Occurrence features of simultaneous H+- and He+-band EMIC emissions in the outer radiation belt

As an important loss mechanism of radiation belt electrons, electromagnetic ion cyclotron (EMIC) waves show up as three distinct frequency bands below the hydrogen (H⁺), helium (He⁺), and oxygen (O⁺) ion gyrofrequencies. Compared to O⁺-band EMIC waves, H⁺- and He⁺-band emissions generally occur more frequently and result in more efficient scattering removal of <～5?MeV relativistic electrons. Therefore, knowledge about the occurrence of these two bands is important for understanding the evolution of the relativistic electron population. To evaluate the occurrence pattern and wave properties of H⁺- and He⁺-band EMIC waves when they occur concurrently, we investigate 64 events of multi-band EMIC emissions identified from high quality Van Allen Probes wave data. Our quantitative results demonstrate a strong occurrence dependence of the multi-band EMIC emissions on magnetic local time (MLT) and L-shell to mainly concentrate on the dayside region of L?=?～4–6. We also find that the average magnetic field amplitude of H⁺-band waves is larger than that of He⁺-band waves only when L?<?4.5 and AE¹?<?300?nT, and He⁺-band emissions are more intense under all other conditions. In contrast to 5 events that have average H⁺-band amplitude over 2 nT, 19 events exhibit >2 nT He⁺-band amplitude, indicating that the He⁺-band waves can be more easily amplified than the H⁺-band waves under the same circumstances. For simultaneous occurrences of the two EMIC wave bands, their frequencies vary with L-shell and geomagnetic activity: the peak wave frequency of H⁺-band emissions varies between 0.25 and 0.8 f_cp with the average between 0.25 and 0.6 f_cp, while that of He⁺-band emissions varies between 0.03 and 0.23 f_cp with the average between 0.05 and 0.15 f_cp. These newly observed occurrence features of simultaneous H⁺- and He⁺-band EMIC emissions provide improved information to quantify the overall contribution of multi-band EMIC waves to the loss processes of radiation belt electrons.     

Prediction of landslides using ASTER imagery and data mining models

The aim of this study was to identify landslide-related factors using only remotely sensed data and to present landslide susceptibility maps using a geographic information system, data-mining models, an artificial neural network (ANN), and an adaptive neuro-fuzzy interface system (ANFIS). Landslide-related factors were identified in Advanced Spaceborne Thermal Emission and Reflection Radiometer (ASTER) satellite imagery. The slope, aspect, and curvature of topographic features were calculated from a digital elevation model that was made using the ASTER imagery. Lineaments, land-cover, and normalized difference vegetative index layers were also extracted from the imagery. Landslide-susceptible areas were analyzed and mapped based on occurrence factors using the ANN and ANFIS. The generalized bell-shaped built-in membership function of the ANFIS was applied to landslide susceptibility mapping. Analytical results were validated using landslide test location data. In the validation results, the ANN model showed 80.42% prediction accuracy and the ANFIS model showed 86.55% prediction accuracy. These results suggest that the ANFIS model has a better performance than does the ANN in predicting landslide susceptibility.     

Stress analysis and damage evolution in individual plies of notched composite laminates subjected to in-plane loads

This work aims to investigate local stress distribution, damage evolution and failure of notched composite laminates under in-plane loads. An analytic method containing uniformed boundary equations using a complex variable approach is developed to present layer-by-layer stresses around the notch. The uniformed boundary equations established in series together with conformal mapping functions are capable of dealing with irregular boundary issues around the notch and at infinity. Stress results are employed to evaluate the damage initiation and propagation of notched composites by progressive damage analysis(PDA). A user-defined subroutine is developed in the finite element(FE) model based on coupling theories for mixed failure criteria and damage mechanics to efficiently investigate damage evolution as well as failure modes. Carbon/epoxy laminates with a stacking sequence of [45°/0°/ 60°/90°]sare used to investigate surface strains, in-plane load capacity and microstructure of failure zones to provide analytic and FE methods with strong validation. Good agreement is observed between the analytic method, the FE model and experiments in terms of the stress(strain) distributions, damage evaluation and ultimate strength, and the layerby-layer stress components vary according to a combination effect of fiber orientation and loading type, causing diverse failure modes in individuals.     

航空火控技术的发展与探讨

航空火力控制技术是将飞机、目标及武器之间所构成的作战态势与攻击瞄准操纵结合在一起,充分发挥人机效能的一种综合技术。本文对航空火控技术的发展进行了深入的分析和探讨,并结合火控系统一线工作的经验,对我国航空火控系统的发展方向提出了看法。     

热激励在超声速进气道内对激波诱导的边界层分离的控制机理

通过数值模拟的方法研究了马赫5的超声速进气道内,热激励对激波/边界层相互作用的控制机理。研究了热激励器放热功率(E)、热激励器展向放置数目(N)和热激励器到控制激波的距离(S)三个参数在超声速进气道内激波控制和边界层分离改善中的表现。分别针对以下四种条件进行了数值模拟:1)E=2k W、N=2、S=0.02m;2)E=3k W、N=2、S=0.02m;3)E=2k W、N=3、S=0.02m;4)E=2k W、N=2、S=0m。分析发现:在以上四种条件下,均可观察到热激励在控制激波和改善激波诱导边界层分离上有着显著的效果。热激励器的放热功率对激波的控制效果有着明显的影响,在本文所考虑的热激励能量范围内,放热功率越大,原激波角的改变越大,最终分离区的改变越明显;展向放置的热激励器数目N影响着输入到流场的能量密度,并且N越大,壁面附近的激波面越趋于平面。尽管N对上壁面沿展向的压力分布无明显影响,但对上壁面分离区大小有明显的影响;对比条件1和4下的计算结果,发现S=0.02m可以得到很好的控制效果,而S=0m时流场结构几乎没有变化,这就表明热激励器必须放置在控制激波上游的一定距离处才会有预期的效果。     

基于伴随方程和自由变形技术的跨声速机翼气动设计方法研究

将连续伴随方程法与自由变形技术(Free Form Deform-FFD)相结合开展了跨声速机翼气动外形优化设计方法研究。采用Bernstein基函数建立了空间FFD参数化方法,并应用基于控制理论的连续伴随方程方法建立了目标函数对于待优化几何外形的梯度求解模式,将几何外形参数化方法、连续伴随方法以及CFD数值模拟技术相结合,研究、构建了适合跨声速机翼的气动外形优化设计系统。利用该系统对ONERA M6机翼及某型民用客机机翼进行了气动减阻设计,算例验证表明该方法应用于跨声速机翼气动减阻设计效果明显,并且能较好的保持几何表面连续性和光滑性。     

Dihedral influence on lateral–directional dynamic stability on large aspect ratio tailless flying wing aircraft

The influence of dihedral layout on lateral–directional dynamic stability of the tailless flying wing aircraft is discussed in this paper. A tailless flying wing aircraft with a large aspect ratio is selected as the object of study, and the dihedral angle along the spanwise sections is divided into three segments. The influence of dihedral layouts is studied. Based on the stability derivatives calculated by the vortex lattice method code, the linearized small-disturbance equations of the lateral modes are used to determine the mode dynamic characteristics. By comparing 7056 configurations with different dihedral angle layouts, two groups of stability optimized dihedral layout concepts are created. Flight quality close to Level 2 requirements is achieved in these optimized concepts without any electric stability augmentation system.     

某大型民用客机机头顶部板结构抗鸟撞性能优化研究

对弹性动力学的基本理论以及SPH(光滑粒子流体动力学)鸟体模型进行了介绍,并结合相关材料性能参数,以显式动态冲击有限元软件PAM-CRASH为平台,开展某大型民用客机机头顶部板结构抗鸟撞性能验证工作。并设计两种金属玻璃纤维材料作为优化材料,在不增加结构总重量的基础上通过比较结构吸能效果对材料铺层进行优化,选取出抗鸟撞性能最佳的材料供工程设计参考。     

覆冰四分裂导线静态气动力特性试验

覆冰四分裂导线的空气动力特性,由于覆冰子导线尾流的相互干扰可能不同于覆冰单导线。针对两种不同冰型制作覆冰四分裂导线模型,通过风洞试验测试获得不同冰厚和不同风速下覆冰四分裂导线静态空气动力系数随攻角的变化曲线。结果表明,在一定的攻角下,子导线尾流相互干扰对空气动力系数有明显影响。所得试验结果为覆冰四分裂导线的舞动及其防止技术的研究提供必要的数据。     

沉积温度对碳芯SiC 纤维微观结构的影响

以沥青基碳单丝为基体,一甲基三氯硅烷为碳化硅前驱体,使用通电加热的冷壁CVD工艺,温度在1 473～1 773 K,制备了碳芯SiC纤维.采用扫描电子显微镜和拉曼光谱对纤维的表面形貌及结构进行了表征,研究了沉积温度对其结构的影响.结果表明,SiC涂层为β-SiC晶型.沉积温度的升高引起了沉积速率的增加以及SiC涂层晶粒尺寸的长大.同时,导致碳芯中心区域发生结构重排,引起了该区域取向度的提高以及晶粒尺寸的减小.