平流层飞艇艇务管理任务分析

针对平流层飞艇的特点，文章分析艇务管理的主要任务，并对艇务管理的任务特点探讨了艇务管理系统在设计时可采用的各种技术，为开展平流层飞艇的研制提供设计思路。     

平流层飞艇艇务管理任务分析

针对平流层飞艇的特点,文章分析艇务管理的主要任务,并对艇务管理的任务特点探讨了艇务管理系统在设计时可采用的各种技术,为开展平流层飞艇的研制提供设计思路。     

飞艇的信息战应用研究

飞艇广泛应用于预警、侦察、通讯、干扰等信息对抗领域,具有传统航空器无法取代的优势.分析了飞艇的信息化作战应用和国外的技术现状,并在此基础上,讨论了飞艇信息战应用的发展趋势和所涉及的一系列关键技术.     

平流层飞艇的环境控制

文章叙述了平流层飞艇要经历的对流层和平流层的环境特点,对平流层飞艇的环境控制进行了分析,并提出了环境控制的几个注意问题。     

平流层飞艇控制与推进技术

飞艇作为平流层平台可以实现无线通信、空间观测、大气测量以及军事侦察等目的。本文主要结合平流层的环境特点对平流层飞艇动力推进系统的组成和概念进行初步分析,并对飞艇在升空、浮空、回收过程中的飞行控制策略进行探讨,同时简要分析了控制系统的组成、控制难点和飞艇应急控制问题。     

平流层飞艇的结构健康监测系统初探

文章从介绍平流层飞艇的结构健康监测定义入手,说明了该系统研究的作用和意义以及工作原理。在分析平流层飞艇运行环境和结构可能的损伤模式的基础上,从工程应用角度出发,对结构健康监测系统方案展开了研究,探讨了平流层飞艇结构健康监测系统中的一些关键因素,为今后结构健康监测系统设计提供参考。     

基于阻力气动特性计算的飞艇艇身外形研究

采用SIMPLE算法、S-A湍流模型求解了三维不可压雷诺平均N-S方程,数值模拟了绕飞艇的低速不可压粘性流动,计算了不同艇身外形的阻力特性.本文方法计算结果与实验结果或其他文献的计算结果符合良好,可以用于飞艇的气动特性计算.通过对6个不同外形的相同体积飞艇阻力特性计算,得到了最佳艇身外形,表明本文方法可以用于艇身外形的选型设计.     

A general calculation method to specify center-of-buoyancy for the stratospheric airship with multiple gas cells

As the lighter-than-air (LTA) flight vehicle, the stratospheric airship is a desirable platform to provide communication and surveillance services. During the ascent from sea-level to the mission altitude, the volume of the lifting gas may change significantly, which will result in the change of the center-of-buoyancy (CB). A general calculation method is developed to specify CB for the stratospheric airship with a double-ellipsoid hull and an arbitrary number of the gas cells. The cross-section-integral (CSI) method is used as a basic calculation scenario to specify CB. Considering the complexity in determining the boundary between the helium and air in the gas cell, a searching algorithm is put forward and the specification of CB can be conducted by the iterative calculation. As an important application, the stable condition of the pitch angle is analyzed when the change of CB is involved. Under different initial configurations, the stable pitch angle of the stratospheric airship during the ascent is specified and compared, which shows the advantages of the multi-gas-cell configuration. The results of this paper may provide an important reference for the engineering application of the stratospheric airship.     

A comparative and numerical study of effects of gravity waves in small miss-distance and miss-time GPS radio occultation temperature profiles

The Global Positioning System (GPS) Radio Occultation (RO) technique has global coverage and is capable of generating high vertical resolution temperature profiles of the upper troposphere and lower stratosphere with sub-Kelvin accuracy and long-term stability, regardless of weather conditions. In this work, we take advantage of the anomalously high density of occultation events at the eastern side of the highest Andes Mountains during the initial mission months of COSMIC (Constellation Observing System for Meteorology, Ionosphere and Climate). This region is well-known for its high wave activity. We choose to study two pairs of GPS RO, both containing two occultations that occurred close in time and space. One pair shows significant differences between both temperature profiles. Numerical simulations with a mesoscale model were performed, in order to understand this discrepancy. It is attributed to the presence of a horizontal inhomogeneous structure caused by gravity waves.     

Temperature comparison between CHAMP radio occultation and TIMED/SABER measurements in the lower stratosphere

Global Positioning System (GPS) receiver on the CHAllenging Mini-satellite Payload (CHAMP) and the Sounding of the Atmosphere using Broadband Emission Radiometry (SABER) instrument, one of four on board the TIMED satellite, provide middle atmosphere temperature profiles by Radio Occultation (RO) and limb viewing infrared emission measurements, respectively. These temperature profiles retrieved by two different techniques in the stratosphere are compared with each other using more than 1300 correlative profiles in March, September and December 2005. The over-all mean differences averaged over 15 and 35 km are approximately −2 K and standard deviation is less than 3 K. Below 20 km of altitude, relatively small mean temperature differences ∼1 K are observed in wide latitudinal range except for June (during the SABER nighttime observation). In the middle to low latitudes, between 30°S and 30°N, the temperature difference increases with height from ∼0–1 K at 15 km, to ∼−4 K at 35 km of altitude. Large temperature differences about −4 to −6 K are observed between 60°S and 30°N and 31–35 km of altitude for all months and between 0° and 30°N below 16 km during June (nighttime).