粒子分离器气动特性数值研究

本文利用张量分析建立了三维贴体坐标系上的通用输运方程;采用贴体网格计算了粒子分离器二相流的三维流场;建立了三维的粒子运动轨迹微分方程,理论上分析了粒子分离器结构设计对其性能的影响,与试验结果吻合较好。     

Stable Supervisory-Adaptive Controller for Spinning Satellite using Only Magnetorquers

In this paper, an adaptive controller for spinning satellites has been designed to achieve high attitude accuracy. In the cases which magnetorquers are used as actuators, the generated torque is perpendicular to the Earth's magnetic field, so a satellite is not completely controllable. In addition, the maximum value of achievable torque is limited due to capacity of magnetorquers. Hence, implementation of adaptive control law causes attitude error in system and also decreases the speed of response. To overcome these problems, a supervisory-adaptive controller has been designed. In this regard, sliding control has been used as a supervisory controller to correct the control signal applicable to magnetorquers. As a result of this method, stability of the system has been proved, output error has been decreased, and speed of response has been increased.     

微型飞行器桨翼气动干扰的数值模拟

对某一固定翼微型飞行器进行了桨翼气动干扰数值模拟研究,采用作用盘理论模拟真实桨盘的工作状态,通过时间平均稳态处理将非定常流场简化为准定常流场计算。利用FLUENT的用户自定义函数UDF实现作用盘前后压力、速度的变化。通过与无滑流影响下单独机身数值计算结果的比较,结果显示螺旋桨滑流延缓了机体上表面的气流分离,增强气流再附着能力,飞机的失速迎角增加2°,升力、阻力、俯仰力矩系数增加2%～5%,升阻比减小2%～3%。     

毫米波鳍线平衡混频器研究

 本文研究了一种八毫米波段平衡混频器的工程设计方法,并给出了实验测试结果。在针对实际电路结构建立起等效电路模型后,采用最优化方法对电路结构参量作了优化。对实际制做的混频器性能作了初步测试,最佳双边带噪声系数约为6dB(其中包括1.4dB中放噪声贡献在内)。     

一种安全的身份认证模型的研究与实现

研究分析了Radius身份认证协议,就其在安全性方面的不足给出了解决办法,同时根据给出的解决方案构建一种身份认证模型,最后对新构建的模型进行安全性分析,通过实例证明该模型是安全的、可靠的、实现简单的、并具有很强的实用价值。     

非结构聚合多重网格法流场数值模拟研究

 在非结构网格上应用聚合多重网格技术来加速 Euler方程的收敛过程。设计了一种高效率的网格聚合方法。采用四重网格,在每一层网格上采用有限体积法进行计算。通过对多段翼型绕流的数值求解验证了多重网格加速收敛的高效性。     

大展弦比机翼剖面刚度分析

通过对变截面悬臂梁在一端受载时,自由端的位移、转角和悬臂梁各剖面刚度之间关系的分析,推导出一种基于有限元模型的剖面刚度计算方法。针对某型飞机,对机翼结构进行适当简化,建立机翼主承力结构的有限元模型,采用所推导出的方法计算了机翼沿展向各剖面的刚度,其结果可为某型飞机机翼结构设计和气动弹性分析提供参考。     

A UHF True Logarithmic IF Amplifier

A UHF ?true logarithmic IF? which yields a carrier output proportional in amplitude to the logarithm of the carrier input has been constructed. Although this ?true? form has been known for a number of years, it appears to have been neglected in development. Good performance has been obtained over a 60-dB input signal range with rise and fall times of 2 ns per 20 dB. A high-level, detected dc coupled output without the use of any dc amplifier is obtained. Coherent signal processing of the output carrier is possible, and other important advantages to this type of logarithmic IF are described.     

民用飞机风挡表面对流换热系数的校核

适航条款要求在结冰条件下,应确保风挡表面不能结冰,防止影响飞行员视界。因此应确定结冰条件下具有足够的电加热功率使风挡表面温度高于冰点(零度),而影响加热功率的关键因素是外表面的对流换热系数。为了获得准确的对流换热系数,在低速风洞中测量了不同工况下风挡表面对流换热系数,并利用CFD方法建立了一个仿真风洞模型,计算试验工况下的风挡表面对流换热系数,通过测量值来校核CFD的计算值,获得一个修正方法,最终使用这个修正方法计算获得其他工况下的对流换热系数。     

Theoretical study of flow ripple for an aviation axial-piston pump with damping holes in the valve plate

Based on the structure of a certain type of aviation axial-piston pump＇s valve plate which adopts a pre-pressurization fluid path （consisting a damping hole, a buffer chamber, and an orifice） to reduce flow ripple, a single-piston model of the aviation axial-piston pump is presented. This sin- gle-piston model comprehensively considers fluid compressibility, orifice restriction effect, fluid resistance in the capillary tube, and the leakage flow. Besides, the instantaneous discharge areas used in the single-piston model have been calculated in detail. Based on the single-piston model, a multi-piston pump model has been established according to the simple hydraulic circuit. The sin- gle- and multi-piston pump models have been realized by the S-function in Matlab/Simulink. The developed multi-piston pump model has been validated by being compared with the numerical result by computational fluid dynamic （CFD）. The effects of the pre-pressurization fluid path on the flow ripple and the instantaneous pressure in the piston chamber have been studied and opti- mized design recommendations for the aviation axial-piston pump have been given out.     

AFIT neural network research

A brief summary of research done at the Air Force Institute of Technology (AFIT) in the area of neural networks is provided. It has been shown that backpropagation, used for feedforward artificial neural networks, is just a degenerate version of an extended Kalman filter, and that networks can do about as well as the optimum statistical classification technique. A method of finding the importance of features for use by a neural network classifier has been determined. Techniques for using neural networks for image segmentation have been developed. In optical pattern recognition, techniques that allow the processing of real FLIR (forward-looking infrared) images with existing binary spatial light modulators have been devised. An optical direction of arrival detector applicable to laser illumination direction determination has been designed and tested; the design is similar to a fly's eye. Coated mirrors for the optical confocal Fabry-Perot interferometer have been designed, specified, fabricated, and installed. Significant progress has been made in the use of neural networks for processing multiple-feature sets for speech recognition     

NND格式在航天飞机头部段N—S方程求解中的应用

本文采用实质上为二阶精度的无波动、无自由参数的耗散差分格式(NND格式)求解了非定常的二维和三维完全N-S方程,对类似于航天飞机头部外形的超声速粘性气体绕流流场进行了模拟。在计算中,使用了代数网格生成技术,对脱体激波采用了装配法。作为验证算例的二维圆柱绕流计算结果同文献[4]的数据进行了比较。二维凹陷外形绕流的计算结果同无粘流结果进行了对比,由于粘性流动出现了分离,二者的壁面压力是有差异的。最后,对三维外形的绕流也进行了模拟,计算结果提供了流场的细节。     

尾迹与涡轮叶栅边界层的相互作用

通过实验和数值模拟的手段研究了尾迹与边界层的相互作用,其中上游叶排尾迹的模拟是通过在涡轮叶栅前设置周期性运动的圆柱实现的.研究表明,上游尾迹对涡轮叶栅边界层的发展有显著影响,在其作用下,吸力面边界层提前转捩,分离得到明显的抑制,利用尾迹与边界层相互作用的非定常效应可以明显提高低压涡轮叶栅气动负荷.      

基于SIMULINK的超声速进气道仿真方法

将进气道一维流动的偏微分方程离散为一系列可积分的线性常微分方程,基于此创建了超声速进气道仿真模型,提出了一种基于SIMULINK的进气道仿真方法,模拟了来流参数和燃烧室反压扰动时流场内各个参数的变化规律。对一个一维变几何超声速进气道进行仿真,获得了结尾正激波的稳态特性及动态特性。该模型定义并输出了激波位置,有效地将一维超声速进气道的分布参数问题转换为零维问题,解决了系统分析与控制系统设计中无法实现集总参数的困难。     

Some early results of the keV plasma experiment on GEOS-1

Some preliminary new results are presented of the keV plasma experiment on GEOS-1. Electrons and ions have been observed to stream along the magnetic field lines in the dayside magnetosphere from the ionospheric side of the satellite towards the equatorial plane during magnetic storms, with streaming velocities corresponding to a kinetic energy of the order of a keV. The opposite streaming velocity has also been seen, but primarily in the ions only and with a smaller flux ratio for the two opposite directions along the field lines. The transition between the two opposite streaming directions, as seen by the satellite, has been found to occur even in a fraction of a second.In magnetic storm conditions azimuthal asymmetries in ion fluxes corresponding to electric field intensities of several tens of millivolts per meter have been observed.     

Cavity element for resonant micro optical gyroscope

Significant strides have been made towards a feasible resonant micro optic gyro (RMOG). Uniquely crucial components have been developed. Experimental measurements, when coupled with theoretical analysis predicts that 1 degree/hour performance can be achieved. Three critical elements required for the successful development have been demonstrated. A high quality trench waveguide has been designed, fabricated and demonstrated to have losses as little as 0.1 dB/cm. The waveguide has been demonstrated to have gain in the 4.0 dB/cm range. Finally, a waveguide laser has been fabricated and has shown nearly enough power to adequately drive an RMOG. Analysis of the measured performance predicts that a 1 degree/hour RMOG can be constructed. The small size and projected ruggedness of the RMOG will be advantageous in high G applications. Other applications, such as man portable guidance systems, where weight and size are critical, may also benefit from RMOG technology     

雨雾环境下温度传感器动态特性测试方法

针对雨雾环境下温度传感器的动态特性测试，对常规测试装置进行了改进，研究了雨雾环境的产生和控制方法，并提出了雨雾环境下传感器动态特性的试验方法，在此基础上对某传感器进行了试验，得到了其常规环境和雨雾环境下的动态特性试验结果，试验结果表明雨雾环境下传感器的动态特性会大幅提高；最后，对试验结果和试验中存在的问题进行了分析，明确了试验方法的改进方向。     

Stability,flying qualities and longitudinal parameter estimation of a twin-engine CS-23 certified light aircraft

This paper presents some results of the flight test campaign conducted on the Tecnam P2006T aircraft, on the occasion of its certification process. This twin-engine propeller airplane is certified under the normal category CS-23 and FAR 23. A prototype of this light aircraft has been tested in flight for a post-design performance optimization and for the assessment of flight qualities. These experiences have led to the application of two winglets to the original wing. The final configuration has been extensively tested for the achievement of CS-23 certification. The longitudinal and lateral-directional response modes have been assessed and quantified. At the same time the longitudinal airplane model, through a dedicated set of flight maneuvers, has been characterized by means of parameter estimation studies. The aircraft stability derivatives have been estimated from the acquired flight data using the identification technique known as Output Error Method (OEM). Some estimated stability derivatives have been also compared with the corresponding values extracted from leveled flight tests and from wind tunnel tests performed on a scaled model of the aircraft.     

The SOURDINE Project: developing environmentally friendly arrival and departure procedures

Next to other projects to reduce the aircraft source noise, SOURDINE has performed on initial study into the possibilities to reduce aircraft noise by modifications to current aircraft operational approach and departure procedures. A number of potential solutions have been identified in this area and an illustration of the obtainable benefits has been made. The project has been carried out in preparation of a follow-on project, which will further develop the most promising solutions that have been identified in this project.     

直升机海上搜潜控制的设计与仿真

对反潜直升机海上搜潜控制系统进行了详细的研究。建立了完整的系统各部件的模型。通过建立合适的海浪模型，采用维纳滤波法设计出实用的海浪滤波器。设计了缆位稳定模态和缆高保持模态控制律，通过数学仿真，对控制律的结构和参数进行了相应的调整，并在试飞中通过了验证。