Model simulations of fuel sulfur conversion efficiencies in an aircraft engine: Dependence on reaction rate constants and initial species mixing ratios

The fuel sulfur conversion efficiency ε behind the combustor of a JT9D-7A aircraft engine in flight has been simulated using an extended exhaust plume chemistry model. The model simulations start in the high-temperature intra-engine regime behind the combustor. The simulations show that the sulfur conversion efficiency is sensitively dependent on model assumptions like reaction rate constants and initial mixing ratios. Sensitivity studies to demonstrate the effect of the uncertainties and variabilities of these parameters on ε are presented. Among the rate constants k, the uncertainty of the reaction rate constant for SO₂ + OH + M → HSO₃ + M has the greatest effect on ε: The uncertainty of k(SO₂ + OH) results in an uncertainty range of 1.1% <ε<6.2% for our simulation scenario, with a most probable value around 3.8%. The effect of the reaction SO₂ + O + M → SO₃ + M on ε is very small if the initial mixing ratio of O is smaller than that of OH. Among the initial mixing ratios, the variation of the initial OH mixing ratio OH₀ has the greatest effect on ε. For our simulation scenario, the uncertainty range of 5.7 ppmv < OH₀ < 14.7 ppmv (inferred from measurements) leads to an uncertainty range of 2.7% <ε<5.0%.     

Regularities between kinematic and aerodynamic characteristics of flexible membrane wing

The kinematic characteristics of flexible membrane wing have vital influences on its aerodynamic characteristics. To deeply explore the regularities between them, time-resolved aerodynamic forces and deformations at different aeroelastic parameters and angles of attack(α) were measured synchronously by wind tunnel experiments. The membrane motion can be mainly divided into two states at α > 0° with various lift-enhancement regularities: Deformed-Steady State(DSS)at pre-stall, and Dynamic Bala...     

Satellite Measurements of Middle Atmospheric Impacts by Solar Proton Events in Solar Cycle 23

Solar cycle 23 was extremely active with seven of the largest twelve solar proton events (SPEs) in the past forty years recorded. These events caused significant polar middle atmospheric changes that were observed by a number of satellites. The highly energetic protons produced ionizations, excitations, dissociations, and dissociative ionizations of the background constituents in the polar cap regions (>60 degrees geomagnetic latitude), which led to the production of HO_x (H, OH, HO₂) and NO_y (N, NO, NO₂, NO₃, N₂O₅, HNO₃, HO₂NO₂, BrONO₂, ClONO₂). The HO_x increases led to short-lived ozone decreases in the polar mesosphere and upper stratosphere due to the short lifetimes of the HO_x constituents. Polar middle mesospheric ozone decreases greater than 50 % were observed and computed to last for hours to days due to the enhanced HO_x. The NO_y increases led to long-lived polar stratospheric ozone changes because of the long lifetime of the NO_y family in this region. Upper stratospheric ozone decreases of >10 % were computed to last for several months past the solar events in the winter polar regions because of the enhanced NO_y.     

Time-implicit simulation of particle-fluid systems

This paper presents one-dimensional particle-fluid hybrid simulations in which the strongly collisional components of the plasma (e.g., ions and thermal electrons with ν_cfΔt > 1) are treated as fluids and the weakly collisional components (e.g., energetic electrons with ν_cpΔt ≪ 1) are treated as particles. Here ν_cf denotes the fluid ion and electron collision frequencies, ν_cp is the energetic particle collision frequency and Δt is the time step. Collisions between particle and fluid components are treated by a Monte-Carlo method and mass transfers between the particle and fluid electron components are governed by collision frequency thresholds. The field is computed implicitly to allow time steps with Ω_p Δt > 1 (Ω_p: plasma frequency).     

弧齿锥齿轮的齿距误差对传动性能的影响研究

采用齿轮啮合仿真和承载啮合仿真技术 ,对重合度达到 2 .0的航空弧齿锥齿轮的齿距误差的影响进行了研究。首先定义了航空弧齿锥齿轮相对齿距误差 ,选取了量级 ,研究了这一误差对齿轮实际重合度、传动误差、齿面载荷分布和齿间载荷分配的影响。进一步又分析了在一定齿距误差下载荷变化的影响以及固定载荷下误差变化的影响 ,为高重合度航空弧齿锥齿轮的应用提供了依据     

加力燃烧室用齿冠状混合器的数值研究与验证

基于CFD(computational fluid dynamics)技术,分别采用有限速率/涡耗散(finite-rate/eddy-dissipation)、涡耗散(eddy-dissipation)和涡耗散概念(EDC)燃烧模型,对一种曲面齿冠状混合器作用下的加力燃烧室进行数值计算.计算结果表明:曲面齿冠状混合器下游产生明显的流向涡对,流向涡的存在可以增强内外涵冷热气流掺混;与直面齿冠状混合器相比,曲面齿冠状混合器下游流向涡强度大于直面齿冠状混合器,其混合效率高于直面齿冠状混合器;加力燃烧室内氧气和二氧化碳质量分数分布结构表明了涡耗散模型的计算更为合理;计算结果可为加力燃烧室混合器选型和燃烧数值模拟提供依据.      

Constraining Fundamental Constants of Physics with Quasar Absorption Line Systems

We summarize the attempts by our group and others to derive constraints on variations of fundamental constants over cosmic time using quasar absorption lines. Most upper limits reside in the range 0.5–1.5×10^?5 at the 3σ level over a redshift range of approximately 0.5–2.5 for the fine-structure constant, α, the proton-to-electron mass ratio, μ and a combination of the proton gyromagnetic factor and the two previous constants, g _p(α ²/μ) ^ν , for only one claimed variation of α. It is therefore very important to perform new measurements to improve the sensitivity of the numerous methods to at least <0.1×10^?5 which should be possible in the next few years. Future instrumentations on ELTs in the optical and/or ALMA, EVLA and SKA pathfinders in the radio will undoutedly boost this field by allowing to reach much better signal-to-noise ratios at higher spectral resolution and to perform measurements on molecules in the ISM of high redshift galaxies.     

The Effects of Transverse Magnetic Field and Density Variations on the Particle Energy Spectra in a Reconnecting 3D Current Sheet

Electron and proton acceleration by a super-Dreicer electric field is further investigated in a non-neutral reconnecting current sheet (RCS) with a variable plasma density. The tangential B _z and transverse magnetic field components B _x are assumed to vary with the distances x and z from the X nullpoint linearly and exponentially, respectively; the longitudinal component (a ‘guiding field’) is accepted constant. Particles are found to gain a bulk of their energy in a thin region close to the X nullpoint where the RCS density increases with z exponentially with the index λ and the tangential magnetic field B _x also increases with z exponentially with the index α. For the RCS with a constant density (λ = 0), the variations of the tangential magnetic field lead to particle power-law energy spectra with the spectral indices γ₁ being dependent on the exponent α as: for protons and for electrons in a strong guiding field (β > 10⁻²) and for electrons in a moderate or weak guiding field (β > 10⁻⁴). For the RCS with an exponential density increase in the vicinity of the X nullpoint (λ≥ 0) there is a further increase of the resulting spectral indices γ that depends on the density exponent index λ as for protons and for electrons in weaker guiding fields and as for electrons in stronger guiding fields. These dependencies can explain a wide variety (1.5–10) of particle spectral indices observed in solar flares by the variations of a magnetic field topology and physical conditions in a reconnecting region. This can be used as a diagnostic tool for the investigation of the RCS dynamics from the accelerated particle spectra found from hard X-ray and microwave emission.     

Rosina – Rosetta Orbiter Spectrometer for Ion and Neutral Analysis

The Rosetta Orbiter Spectrometer for Ion and Neutral Analysis (ROSINA) will answer important questions posed by the mission’s main objectives. After Giotto, this will be the first time the volatile part of a comet will be analyzed in situ. This is a very important investigation, as comets, in contrast to meteorites, have maintained most of the volatiles of the solar nebula. To accomplish the very demanding objectives through all the different phases of the comet’s activity, ROSINA has unprecedented capabilities including very wide mass range (1 to >300 amu), very high mass resolution (m/Δ m > 3000, i.e. the ability to resolve CO from N₂ and ¹³C from ¹²CH), very wide dynamic range and high sensitivity, as well as the ability to determine cometary gas velocities, and temperature. ROSINA consists of two mass spectrometers for neutrals and primary ions with complementary capabilities and a pressure sensor. To ensure that absolute gas densities can be determined, each mass spectrometer carries a reservoir of a calibrated gas mixture allowing in-flight calibration. Furthermore, identical flight-spares of all three sensors will serve for detailed analysis of all relevant parameters, in particular the sensitivities for complex organic molecules and their fragmentation patterns in our electron bombardment ion sources.     

The Hydrogen Exospheric Density Profile Measured with ASPERA-3/NPD

We have evaluated the Lyman-α limb emission from the exospheric hydrogen of Mars measured by the neutral particle detector of the ASPERA-3 instrument on Mars Express in 2004 at low solar activity (solar activity index = 42, F_10.7=100). We derive estimates for the hydrogen exobase density, n _H = 10¹⁰ m^?3, and for the apparent temperature, T > 600 K. We conclude that the limb emission measurement is dominated by a hydrogen component that is considerably hotter than the bulk temperature at the exobase. The derived values for the exosphere density and temperature are compared with similar measurements done by the Mariner space probes in the 1969. The values found with Mars Express and Mariner data are brought in a broader context of exosphere models including the possibility of having two hydrogen components in the Martian exosphere. The present observation of the Martian hydrogen exosphere is the first one at high altitudes during low solar activity, and shows that for low solar activity exospheric densities are not higher than for high solar activity.     

基于承载传动误差幅值最小的斜齿轮齿面修形优化设计

为了减小振动与噪声,提出了以承载传动误差幅值最小为优化目标的修形齿面设计方法:通过两段曲线与一段直线分别设计齿廓、齿向、三维修形(齿廓与齿向修形的叠加)修形曲线,通过三次B样条拟合了相应的修形曲面,与理论齿面叠加构造了斜齿轮修形齿面,推导了其法矢,将斜齿轮修形技术与承载接触分析技术结合起来,采用遗传算法对修形曲线参数进行优化,编制了一套齿面修形优化分析程序,能对修形后的斜齿轮副进行齿面接触分析(TCA)、承载接触分析(LTCA).结果表明:无修形齿轮副的传动误差幅值随载荷增加而增大,修形后随载荷的增加重合度逐渐增大,幅值会产生波动,然后保持稳定,为斜齿轮修形齿面优化设计提供了新的方法.      

Non-linear resonant excitation of whistler mode waves in the Earth's ionosphere

We examine the resonant non-linear interaction in the Earth's ionosphere of two powerful high frequency radio beams with frequencies f ₁ and f ₂ (both larger than the plasma frequency at F2_max) and wave numbers k ₁ and k ₂ such that a whistler mode wave can be excited with a frequency f ₃ = f ₁ — f ₂ and a wave number k ₃ = k ₁ – k ₂. The feasibility of an effective ground based installation, sited at low latitudes, is discussed and the field strength of the wave emerging from a 10 km wide ionospheric region illuminated by the beams is evaluated for a range of transmitted frequencies, beam orientations and plasma frequencies in the interaction region. It is suggested that the longitude dependence of the enhancement of VLF noise bands detected by the Ariel 3 satellite may be due to a non-linear interaction of this type between any two or more medium wavelength signals from areas where there is a high concentration of commercial broadcasting stations, such as the NE region of the U.S.A.     

Competing effects of surface catalysis and ablation in hypersonic reentry aerothermodynamic environment

Under hypersonic flow conditions, the complicated gas-graphene interactions including surface catalysis and surface ablation would occur concurrently and intervene together with the thermodynamic response induced by spacecraft reentry. In this work, the competing effects of surface heterogeneous catalytic recombination and ablation characteristics at elevated temperatures are investigated using the Reactive Molecular Dynamics(RMD) simulation method. A GasSurface Interaction(GSI) model is establi...     

Characterization and Calibration of the CheMin Mineralogical Instrument on Mars Science Laboratory

A principal goal of the Mars Science Laboratory (MSL) rover Curiosity is to identify and characterize past habitable environments on Mars. Determination of the mineralogical and chemical composition of Martian rocks and soils constrains their formation and alteration pathways, providing information on climate and habitability through time. The CheMin X-ray diffraction (XRD) and X-ray fluorescence (XRF) instrument on MSL will return accurate mineralogical identifications and quantitative phase abundances for scooped soil samples and drilled rock powders collected at Gale Crater during Curiosity’s 1-Mars-year nominal mission. The instrument has a Co X-ray source and a cooled charge-coupled device (CCD) detector arranged in transmission geometry with the sample. CheMin’s angular range of 5^° to 50^° 2θ with <0.35^° 2θ resolution is sufficient to identify and quantify virtually all minerals. CheMin’s XRF requirement was descoped for technical and budgetary reasons. However, X-ray energy discrimination is still required to separate Co?Kα from Co?Kβ and Fe?Kα photons. The X-ray energy-dispersive histograms (EDH) returned along with XRD for instrument evaluation should be useful in identifying elements Z>13 that are contained in the sample. The CheMin XRD is equipped with internal chemical and mineralogical standards and 27 reusable sample cells with either Mylar^? or Kapton^? windows to accommodate acidic-to-basic environmental conditions. The CheMin flight model (FM) instrument will be calibrated utilizing analyses of common samples against a demonstration-model (DM) instrument and CheMin-like laboratory instruments. The samples include phyllosilicate and sulfate minerals that are expected at Gale crater on the basis of remote sensing observations.     

Physical and ballistic characterization of AlH3-based space propellants

Experimental and numerical analyses of laboratory-type composite solid rocket propellants based on α-AlH₃ are presented. Chemical and physical properties of this innovative energetic ingredient are discussed, ballistic properties experimentally evaluated, and flame structure compared with the corresponding aluminized propellants. Numerical 2D and 3D simulations of the subsequent two-phase flow in supersonic nozzles are reported. The obtained results overall disclose a competitive performance of α-alane-based propellants with respect to aluminized propellants and encourage its use in space applications.     

基于能量等效的直齿锥齿轮时变啮合刚度计算

针对直齿圆锥齿轮啮合刚度的计算问题,从微元思想出发,将变截面齿廓划分为若干等截面微段齿段,基于能量等效建立微段齿段啮合刚度计算模型,并利用积分方法获得单齿啮合刚度。此外,基于力平衡和变形协调条件进一步提出了齿轮时变啮合刚度计算模型,同时根据几何关系导出了相应传动误差计算式。利用有限元分析对解析计算模型进行了验证,并分析了误差来源。结果表明:利用该模型不仅能够将直齿锥齿轮啮合刚度计算精度保证在2%以内,还达到了快速求解的目的。      

有限元法在标准直齿圆柱齿轮齿弯曲疲劳强度计算中的应用

本文利用有限元法计算了标准直齿圆柱齿轮轮齿应力，得出其分布规律以及危险截面应力最大值。与传统计算结果相比较，其结果更为准确，为轮齿弯曲疲劳强度计算提供了一种简洁、精确的计算方法。     

直通篦齿蜂窝封严结构的风阻特性试验

试验研究了直通直齿和直通斜齿与蜂窝衬套和光滑衬套4种组合的三齿两腔封严结构的风阻特性,得到了风阻特性随转速、压比、衬套和齿形结构的变化规律.结果表明:4种组合封严结构在低转速时风阻生热基本都可以忽略,转速在3000r/min到6000r/min之间变化时风阻生热引起的流体总温升随转速增大;采用光滑衬套时,泄漏流体流至首级齿腔处的总温升占进出口总温升比例维持在45%以上,而蜂窝衬套对气流黏滞作用大,低压比时首级齿腔总温升占进出口总温升的比例仅有20%左右,继续增加压比,首级齿腔处的总温升比例由20%增加到50%左右后保持不变;相同衬套时,斜齿比直齿具有较长的齿表面曲线长度,从而具有较高的风阻生热.      

Instability characteristics of a co-rotating wingtip vortex pair based on bi-global linear stability analysis

The Stereo Particle Image Velocimetry (SPIV) technology is applied to measure the wingtip vortices generated by the up-down symmetrical split winglet. Then, the temporal bi-global Linear Stability Analysis (bi-global LSA) is performed on this nearly equal-strength co-rotating vortex pair, which is composed of an upper vortex (vortex-u) and a down vortex (vortex-d). The results show that the instability eigenvalue spectrum illustrated by (ω_r, ω_i) contains two types of branches: discrete branch and continuous branch. The discrete branch contains the primary branches of vortex-u and vortex-d, the secondary branch of vortex-d and coupled branch, of which all of the eigenvalues are located in the unstable half-plane of ω_i > 0, indicating that the wingtip vortex pair is temporally unstable. By contrast, the eigenvalues of the continuous branch are concentrated on the half-plane of ω_i < 0 and the perturbation modes correspond to the freestream perturbation. In the primary branches of vortex-u and vortex-d, Mode P_u and Mode P_d are the primary perturbation modes, which exhibit the structures enclosed with azimuthal wavenumber m and radial wavenumber n, respectively. Besides, the results of stability curves for vortex-u and vortex-d demonstrate that the instability growth rates of vortex-u are larger than those of vortex-d, and the perturbation energy of Mode P_u is also larger than that of Mode P_d. Moreover, the perturbation energy of Mode P_u is up to 0.02650 and accounts for 33.56% percent in the corresponding branch, thereby indicating that the instability development of wingtip vortex is dominated by Mode P_u. By further investigating the topological structures of Mode P_u and Mode P_d with streamwise wavenumbers, the most unstable perturbation mode with a large azimuthal wavenumber of m = 5–6 is identified, which imposes on the entire core region of vortex-u. This large azimuthal wavenumber perturbation mode can suggest the potential physical-based flow control strategy by manipulating it.