RTM用炔基改性苯并噁嗪树脂工艺及力学性能

文摘为改善苯并噁嗪树脂对树脂传递模塑(RTM)成型工艺的适应性,并进一步提升苯丙噁嗪基复合材料的耐高温性能。提出利用炔基改性苯并噁嗪树脂,以提高树脂的交联密度,并改善树脂流变特性。结果表明:改性后的炔基苯并噁嗪树脂在81. 5℃时黏度低至805 mPa·s可满足RTM工艺灌注要求,在110℃其工艺窗口高达310 min。同时,炔基苯并噁嗪树脂的起始固化温度低至130℃,固化温度为167℃,后处理温度为208℃,满足低温固化要求。通过DMA与TGA分析,RTM成型低温固化苯并噁嗪/碳纤维复合材料的Tg为411℃,在N_2环境下800℃残留率高达88. 6%,表明其复合材料具有良好的耐高温性能。SEM观察发现该树脂与纤维界面粘结强度较高,碳纤维复合材料350℃拉伸性能保留率达99%以上,弯曲、层剪性能保留率达70%以上,压缩性能保留率也达60. 9%。     

基体厚向梯度化聚酰亚胺复合材料制备与表征

研制树脂传递模塑成型（RTM）用聚酰亚胺树脂基体RTM-PI,采用RTM工艺制备基体厚向梯度化聚酰亚胺复合材料,提升复合材料热稳定性能。基体梯度化复合材料包括RTM-PI树脂基芯层和高热稳定树脂基表层,RTM成型工艺参数基于树脂升温热失重、流变和固化反应数据确定。结果表明：RTM-PI树脂兼具低黏度、超长工艺适用期和耐高温性能,最低黏度在0.1 Pa·s以下,工艺期在300 min以上,玻璃化转变温度达到445℃;基体厚度梯度化复合材料内部质量优异,350℃热老化100 h的失重相对纯RTM-PI复合材料可降低48%以上。     

适用于室温RTM工艺的氰酸酯树脂基体的研究

用苯乙烯、二乙烯基苯对双酚 A型氰酸酯 (BADCy)进行改性 ,研制了适用于室温下树脂传递模塑 (RTM)工艺操作的高性能树脂基体。该树脂具有较高的耐热性 (热变形温度 1 90～ 2 0 0℃ )和耐湿热稳定性 ;力学性能与同属 RTM工艺的 45 0 3 A树脂相当 ,某些指标优于 45 0 3 A。较好地达到了改性目的     

RTM 用R801 树脂工艺及性能

对一种新型RTM用双马来酰亚胺树脂R801的固化反应特性、成型工艺及其制备的复合材料性能进行了研究,DSC曲线表明该树脂体系的固化温度为170～220℃;黏度随温度变化曲线表明在70～120℃,树脂黏度增长缓慢,具有不少于7 h的适用期;在90℃左右时,其初始黏度<100 mPa.s,工艺操作窗口时间≥10 h;该树脂制备的MT300碳纤维复合材料在300℃时的压缩、弯曲、层剪性能保持率均≥63%。     

RTM 用耐高温R802 树脂工艺及性能

研究了RTM用耐高温R802邻苯二甲腈树脂黏度随温度、时间的变化,不同升温速率下的DSC特性,常、高温复合材料弯曲、层间剪切强度、树脂与纤维的界面等。黏度随时间变化曲线表明,其140℃下RTM工艺窗口不少于180 min;DSC曲线表明,在180℃时开始凝胶,固化温度203℃,后处理温度256℃;力学性能测试结果表明,R802/MT300复合材料200℃下弯曲强度保持率为103.8%,500℃下弯曲强度保持率为41.1%,300℃下层间剪切强度较常温提高18%,500℃下层间剪切强度保持率为44%,其树脂与纤维结合良好。     

RTM成型用聚酰亚胺树脂及其复合材料研究进展

聚酰亚胺复合材料因其优异的耐高温性能和机械性能,在航空航天领域获得了广泛应用,但复杂、高成本的热压罐成型工艺难以满足聚酰亚胺树脂基复合材料快速加工成型,限制了其进一步的应用。本文综述了适用于树脂传递模塑成型（RTM）技术的聚酰亚胺树脂及其复合材料的研究现状与发展趋势,重点论述了苯乙炔基封端的聚酰亚胺树脂及其复合材料的国内外研究情况,提高RTM技术成型聚酰亚胺树脂及其复合材料耐温等级的同时保持低充模黏度和高韧性将会是重要的发展方向。     

碳纤维增强耐热环氧树脂复合材料工艺性能研究

研究了一种低黏度耐高温环氧树脂体系的黏温特性及固化反应动力学,考察了该树脂体系的浇注体及其碳纤维复合材料的力学性能,通过热机械分析(DMTA)研究了树脂浇注体及其复合材料的动态热机械性能.结果表明,该树脂体系在室温下黏度为0.3 Pa·s,50℃下适用期在10 h以上,130℃下可以快速固化反应,适合于RTM等快速成型工艺,Tg达到220℃以上,其碳纤维复合材料具有优良的耐高温性能.     

含硅芳炔树脂的化学流变特性

含硅芳炔树脂的流变特性对于其RTM成型工艺有重要参考价值,采用DSC热分析及黏度测量表征了含硅芳炔树脂的固化特性和黏度与温度的关系,发现含硅芳炔树脂为典型的牛顿流体,且在100～130℃范围内具有较低黏度,维持时间长.根据其黏度-温度-时间关系建立了双阿伦尼乌斯黏度模型,模型分析与实验结果取得较好的一致性,可为RTM成型工艺窗口的预测提供支撑.     

RTM工艺用耐高温树脂研制

以某飞行器透波结构件对材料的要求为背景，研制了可用于RTM成形工艺的耐高温树脂SH。SH树脂100℃下8h后粘度仅200mPa.s，适于RTM工艺成形；该树脂耐热性良好，玻璃化转变温度Tg为269℃，430℃热失重仅为10％；石英纤维／SH树脂腹合材料300℃时的弯曲强度σb＝139MPa，弯曲模量Eb＝9．5GPa，可在300℃以上短时使用。     

新型聚苯并噁嗪改性树脂的制备与性能

通过预聚反应制备了一种新型聚苯并噁嗪改性树脂.利用FTIR、GPC表征了改性树脂.利用旋转黏度计、DSC、DMA和TGA分别考察了树脂的流动性能、固化行为和改性树脂固化物的热性能.结果表明:制备的苯并噁嗪改性树脂在60～ 100℃,黏度小于500 mPa·s,恒温6h黏度不明显增大,具有良好的流动性能,适用于RTM成型工艺.改性树脂聚合温度较低,具有良好的固化工艺性.改性树脂固化物在氮气气氛下Td5在430℃以上,在900℃的残重高达73.71％,Ts为353.4℃,具有良好热性能.     

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.      

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）。     

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。     

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。