不同旋流情况对旋转流线涡燃烧室性能的影响

为探究不同旋流器位置和数目对航空发动机燃烧室性能的影响规律,运用FLUENT软件,采用计算流体力学法对某旋转流线涡燃烧室冷态流场和燃烧性能进行了研究。结果表明:相比于其他位置,旋流器距离燃烧室头部为88 mm时流线涡更稳定、更不易脱落,且燃烧效率最高,火焰长度也最短,燃烧效果最理想;旋流器数量的改变对压力损失和火焰长度的影响并不明显,但3个旋流器产生的涡范围更大,且会使空气与燃料掺混得更好,壁面温度场更加理想,燃烧性能更好。     

用于航空发动机故障诊断的双发性能参数差值分析法

为克服双发民用飞机目前普遍采用的3大发动机生产厂家(Original Equipment Manufacturer,OEM)开发的发动机性能监控软件的局限性,研究总结了双发性能参数差值分析法。通过3起发动机故障诊断实际案例,利用该方法对双发性能参数进行差值计算,并观察其变化趋势,可以有效地排除外界飞行条件等的影响,高效地判断出发动机故障;同时,可以对飞机航空专用数据链通信系统(Aircraft Addressing and Reporting System,ACARS)报文上任何所需的参数进行分析。     

采用脉冲爆震外涵加力燃烧室的涡扇发动机性能研究

为了研究带外涵加力脉冲爆震燃烧室(Pulse detonation combustor,PDC)的分开排气涡扇发动机性能,建立了其性能模型。利用该模型对带PDC外涵加力原理性试验模型的性能进行了评估,同时选取涡扇发动机对该发动机采用PDC外涵加力后的部件特性及整机性能进行研究,并比较了等燃油流量下外涵道装有PDC和传统等压燃烧室的发动机性能。理论计算结果和实验值对比表明,加装合适的喷管结构能够大大提高该原理性试验模型的推力性能。算例的计算结果显示:随着PDC工作频率的提高,发动机总推力增加,耗油率增大;在同一工作频率下,PDC平均增压比、平均出口温度和发动机总推力在当量比1.1左右达到最大值,发动机总耗油率随着当量比的增大而增加;当PDC工作频率超过50Hz时,外涵道装有PDC的发动机总推力大于外涵道装有传统等压燃烧室的发动机推力,且耗油率要小。     

基于支持向量机的航空发动机性能衰退指标预测

针对航空发动机性能衰退状态的趋势预测问题,基于非线性支持向量机回归建立了发动机性能衰退指标的预测模型,给出了反映其性能衰退的综合指标。利用该模型对发动机的性能衰退指标进行了预测分析,并与神经网络模型预测结果进行了比较。结果表明:支持向量机回归预测模型能更准确地对发动机的未来状况进行预测。     

双级波瓣引射混合器的引射性能

采用实验和数值方法对双级波瓣引射混合器的引射性能进行研究,重点研究混合管在两种不同进口方式下的引射混合器气动特征差异,并初步分析混合管面积比和长径比对双级波瓣引射混合器引射性能的影响.结果表明:混合管进口方式对引射能力有非常重要的影响,在研究的结构参数条件下,对于受限式进口,单级波瓣引射混合器的引射能力要强于双级波瓣引射混合器约10%;而对于敞开式进口,其引射能力要优于受限式进口最大约35%,此时双级波瓣引射混合器的引射能力要略好于单级波瓣引射混合器.在较大的混合管面积比或较小的长径比下,敞开式进口下双级波瓣引射混合器较受限式进口表现尤为优越.      

Attitude control system design and on-orbit performance analysis of nano-satellite––‘‘Tian Tuo 1’’

‘‘Tian Tuo 1'(TT-1) nano-satellite is the first single-board nano-satellite that was successfully launched in China. The main objective of TT-1 is technology demonstration and scientific measurements. The satellite carries out the significant exploration of single-board architecture feasibility validation, and it is tailored to the low-cost philosophy by adopting numerous commercialoff-the-shelf(COTS) components. The satellite is featured with three-axis stabilization control capability. A pitch bias momentum wheel and three magnetic coils are adopted as control actuators.The sun sensors, magnetometers and a three-axis gyro are employed as the measurement sensors.The quaternion estimator(QUEST) and unscented Kalman filter(UKF) method are adopted for the nano-satellite attitude determination. On-orbit data received by ground station is conducted to analysis the performance of attitude determination and control system(ADCS). The results show that the design of ADCS for TT-1 is suitable, robust and feasible.     

Dynamic analysis of C/C composite finger seal

A seal device as an important component of aeroengines has decisive influence on per- formance, reliability, and working life of aeroengines. With the development of aeroengines, demands on the performance characteristics of seal devices are made strictly. Finger seal as a novel kind of sealing device, recently attracts more and more attentions in academic circles and engineer- ing fields at home and abroad. Research on finger seals has been extensively developed, especially on leakage and wear performances under dynamic conditions. However, it is a pity that the work on finger seals has been limited with a single approach that is improving the performance by structural optimization; in addition, the technology of dynamic analysis on finger seals is weak. Aiming at the problems mentioned above, a distributed mass equivalent dynamic model of finger seals considering the coupling effect of overlaid laminates is established in the present paper, the dynamic perfor- mance of 2.5 dimension C/C composite finger seal is analyzed with the model, and then the effects of fiber bundle density and fiber bundle preparation direction on finger seal＇s dynamic performance are discussed, as well as compared with those of Co-based alloy finger seal. The current work is about dynamic analysis of finger seals and application of C/C composite in this paper may have much academic significance and many engineering values for improving research level of finger seal dynamics and exploring feasibility of C/C composite being used for finger seals.     

基于技术参数评估的涡扇发动机总体性能设计分析

为了充分掌握各代涡扇发动机技术参数水平及其发展趋势,统计包括现役型号在内的15台2～4代涡扇发动机的总体性能参数、循环参数和部件参数,采用考虑涡轮冷却的总体性能计算和重量预测相结合的发动机技术参数综合评估模型并利用计算程序绘制趋势曲线,评估技术参数的发展趋势,结果表明技术参数逐年改善的趋势是比较稳定的,并用曲线趋势外推法取得下一代关键参数的定量数据。在此基础上探索下一代高推重比涡扇发动机可能的总体性能方案,为下一代先进涡扇发动机的预研和设计提供参考。     

多尾鳍仿生航行器推进性能的三维数值研究

采用格子波尔兹曼方法及浸没边界法,发展了一套适用于自由游动的三维数值研究程序。进而以多尾鳍推进仿生航行器为原型,讨论了尾鳍数目、形状、材料刚度等构型参数及振幅、频率等尾鳍摆动参数对推进性能的影响。结果表明对称布置、反对称摆动的双尾鳍能够明显消除侧向力而避免航行器主体的横向晃动,且推力大于两个单独尾鳍的简单加和;在中等Reynolds数下,具有波动性质的柔性尾鳍不论是推进速度还是推进效率均优于刚性尾鳍;当尾鳍单纯摆动推进时,具有完整鳍面的半椭圆形尾鳍的推进性能优于后部有缺口的深叉形尾鳍。     

军用直升机雷达隐身性能仿真与评估

采用高频方法计算了某型通用直升机及其隐身改型的RCS数据,基于现有雷达隐身性能计算方法和直升机低空飞行特点,对直升机在单部雷达和雷达组网两种情况下的雷达隐身性能进行仿真分析,给出了单部雷达和雷达组网发现目标的判定准则,分析了直升机可探测范围曲线、平均综合检测概率和暴露时间等隐身指标。通过仿真分析,评估了不同飞行高度下RCS减缩与直升机隐身性能的定量关系,为直升机的隐身设计提供了参考依据。