Spartan 201 coronal spectroscopy during the polar passes of ulysses

Spartan 201 is a shuttle deployed spacecraft that is scheduled to perform ultraviolet spectroscopy and white light polarimetry of the extended solar corona during two 40 hour missions to occur in September 1994 and August 1995. The spectroscopy is done with an ultraviolet coronal spectrometer which measures the intensity and spectral line profile of HI Ly up to heliocentric heights of 3.5 solar radii. It also measures the intensities of the OVI doublet at 1032 and 1037 Å and of Fe XII at 1242 Å. The HI Ly line profile measurements are used to determine the random velocity distribution of coronal protons along the line-of-sight. The absolute HI Ly intensities can be used together with electron densities from the white light coronagraph to estimate electron temperatures from hydrogen ionization balance calculations, and bulk outflow velocities from models of Doppler dimmed resonant scattering. Intensities of minor ion lines are used to determine coronal abundances and outflow velocities of O⁵⁺. Ultraviolet spectroscopy of extended coronal regions from the 11 April 1993 mission of Spartan 201 are discussed.     

Ultraviolet spectroscopy of the extended solar corona during the Spartan 201 mission

The instruments on the Spartan 201 spacecraft are an Ultraviolet Coronal Spectrometer and a White Light Coronagraph. Spartan 201 was deployed by the Space Shuttle on 11 April 1993 and observed the extended solar corona for about 40 hours. The Ultraviolet Coronal Spectrometer measured the intensity and spectral line profile of HI Ly and the intensities of OVI 103.2 and 103.7 nm. Observations were made at heliocentric heights between 1.39 and 3.5 R. Four coronal targets were observed, a helmet streamer at heliographic position angle 135°, the north and south polar coronal holes, and an active region above the west limb. Measurements of the HI Ly geocorona and the solar irradiance were also made. The instrument performed as expected. Straylight suppression, spectral focus, radiometric sensitivity and background levels all appear to be satisfactory. The uv observations are aimed at determining proton temperatures and outflow velocities of hydrogen, protons and oxygen ions. Preliminary results from the north polar coronal hole observations are discussed.     

低速风洞动态试验的高速并联机构设计及动力学分析

为模拟飞行器多自由度(DOF)风洞试验,设计并制造了一种用于低速风洞试验的高速并联六自由度机构,综合分析需求和机构的约束条件,确定机构的结构参数,并分析和总结了该机构的特点。使用ANSYS软件计算系统的固有频率,得到系统极限位置的振动响应。利用ADAMS软件对机构进行柔性动力学仿真,模拟机构在高速运动时紧急制动的动力特征,比较分析刚性和柔性制动的冲击载荷,总结出机构高速制动的特点,所分析结果在机构的设计和实际应用中具有重要的意义。实际运行表明:并联机构可实现单自由度和多自由度耦合运动,具有大工作空间(振幅可达30°/500mm)、高运动精度(达0.05°/0.5mm)和高速(达5m/s)等特点,并具有较高的运动性能,满足风洞试验要求。     

高速飞行姿态解算系统设计与实现

飞行事故分析需要完整记录飞机的飞行姿态,为此设计了一种基于FPGA的高速姿态解算系统,能够在线高速输出姿态信息,为飞行事故分析提供充足的参考数据。系统采用基于四元数的姿态算法,以克服欧拉法在90。具有奇异性的缺陷;用浮点数格式进行数据描述,并在FPGA内设计了浮点数四则运算硬件逻辑电路,以提高解算的精度;同时,在解算过程中充分发挥FPGA分布式、并行化的处理特点,通过并行流水设计及模块复用方法对系统的处理速度和资源消耗进行折中,使得系统在一块小规模FPGA芯片中达到0．38MHz的姿态输出频率。进行仿真数据测试及转台实验,对系统的解算精度及动静态性能进行了分析与评价。实验结果表明,系统性能良好,简单实用,具有较好的工程推广应用前景。     

On the Periodicity of High Speed Solar Wind Streams

In the paper we have investigated the periodicity of high speed solar wind (HSSW) streams using the technique of power spectrum analysis. The data for HSSW streams has been taken from the papers by Lindblad and Lundstedt (1981, 1983) and Lindblad et al. (1989) The power spectrum analysis of the daily HSSW streams events for the period 1964–1975 (solar cycle 20) shows peaks of 14, 7, 2.9 and 2.6 days, and daily HSSW events for the period 1976–1982 (solar cycle 21) shows peaks of 15.4, 7, 2.9 and 2.6 days. The HSSW events for period 1964–1982 (solar cycles 20-21) shows peaks of 15.4, 7, 3.7, 2.9 and 2.6 days. The common periods from above study are 7, 2.9 and 2.6 days. The 2.9, 2.6 days and other periods are folding frequency. The 7 days periodicity is close to the th of solar rotation which may be the time for energy build up for coronal holes to produce HSSW streams. This revised version was published online in August 2006 with corrections to the Cover Date.     

直升机悬停及低速飞行阶段轴间耦合试飞技术

从试飞员角度出发，分析了直升机轴间耦合现象产生的原因，讨论了ADS-33D规范中有关轴间耦合问题的要求，提出了武装直升机轴间耦合试飞方法、数据处理方法、试飞驾驶技术要点以及试验过程中应注意的事项，可供从事武装直升机飞行试验的技术人员和试飞员参考。     

Acceleration of the High Speed Solar Wind in Coronal Holes

We outline a theory for the origin and acceleration of the fast solar wind as a consequence of network microflares releasing a spectrum of high frequency Alfvén waves which heat (by cyclotron absorption) the corona close to the Sun. The significant features of our model of the fast wind are that the acceleration is rapid with the sonic point at around two solar radii, the proton temperatures are high (~ 5 million degrees) and the minor ions are correspondingly hotter, roughly in proportion to their mass. Moreover we argue that since the energy flux needed to power the quiet corona in closed field regions is about the same as that needed to drive the fast solar wind, and also because at deeper levels (< 2 × 10⁵ K) there is no great difference in the properties of supergranules and network in closed and open field regions, the heating process (i.e., dissipation of high frequency waves) must be the same in both cases. This revised version was published online in June 2006 with corrections to the Cover Date.     

直流低速风洞收缩段的数值模拟研究

采用商用软件FLUENT对双三次曲线和维辛斯基曲线这两种收缩段曲线进行了数值模拟,旨在通过仿真结果为低速风洞收缩段的设计选择一种较为合适的曲线。从流函数、静压、速度图中可以看见,收缩段曲线采用双三次曲线时各截面参数均匀,可以达到很好的收敛效果,通过本次数值模拟计算可为低速直流风洞的设计及优化提供了重要的依据。     

民用飞机进气道低速大迎角性能风洞实验和数值计算分析

为了研究民用飞机进气道在起飞低速大迎角状态下的流场特征和性能,对设计马赫数为0.785的进气道进行了风洞实验和数值计算,来流马赫数为0.2,迎角变化为0°～25°,流量系数为0.29～2.07.研究结果表明:在起飞工况条件下,进气道正常工作迎角可达到25°;在起飞单发失效工况条件下,进气道外罩上流动分离迎角在13°～1...     

低速增压风洞支架干扰的数值研究

对气动院FL-9低速增压风洞尾撑支架干扰进行数值计算.通过合理的拓扑结构,生成了YF-16模型的分区对接网格.计算对模型的典型安装状态进行研究,获得了全机气动特性和支架干扰量,探讨了此安装状态下弯刀对飞机气动力的干扰特性,并重点研究了Re数对干扰量的影响规律.     

Y7-200A飞机失速速度试飞

根据在确定Ｙ７－２００Ａ飞机失速速度中所遇到的困难,提出了确定Ｙ７－２００Ａ飞机失速速度的新方法。在对该机对发空中慢车功率状态推力为负进行了验证的基础上,对所有构形的失速速度飞均以双发空中慢车状态来完成。最后,给出了失速速度试飞结果。结果表明,该方法在试飞中是切实可行的,可用于同类型飞机的试飞验证。     

环翼机低速气动特性风洞实验研究

环翼机具有前、后翼,前翼后掠,后翼前掠,机翼在翼尖处连接,形成一个环状结构。为了解环翼的气动特性及环翼的几何参数对环翼机气动特性的影响,本文在低速风洞中对3种不同几何参数环翼飞机进行了纵向及横向测力实验,其中包括前、后翼几何参数改变对气动特性的影响。实验结果表明,与常规飞机相比,环翼机具有如下优点：诱导阻力小,失速特性好,操稳性能易于满足。实验得到的有价值结果,对环翼布局飞机的气动计算和合理设计具有重要意义。     

悬停及小速度前飞状态下旋翼对机身及平尾气动特性的影响

介绍了一副研究型旋翼 Ｚ９ 机身组合模型在 Ｃ Ａ Ｒ Ｄ Ｃ８ｍ ×６ｍ 低速风洞的试验概况,给出了悬停及小速度前飞时旋翼对机身气动特性的影响,着重讨论了水平尾翼对机身纵向气动特性的贡献。机身横截面上的不对称压力分布测量结果,揭示了旋翼在机身表面诱导的附加横侧向气动载荷的机理。     

无人直升机悬停及小速度飞行精确控制设计与仿真

采用姿态内回路和位置外回路的控制方法,设计无人直升机悬停及小速度飞行控制律,并进行仿真验证控制的精确性。     

Properties of Coronal Hole/Streamer Boundaries and Adjacent Regions as Observed by Spartan 201

The Spartan 201 flights from 1993 to 1995 provided us with observations in H I Lyman-α of several coronal hole/streamer boundaries and adjacent streamers during the declining phase of the current solar cycle: Analysis of the latitudinal dependence of the line intensities clearly shows that there is a boundary region at the coronal hole/streamer interface where the H I Lyman-α intensity reaches a minimum value. Similar results are also found in UVCS/SOHO observations. We also discuss differences in the coronal hole/streamer boundaries for different types of streamers and their changes over the three year period of Spartan 201 observations. This revised version was published online in June 2006 with corrections to the Cover Date.     

基于高速相机阵列的起飞着陆段航迹测量技术

针对基于GPS的飞机起降性能测试关键段轨迹细节信息描述不清晰、测量精度低的问题,提出一种利用高速相机阵列对飞机的起飞着陆运动过程进行接力拍摄,通过对各站点高速相机拍摄到的图像序列进行分析处理,得到飞机上标志点在图像坐标系中的坐标,利用近景数字摄影测量中三维直接线性变换(DLT)等算法,解算出飞机的位置及速度数据的方法.介绍了该方法涉及的数学模型及其推导过程,并利用坐标观测量数据进行解算,试验证明了该方法有效.     

载机投放外挂物低速风洞模拟技术

本文介绍在低速风洞中进行载机投放外挂风洞试验模拟原理,模型设计,试验方法和结果处理,并讨论载机行飞高度,飞行速度和飞行姿态角诸参数对外挂物安全投放及其下落轨迹的影响。     

低速大转矩电机冷却系统数值计算

在低速大转矩电机系列设计中,考虑到机座的通用性和外形尺寸的规范性,采用了轴向水路的水冷机座结构。通过对电机冷却系统的流体场计算,得到了电机的散热情况,耦合温度场计算,得到了电机冷却水和机座的温升,并通过对机座的模态分析得到了电机的固有振动频率。     

高功率低偏振度光纤陀螺光源技术

针对高精度光纤陀螺对ASE光源高功率、宽谱宽和低偏振度的应用需求,设计了双程后向ASE光源并进行了仿真和实验验证,研究了铒纤长度为4m、10m和19m的光源光谱特性,分析了泵浦功率、温度的变化对输出功率、平均波长及光谱宽度等参数的影响。结果表明,当铒纤长度为19m时,光源在驱动电流为110mA时的输出功率为4.055mW,光谱宽度为16.63nm,偏振度为1.925%,平均波长随电流的变化量为9.9×10-6/mA。同时,温度实验表明,铒纤长度为19m的光源平均波长随温度的变化量为5.9×10-6/℃。     

一种低速风洞大流量进气道试验系统研制

为了提高FL-8风洞进气道试验能力,结合该风洞特点,在不破坏原有进气道试验系统前提下,研制了一路大流量进气道试验系统,采用直线形式布置在风洞中心,引射混合气体扩压减速后排入风洞扩散段内。该系统可实现进气道流场模拟、性能测量、流量控制与测量。为了验证该系统性能,在FL-8风洞进行试验验证了引射器的引射能力,排气对风洞流场的影响以及流量的控制与测量精度。该系统测量精度高,流量测量精度达到0.3%以上引射能力强,排气对风洞流场影响小,可模拟单路流量2.8kg/s,较原FL-8进气道试验能力提高50%以上,并且与原FL-8进气道试验系统结合使用,可实现三路进气道同时模拟。