型的方法制备了纳米MoS2含量不同(0.5 wt％、1.5 wt％ 和2.5 wt％)的芳纶纤维织物/酚醛树脂复合材料,并采用摩擦磨损试验机对制备复合材料的摩擦学性能进行测试,采用扫描电子显微镜对制备复合材料表面的磨痕进行表征分析.结果表明,加入纳米MoS2可以改善芳纶纤维织物/酚醛树脂复合材料的摩...     

Al-Mg-Sc 和Al-Mg-Er 合金的组织与性能

采用铸造—轧制—稳定化退火技术制备了Sc含量为0.10wt％和Er含量为0.25wt％的两种Al-Mg合金薄板,研究了不同处理工艺下两种合金板材拉伸性能、剥落腐蚀性能和显微组织的变化规律.结果表明,两种合金冷轧板材稳定化退火过程中拉伸性能有相同的变化规律,即随着退火温度升高,板材强度下降而塑性升高,Sc含量为0.10wt％的合金350℃/1 h退火仍然表现出很强的抗退火软化能力,而Er含量为0.25％的合金当退火温度高于280℃后迅速软化;300℃/1 h退火条件下,含Sc合金和含Er合金的抗拉强度、屈服强度和伸长率分别为424 MPa、314 MPa、18.3％和350 MPa、177 MPa、29.1％;与此同时,随退火温度的升高,板材抗剥落腐蚀的能力也表现出相同规律性的变化,即200℃/1 h左右退火时剥落腐蚀最严重,随着退火温度升高,腐蚀抗力增加,两种合金板材经280℃以上1h稳定化退火后,合金板材可以获得较好的抗剥落腐蚀性能;其次,与Sc含量为0.25wt％的5B70合金相比,研制的Sc含量为0.10wt％合金综合性能接近5B70合金,而这种合金的Sc含量只有5B70合金的40％,能显著降低合金的制造成本,预示着低Sc含量的合金在航天领域有良好的开发应用前景.     

有翼高超声速再入飞行器气动设计难点问题

有翼高超声速再入飞行器是近年来的研究热点,气动设计是飞行器设计的关键。为了更清楚地认识有翼高超声速再入飞行器气动设计的难点问题,对有翼高超声速再入飞行器的发展、优势及总体任务剖面进行了介绍,从5个方面详细介绍了该类飞行器气动设计的难点问题,包括多约束复杂面对称气动布局设计、高温真实气体效应对气动特性影响、天地差异与天地换算方法、反作用控制系统(RCS)喷流干扰对气动特性的影响以及气动数据不确定度等,简要阐明了这些难点问题对总体设计的重要性以及初步的解决思路,为有翼高超声速再入飞行器气动设计提供了一些参考。     

Simulation and Analysis of Crashworthiness of Fuel Tank for Helicopters

Crashworthiness requirement of fuel tanks is one of the important requirements in helicopter designs. The relations among the protection frame, textile layer and rubber layer of the fuel tank are introduced. Two appropriate FE models are established, one is for an uncovered helicopter fuel tank without protection frame, and the other is for fuel tank with protection frame. The dynamic responses of the two types of fuel tanks impinging on the ground with velocities of 17.3 m/s are numerically simulated for the purpose of analyzing energy-absorbing capabilities of the textile layer and protection frame. The feasibility of the current crashworthiness design of the fuel tank is examined though comparing the dynamic response behaviors of the two fuel tanks.     

The effect of inlet conditions on the flow and heat transfer in multiple rotating cavity with axial throughflow

This paper discusses experimental results from two different build configurations of a heated multiple rotating cavity test rig.Measurements of heat transfer from the discs and tangential velocities are presented.The test rig is a 70% full scale version of a high pressure compressor stack of an axial gas turbine engine.Of particular interest are the internal cylindrical cavities formed by adjacent discs and the interaction of these with a central axial throughflow of cooling air.Tests were carried out for a range of non-dimensional parameters representative of high pressure compressor internal air system flows(Re up to 5×106 and Rez up to 2×105).Two different builds have been tested.The most significant difference between these two build configurations is the size of the annular gap between the(non-rotating) drive shaft and the bores of the discs.The heat transfer data were obtained from thermocouple measurements of surface temperature and a conduction solution method.The velocity measurements were made using a two component,LDA system.The heat transfer results from the discs show differences between the two builds.This is attributed to the wider annular gap allowing more of the throughflow to penetrate into the cavity.There are also significant differences between the radial distributions of tangential velocity in the two builds of the test rig.For the narrow annular gap,there is an increase of non-dimensional tangential velocity V/Ωr with radial location to solid body rotation V/Ωr=1.For the wider annular gap,the non-dimensional velocities show a decrease with radial location to solid body rotation.      

ν-gap度量及其在飞行控制律评估中的应用

 传统控制律评估方法主要用于单输入单输出（SISO）系统，且对模型参数摄动考虑不够全面,针对这些不足，研究了ν-gap度量方法。在介绍系统广义稳定裕度相关概念的基础上，给出了ν-gap度量的定义、特点和性质以及近似摄动模型的计算，提出ν-gap度量评估控制律的步骤。实例结果表明，该方法不仅克服了上述传统评估方法的缺陷，而且还有根据所求的各摄动影响情况忽略影响小的元素，以减少计算量及可以找到最坏情况下的参数摄动组合等优点。     

突破技术趋同，波音再现竞争优势

 波音公司面临着来自空客公司的巨大挑战,企业战略性创新才是公司成功的关键。为此波音公司的全部战略性研究集中在扩大产品的差异性上,体现在3个方面：电子化（e-Enabled）运营环境、整体复合材料机身部件的制造技术和支持波音787客机的全球协同环境（GCE）。     

临近空间飞行器测控与信息传输系统频段选择

 临近空间飞行器是高性能信息化武器平台,测控（TT&;C）与信息传输系统是其信息保障的核心,而选择合理、可行的频段是展开系统设计的前提和基础。频段选择影响到整个技术方案的制定,是一个需综合考虑、影响深远并具有战略意义的关键问题,从国际电联（ITU）国际标准、高速数传、接收信噪比（SNR）、“三抗”、超视距中继、黑障、雨衰以及设备研制成熟度8个方面全面、细致论证了近空间平台测控系统的频段选择问题,最终得出在视距链路中以Ka频段为宜,在超视距链路中以Ku/Ka双频段为宜的结论。     

基于弯曲激波压缩系统的高超声速进气道反设计研究进展

总结了近十年来弯曲激波压缩研究的主要成果。提出了弯曲激波压缩系统的新概念,即利用特殊设计的楔形弯曲压缩面或空间弯曲压缩面,产生一系列与前缘弱激波相互交汇或叠加的压缩波系,从而使前缘激波弯曲,形成特殊的弯曲激波,它与波后的等熵压缩波来共同完成对气流的压缩。在此基础上,实现了由给定出口气动参数的超声速内流道反设计,实现了由给定压缩面压力分布和给定压缩面马赫数分布要求的型面反设计,实现了由给定激波波面的压缩型面反设计。研究证明,弯曲压缩面-弯曲激波压缩系统具有良好的综合气动性能,为高性能高超声速进气系统的气动设计提供了一种全新的设计方法。     

Integrated Entry Guidance for Reusable Launch Vehicle

A method for the implementation of integrated three-degree-of-freedom constrained entry guidance for reusable launch vehicle is presented. Given any feasible entry conditions, terminal area energy management interface conditions, and the reference trajectory generated onboard then, the method can generate a longitudinal guidance profile rapidly, featuring linear quadratic regular method and a proportional-integral-derivative tracking law with time-varying gains, which satisfies all the entry corridor constraints and meets the requirements with high precision. Afterwards, by utilizing special features of crossrange parameter, establishing bank-reversal corridor, and determining bank-reversals according to dynamically adjusted method, the algorithm enables the lateral entry guidance system to fly a wide range of missions and provides reliable and good performance in the presence of significant aerodynamic modeling uncertainty. Fast trajectory guidance profiles and simulations with a reusable launch vehicle model for various missions and aerodynamic uncertain-ties are presented to demonstrate the capacity and reliability of this method.     

Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance

In order to investigate the effects of fuel injection distribution on the scramjet combustor performance, there are conducted three sets of test on a hydrocarbon fueled direct-connect scramjet test facility. The results of Test A, whose fuel injection is carried out with injectors located on the top-wall and the bottom-wall, show that the fuel injection with an appropriate close-front and centralized distribution would be of much help to optimize combustor performances. The results of Test B, whose fuel injection is performed at the optimal injection locations found in Test A, with a given equivalence ratio and different injection proportions for each injector, show that this injection mode is of little benefit to improve combustor performances. The results of Test C with a circumferential fuel injection distribution displaies the possibility of ameliorating combustor performance. By analyzing the effects of injection location parameters on combustor performances on the base of the data of Test C, it is clear that the injector location has strong coupled influences on combus- tor performances. In addition, an inner-force synthesis specific impulse is used to reduce the errors caused by the disturbance of fuel supply and working state of air heater while assessing combustor performances.     

(高)超声速流动试验技术及研究进展

近年来,与高速飞行器相关的(高)超声速流动受到了极大的关注。这类流动所具有的非定常性、强梯度和可压缩性对试验方法和风洞设计技术提出了挑战。超声速纳米示踪平面激光散射(NPLS)技术是由作者所在团队研发的非接触光学测试技术。它能够以较高的空间分辨率来揭示超声速三维流场的一个瞬态剖面的时间解析的流动结构。介绍了NPLS技术以及基于NPLS开发的密度场测量、雷诺应力测量和气动光学波前测量等方法,并回顾了这些技术在超声速边界层、超声速混合层、超声速压缩拐角、激波/边界层相互作用和光学头罩绕流等流动中的应用,清晰地再现了边界层、混合层、激波等典型流场结构及其时空演化特性。另外,为了模拟和研究高空大气条件下边界层自然转捩和超声速混合层的转捩特性,介绍了高超声速静风洞、超-超混合层风洞的设计技术以及层流化喷管的设计方法。