充气机翼保形设计与气动特性分析

充气机翼是一种典型的柔性充气结构,涉及到变形无人机前沿技术,未来可应用于折叠飞机、科学实验研究飞机、探测火星等其他行星的飞行器。依据内切圆逼近翼型方法,通过静力学进行保形证明,以NACA0018为原型翼型,设计不同内切圆数目逼近的充气机翼,利用CFD方法对所设计的充气机翼进行气动特性分析,研究不同充气机翼的气动特性和优劣性,初步掌握内切圆逼近翼型保形方法的基本性质。最后进行充气机翼的样机制作,并通过飞行试验演示验证充气机翼的飞行性能。结果表明:在低速飞行条件下,充气机翼升力系数较标准翼型有所损失,并且随内切圆数目变化不明显,基本达到标准翼型的80%左右,阻力系数变化较为明显,几乎比标准翼型增加了1.0~1.5倍。     

Modeling and analysis of Earth’s gravity field measurement performance by inner-formation flying system

The Earth’s gravity field can be measured with high precision by constructing the purely gravitational orbit of the inner-satellite in Inner-formation Flying System (IFS), which is independently proposed by Chinese scholars and offers a new way to carry out gravity field measurement by satellite without accelerometers. In IFS, for the purpose of quickly evaluating the highest degree of recovered gravity field model and geoid error as well as analyzing the influence of system parameters on gravity field measurement, an analytical formula was established by spectral analysis method. The formula can reflect the analytical relationship between gravity field measurement performance and system parameters such as orbit altitude, the inner-satellite orbit determination error, the inner-satellite residual disturbances, data sampling interval and total measurement time. This analytical formula was then corrected by four factors introduced from numerical simulation of IFS gravity field measurement. By comparing computation results from corrected analytical formula and the actual gravity field measurement performance by CHAMP, the correctness and rationality of this analytical formula were verified. Based on this analytical formula, the influences of system parameters on IFS gravity field measurement were analyzed. It is known that gravity field measurement performance is a monotone decreasing function of orbit altitude, the inner-satellite orbit determination error, the inner-satellite residual disturbances, data sampling interval and the reciprocal of total measurement time. There is a match relationship between the inner-satellite orbit determination error and residual disturbances, in other words, the change rate of gravity field measurement performance with one of them is seriously restricted by their relative size. The analytical formula can be used to quantitatively evaluate gravity field measurement performance fast and design IFS parameters optimally. It is noted that the analytical formula and corresponding conclusions are applied to any gravity satellite which measures gravity field by satellite perturbation orbit.     

一种遥测缓变参数自动判读的新方法

针对遥测参数中缓变参数的自动判读问题，提出一种基于历史数据统计特性的遥测缓变参数自动判读新方法。首先，设计了一种以参数目标数据时标为基准的时间间隔递推算法和线性插值方法，使历史数据与目标数据的时标得到有效统一。其次，基于方向和距离函数构造了双因子等价权函数，并利用抗差最小二乘估计算法得到了参数的估值和标准差。最后，根据参数的估值和标准差对目标数据进行统计分析，依据目标数据的概率分布判断参数是否存在异常，进而实现参数的自动判读。仿真校验结果表明，该方法能有效辨识缓变参数中的异常参数，且具有较强的抑制随机噪声和抗差自适应能力。与传统以人工为主的判读方式相比，该方法能有效提高遥测参数判读的效率和准确性。     

Solar terrestrial effects of two distinct types

The occurrence frequencies or fluxes of most of the solar phenomena show a 11-year cycle like that of sunspots. However, the average characteristics of these phenomena may not show a 11-year cycle. Among the terrestrial parameters, some related directly to the occurrence frequencies of solar phenomena (for example, ionospheric number densities related to solar EUV fluxes which show 11-year cycle like sunspots) show 11-year cycles, including the double-peak structures near sunspot maxima. Other terrestrial parameters related to average characteristics may not show 11-year sunspot cycles. For example, long-term geomagnetic activity (Ap or Dst indices) is related to the average interplanetary solar wind speed V and the total magnetic field B. The average values of V depend not on the occurrence frequency of ICMEs and/or CIRs as such, but on the relative proportion of slow and high-speed events in them. Hence, V values (and Ap values) in any year could be low, normal or high irrespective of the phase of the 11-year cycle, except that during sunspot minimum, V (and Ap) values are also low. However, 2–3 years after the solar minimum (well before sunspot maximum), V values increase, oscillate near a high level for several years, and may even increase further during the declining phase of sunspot activity, due to increased influence of high-speed CIRs (corotating interplanetary regions). Thus, Ap would have no fixed relationship with sunspot activity. If some terrestrial parameter shows a 11-year cycle, chances are that the solar connection is through the occurrence frequencies (and not average characteristics) of some solar parameter.     

火花型合成射流激励器流动特性及其激励参数数值研究

利用能量方程中的源项模拟电火花能量的输入,数值模拟了火花型合成射流激励器的流场,获得了激励器的能量蓄积、喷射和吸入过程.结果表明:电火花瞬间能量的输入产生了腔体内的高温、高压环境,从而诱发合成射流的形成;在周期性激励下,合成射流在3个周期后稳定,喷口处的速度呈现非正弦的周期性变化,射流喷射过程时间极短,吸入外界环境气体...     

统筹图中求有关参数的权关联矩阵算法

给出一个求统筹图中有关参数的数值算法，证明了算法的理论依据，并举例说明算法的应用。     

Study of atmospheric air pollutants during the partial solar eclipse on 15 January 2010 over Udaipur: A semi-arid location in Western India

The paper describes behavior of surface ozone, its precursor gases, BC along with TOCC, TWVC, AOT1020 nm as well as UV and IR radiation intensities observed during the partial solar eclipse of 15th January, 2010 over Udaipur, where 52% solar disc is obscured due to the moon’s shadow. During the beginning to main eclipse phase, the deviation values of several air pollutants concentrations from eclipse to control day values vary in a small range from −9 to −2 ppb in case of surface ozone and −180 to −80 ppb for CO. The corresponding change in the values of BC observed from −3.3 to −.5 μg/m³. No significant change is found in NO₂, NO or in ratio of NO₂/NO values during the partial eclipse time. TOCC values decrease from 3 to 5 DU along with a reduction in UV radiation intensity from 20 to 35% from starting to the main eclipse phase. The AOT1020 nm values are found to increase from .2 to 1.0 along with a reduction in IR radiation intensity order of 50%. However, TWVC values decrease from .22 to .1 cm during the eclipse hours. The low level of dilution in surface ozone in eclipse period may be attributed with change in local atmospheric boundary layer dynamic conditions or limited air pollutants dispersion, in term of decreases in planetary boundary layer height, wind speed and hence ventilation coefficient in the same eclipse hours. Thus, present studies support the argument for the leading roles of photochemical reactions with its precursor gases under presence of solar radiation in surface ozone variability. Other possible controlling factors are advection of air pollutants from the polluted region as evident from backward wind trajectories and altering the local meteorological conditions.     

Sealing reliability modeling of aviation seal based on interval uncertainty method and multidimensional response surface

Many variables affect the sealing performance, and their distribution characteristics are difficult to obtain with probabilistic methods owing to the high cost involved. Numerous problems in engineering are similar due to the appearance of small-sample parameters. In this study, the sealing reliability of an aviation seal was defined as the research object, and an interval uncertainty method and multidimensional response surface were proposed to calculate the sealing reliability.Based on this, we first analyzed the failure mechanism of the aviation seal and established a leakage rate model. Then, based on the non-probabilistic interval model, an interval uncertainty method was proposed to construct the analytical model. With reference to the limit state equation from the structural reliability theory, the multidimensional response surface was used for fast calculation.Then, we chose the single-cylinder gas steering gear used in aircraft as the case study, its sealing reliability in working and non-working statuses were calculated, and the results were verified with the actual maintenance records. By analyzing the sensitivity of some variables, we can improve the sealing reliability of the aviation seal by improving the surface roughness only if the cost allows.Finally, we consider that the method proposed in this study realizes the application of smallsample uncertainty analysis in reliability analysis, and could provide a feasible way to solve the similar problems in engineering with multidimensional and small-sample parameters.     

喷雾液滴撞击液膜影响参数及流动机理分析

液滴撞击壁面是喷雾冷却中最常见的现象。使用计算流体力学软件中的Volume of Fluid （VOF）模型对液滴撞击壁面过程进行了数值模拟研究，研究了不同参数的液滴撞击壁面液膜过程的水花形态特点，针对水花高度和直径等参数进行了分析，通过运动间断理论和无量纲参数Re和We的变化分析了不同参数对液膜的流动特征和水花形态的影响及水花产生机理。结果表明：大液滴撞击液膜时能够改善液膜的流动状态；过大的液滴速度会产生大量飞溅及表面干涸；液滴撞击薄液膜时，液膜的流动性较好，当0.6<h*<1.2时，液膜的流动性不随液膜厚度改变。     

飞行状态对太阳能飞机中组件性能的影响

基于光伏组件产生功率模型，研究了太阳能飞机中飞行速度、高度、时间及区域等状态参数影响组件性能的规律。以单晶硅组件及Xihe太阳能飞机为研究对象，当飞机飞行速度增加时，组件产生的功率随之增加但趋于饱和。原因在于速度的增加能有效降低组件的表面温度，但提升是有限的。飞机所需的功率随飞行速度呈现指数增加，且组件产生的功率与飞机所需的功率有能量平衡点。组件产生的功率随飞行高度的增加而增加，但有饱和的趋势。原因在于，当飞行高度上升，大气温度随之下降，组件表面温度下降；同时海拔越高，大气密度和大气通透率越大，太阳辐射增加，从而组件产生的功率增加了；饱和的原因在于组件本身性能的限制。一天之中，组件产生的功率基本以太阳时12点为中心左右近似对称，中午最强；一年中组件性能在夏季最强，冬季最弱。原因在于组件性能主要由所受太阳辐射决定。随着纬度的增加，组件产生的功率减小。原因在于，纬度越高，太阳高度角越小，组件所能接受到的太阳辐射也就越小；纬度越低，组件总产生功率越高且平稳。纬度低的地区更适合太阳能飞机的飞行。该文为太阳能飞机的能量分配、长时间驻空提供一定的帮助。