平流层飞艇气动外形优化设计:螺旋桨的影响

建立综合螺旋桨影响的平流层飞艇气动外形优化设计平台.采用Hicks-Henne型函数法参数化艇身轮廓,发展IDW-TFI混合动网格技术实现变形网格高效生成;基于作用盘理论模拟螺旋桨,建立飞艇流场高效数值求解方法.以LOTTE飞艇作为初始外形,阻力系数最小为目标,飞艇体积作为约束条件,通过NLPQL算法寻优获得最佳艇身设计方案.优化后飞艇的尾部形状较平坦,艇身最大横截面位置前移,气动性能得到明显改善,其阻力系数相对于初始外形降低了26.88%.     

激光本振红外光谱干涉成像及其艇载天文应用展望(特邀)

本文分析了红外干涉成像现状和难点,介绍了激光本振红外相干探测的原理,阐述了基于电子学的红外光谱细分和干涉成像原理,讨论了激光本振红外阵列探测器形式.激光本振和相干探测器的设置,可保证两个望远镜的红外信号相位的正确传递,在电子学实施窄带滤波形成的窄带红外信号有利于实现长基线干涉成像.在此基础上,类似微波综合孔径射电望远镜...     

平流层飞艇绕流场与柔性变形的数值模拟

处于平流层流场中的飞艇,其整体刚度较小,为柔性体,可视为弹性薄膜结构,外围的流场的状态分布与其形状有着密切的关系,从本质上说是一个流固耦合问题。本论文以此为背景,分析了平流层飞艇的外围流场与柔性蒙皮变形的非动态耦合关系。我们采用叠代计算方法来处理这一问题,其中飞艇的三维流场的计算本文采用基于有限体积法的压力修正SIMPLE算法,而飞艇弹性变形的数值模拟计算应用了薄壳无矩理论。本文比较了气动弹性变形和静态超压变形两种不同情况下的飞艇流场压力分布以及气动参数,分析了飞艇变形与流动参数、气动荷载变化的关系。     

临近空间平台光电探测系统在空间态势感知中的应用

介绍了空间态势感知的概念,以及地基、天基光电探测系统和临近空间平台的特点及研究现状,对不同平台光电探测系统的性能与特点进行了分析。分析表明,地基光电探测系统的观测质量受地球大气湍流和大气吸收的影响,有其极限探测能力,且大部分大气扰动发生在大气最底层的对流层;天基光电探测系统虽然可不受大气湍流的扰动,但光电探测平台的探测时间只有地基望远镜的1/3,且耗资巨大;临近空间平流层平台(飞艇)光电探测系统不受对流层大气扰动的影响,其分辨力可显著提高,并且具有灵活布站等优势。基于临近平台光电探测系统的优势,综述了发展临近平台空间光电探测系统的可行性,归纳总结了将其应用于空间态势感知的技术要求,涉及材料、控制、能源和高能物理等。     

Correction of temperature influence on the wind retrieval from a mobile Rayleigh Doppler lidar

A mobile Rayleigh Doppler lidar based on double-edge technique is implemented for simultaneously observing wind and temperature at heights of 15 km-60 km away from ground.Before the inversion of the Doppler shift due to wind,the Rayleigh response function should be calculated,which is a convolution of the laser spectrum,Rayleigh backscattering function,and the transmission function of the Fabry-Perot interferometer used as the frequency discriminator in the lidar.An analysis of the influence of the temperature on the accuracy of the Une-of-sight winds shows that real-time temperature profiles are needed because the bandwidth of the Rayleigh backscattering function is temperature-dependent.An integration method is employed in the inversion of the temperature,where the convergence of this method and the high signal-to-noise ratio below 60 km ensure the accuracy and precision of the temperature profiles inverted.Then,real-time and on-site temperature profiles are applied to correct the wind instead of using temperature profiles from a numerical prediction system or atmosphere model.The corrected wind profiles show satisfactory agreement with the wind profiles acquired from radiosondes,proving the reliability of the method.     

AIRSHIP ATTITUDE TRACKING SYSTEM

The attitude tracking control problem for an airship with parameter uncertainties and external disturbances was considered in this paper. The mathematical model of the airship attitude is a multi-input/multi-output uncertain nonlinear system. Based on the characteristics of this system, a design method of robust output tracking controllers was adopted based on the upper-bounds of the uncertainties. Using the input/output feedback linearization approach and Liapunov method, a control law was designed, which guarantees that the system output exponentially tracks the given desired output. The controller is easy to compute and complement. Simulation results show that, in the closed-loop system, precise attitude control is accomplished in spite of the uncertainties and external disturbances in the system.     

NUMBER CONCENTRATION, SIZE DISTRIBUTION AND FINE PARTICLE FRACTION OF TROPOSPHERIC AND STRATOSPHERIC AEROSOLS

1. Introduction The number concentration and size distribution of at-mospheric particles are the two major parameters for aerosol radiative forcing calculation, as the aerosol bur-dens affect the radiative transfer of solar and terrestrial emissions, while the size distribution of atmospheric aerosol is critical to all climatic influences (IPCC, 2001). However most measurements on the characteristics of the number-size distribution were carried out near the earth surface, with only a few exte…     

风场环境下平流层飞艇运动建模

平流层飞艇驻空飞行阶段的航速和空速量级可比拟,考虑风的影响时,基于地速的动力学模型必须显式补充风引起的附加惯性力,其运动方程将变得很复杂.作者首先依据风场环境下地速、风速和空速之间的关系,推导了基于空速的动力学模型.该模型具有形式简单、与飞艇动力学联系更加密切且无需计算风引起的附加力的优点.其次,建立了基于上述模型的飞艇六自由度动力学仿真模型,并针对标称运动条件下的系统开环输入进行仿真并简要分析了仿真结果.     

Detection of minor constitutents of the stratosphere by far infrared emission spectroscopy

The far infrared (30–110 cm^–1) emission spectrum of the lower stratosphere has been measured from balloon altitudes with a high resolution (0.06 cm^–1) rapid-scanning Michelson interferometer on two flights in 1976. The quality and resolution of the spectra obtained from two altitudes have permitted a careful search for emission lines from environmentally important molecules such as HCl, NO₂, OH, H₂O₂, and CO, among the more prominent and well-known features due to H₂O, O₃ and O₂. Column densities have been determined for H₂O and O₃ and upper limit estimates have been made from tentative identifications of several other constituents. However, the large angular field of view observed by the instrument prevented the determination of concentration profiles from atmospheric limb scans to the horizon. The possible future directions of this technique are outlined on the basis of operating experience over a 6 year programme. The viability of this method of monitoring the concentrations of minor constituents in the stratosphere is discussed with respect to other equivalent techniques.     

飞艇红外探测系统探测高超声速目标性能研究

以X-51A为例,研究了飞艇红外探测系统对临近空间高超声速目标的探测性能。首先,根据飞行器的飞行状态和飞行高度建立了临近空间高超声速目标不同波段的红外辐射特性模型,以及随高度变化的目标背景红外辐射强度模型;其次,综合考虑飞行器与飞艇高度、地球曲率及红外辐射在大气中传播的波段选择性等因素,建立了红外辐射在临近空间大气中传播的透过率模型;在此基础上,建立了飞艇红外探测系统对高超声速目标的探测距离模型。通过仿真得到了临近空间高超声速目标在不同飞行状态下3个波段的红外辐射强度随目标飞行高度变化的曲线,以及飞艇红外探测系统对飞行器在不同飞行状态下3个红外辐射波段的探测能力。研究结果表明:飞艇红外探测系统对高超声速目标的有效探测距离可以达到百公里量级;当飞行器飞行状态一定时,随着飞行器飞行高度的增加,系统对目标的探测距离先增大后减小;与长波波段相比,中短波波段的探测距离更大,并给出了临近空间飞艇应尽量布置在海拔高度大于18 km的高空中的部署建议。