基于DATCOM的飞机初步设计

为减少飞机设计过程中的不必要的硬件更改，提出了飞机初步设计阶段基于模型的设计思路。通过一个1/4风笛手J-3幼兽无人机的实例，说明如何通过DATCOM优化一个飞机结构设计、计算出气动特性，并提前分析所选择特定结构外形的飞机起飞着陆等性能，以提前预估所设计的飞机是否能够满足或基本满足设计要求。分析表明，基于模型的设计过程能够在一种快速可重复的模式下进行，能够很好控制飞机设计过程中的成本。     

Interference-free wind tunnel testing of jet propelled missiles

Wind tunnel evaluation of the aerodynamic interaction effects between plume and the external flow past the missile body including the wake boundary (“slipstream”) over powered flight envelopes of rocket propelled vehicles can be greatly facilitated — or even made possible — by a methodology replacing the hot propellant by cold, inert gases. Model nozzle design is based on the second order matching of plume geometry and first order modeling of plume stiffness. Since modeled nozzles will have larger throat radii than the prototypes, one can use sting-supported, sting-fed model installations thus eliminating aerodynamic interference effects due to struts. The concepts of simulated altitude and simulated full-scale Reynolds Number greatly reduce wind tunnel occupancy time. Computer programs, covering all steps of evaluating prototype nozzle performance, model sting nozzle design, model test evaluation and interpretation have been developed. The modeling methodology is supported by experimental results obtained in an induction wind tunnel at the FFA, Bromma, Sweden and in the 16 T and VKF-A altitude tunnels at AEDC, Tullahoma, Tenn.     

涡扇发动机空中减速过程转速预测

以某型涡扇发动机为研究对象,对其空中减速的试验数据进行深度挖掘,分析了减速过程中低压和高压转速的变化规律,得到该型发动机空中减速过程中转速的预测关系式,并对预测结果进行验证。结果表明,通过预测关系式计算所得结果与飞行试验数据吻合良好,可用作该型发动机空中减速过程的转速预测。     

Loop Models from SOHO Observations

The Coronal Diagnostic Spectrometer (CDS) on SOHO is a grazing/normal incidence spectrograph, aimed to produce stigmatic spectra of selected regions of the solar surface in six spectral windows of the extreme ultraviolet from 150 Å to 785 Å (Harrison et al. 1995). In the present work, CDS, EIT, MDI and Yohkoh observations of active region lops have been analyzed. These observations are part of JOP 54. CDS monochromatic images from lines at different temperatures have been co-aligned with EIT and MDI images, and loop structures have been clearly identified using Fe XVI emission lines. Density sensitive lines and lines from adjacent stages of ionization of Fe ions have been used to measure electron density and temperature along the loop length; these measurements have been used to determine the electron pressure along the loop and test the constant pressure assumption commonly used in loop modeling. The observations have been compared with a static, isobaric loop model (Landini and Monsignori Fossi 1975) assuming a temperature-constant heating function in the energy balance equation. Good agreement is found for the temperature distribution along the loop at the coronal level. The model pressure is somewhat higher than obtained from density sensitive line ratios.     

Coronal Heating: a Comparison of Ion-cyclotron and Gravity Damping Models

SOHO/UVCS data indicate that minor ions in the corona are heated more than hydrogen, and that coronal heating results in T_⊥ larger than T_‖. Analogous behavior has been known from in situ measurements in solar wind for many years. Here we compare and contrast two mechanisms which have been proposed to account for the above behavior: ion-cyclotron resonance and gravity damping. This revised version was published online in June 2006 with corrections to the Cover Date.     

Comparison of Polar and Equatorial Coronal Holes Observed by UVCS/SOHO: Geometry and Physical Properties

We analyzed UVCS/SOHO data and compared the H I Lyα (121.6 nm) and O VI (103.2 nm, 103.7 nm) emission in the polar and equatorial coronal holes. We found that the emission lines have similar characteristics in these two types of coronal holes. Both types show evidence for superradially diverging boundaries. The latitudinal distribution of the O VI line ratio may indicate that the equatorial coronal hole has O⁺⁵ outflow velocities lower than in the polar coronal holes. This revised version was published online in June 2006 with corrections to the Cover Date.     

空气动力对飞机内藏式导弹分离轨迹影响的低速风洞试验研究

在４ｍ×３ｍ低速风洞中研究了空气动力对战斗机内藏式导弹弹射分离轨迹的影响。采用简单网格法测量了导弹在干扰流场中的气动力，进行了分离轨迹估算，用捕获轨迹试验得到了分离轨迹，选定了最佳弹射力参数。试验结果表明，实验导弹安全分离必须采用弹射力，气动俯仰力矩是影响导弹姿态的重要因素，气动力对分离位置影响较小。     

UVCS/SOHO Observations of H I Lyman Alpha Line Profiles in Coronal Holes at Heliocentric Heights Above 3.0 R⊙

The Ultraviolet Coronagraph Spectrometer (UVCS) on the Solar and Heliospheric Observatory (SOHO) has been used to measure spectral line profiles for H I Lyα in the south polar coronal hole at projected heliocentric heights from 3.5 to 6.0 R_⊙ during 1998 January 5–11. Observations from 1.5 to 2.5 R_⊙ were made for comparison. The H I Lyα profile is the only one observable with UVCS above 3.5 R_⊙ in coronal holes. Within this region the outflowing coronal plasma becomes nearly collisionless and the ionization balance is believed to become frozen. In this paper, the 1/e half widths of the coronal velocity distributions are provided for the observed heights. The velocity distributions include all motions contributing to the velocities along the line of sight (LOS). The observations have been corrected for instrumental effects and interplanetary H I Lyα. The half widths were found to increase with projected heliographic height from 1.5 to 2.5 R_⊙ and decrease with height from 3.5 to 5 R_⊙. This revised version was published online in June 2006 with corrections to the Cover Date.     

多发飞机着陆进场最小操纵速度人机闭环仿真

为了提高着陆进场最小操纵速度(VMCL)的分析预测精度,提出了一种通过人机闭环数学仿真来计算多发飞机着陆进场VMCL的方法。考虑临界发动机突然停车后拉力的衰减过程、驾驶员意识到发动机失效后采取操纵的时间延迟,以及符合VMCL验证试飞操纵特点的驾驶员模型,建立了能够真实模拟VMCL验证试飞过程及驾驶员操纵策略的某型四发螺旋桨飞机人机闭环仿真数学模型。仿真结果表明,该方法可以准确模拟VMCL验证试飞时发动机衰减特性、舵机动态特性、驾驶员反应延迟等因素的影响,以及飞机各运动参数的动态变化过程。