耦合时间精度对模拟飞行器自由运动特性的影响

将亚迭代技术引入流体动力学和刚体动力学方程的耦合求解,获得细长三角翼极限环运动的规律.探讨耦合时间精度对飞行器非定常运动特性的影响,细长三角冀的大迎角自由滚运动最终形成极限环振荡的周期性自维持运动,不同攻角自由滚振幅阶跃式的变化特点较好地吻合了自由滚试验的规律.对于多系统耦合问题,亚迭代耦合求解(耦合时间精度为二阶)对物理时间步长的依赖性不明显;而存在一阶时间滞后的解耦推进方法的数值结果强烈地依赖于物理时间步长选取,稍大的时间步长将导致非物理的数值结果.     

三角翼涡破裂的高精度数值模拟

采用5阶精度的加权紧致非线性格式(WCNS-E-5)数值模拟65°后掠角尖前缘三角翼的大攻角跨声速绕流流场,考察低耗散、高分辨率的WCNS-E-5格式对于三角翼涡破裂模拟的适用性,及激波旋涡干扰对涡破裂点位置的影响,重点研究三角翼大攻角旋涡破裂点的突然前移.通过求解任意坐标系下的非定常雷诺平均N-S方程,采用WCNS-E-5和SST两方程湍流模型,与试验结果和文献计算结果对比,表明既有高阶精度又能光滑捕捉激波的WCNS格式在模拟三角翼旋涡破裂方面具有一定优势,其数值结果与试验结果吻合较好,三角翼大攻角旋涡破裂点的突然前移是由于跨声速流场的激波旋涡干扰.     

基于数值模拟的飞行员高速气流吹袭损伤分析

研究飞行员高速气流吹袭的损伤机理,应用尺度适应模型对人椅系统外流场进行数值模拟.在马赫数为0.6,迎角为-90°~90°条件下的数值计算结果与风洞试验结果吻合较好.对不同马赫数、不同迎角的无防护状态下的人椅系统进行数值模拟,研究发现高速气流吹袭下飞行员面颈部、胸腹部、上臂内侧、小腿迎风侧压力较大;增大人椅系统的迎角可以改善飞行员身体各部分的受力情况.     

翼型前缘分离流动在等离子体激励器控制下的响应

将等离子体对中性气体的作用模型化为彻体力矢量,采用DES(Detached Eddy Simulation)和DDES(Delayed-Detached Eddy Simulation)方法,求解带彻体力源项的Navier-Stokes方程,研究NACA0015翼型16°迎角下,前缘分离流动在等离子体激励器控制下的响应过程.激励器工作后,DDES计算结果显示,分离流动经历一个渐近的再附过程;DES计算因发生网格诱导分离,得到了非定常的响应过程.     

边条翼后掠角对钝头细长旋成体非对称流动的影响

为探究大迎角时边条翼前缘后掠角对钝头细长旋成体导弹绕流特性的影响,开展了模型表面测压和粒子图像测速的风洞实验,研究了亚临界Reynolds数Re=150000、迎角α=50°条件下不同前缘后掠角固定边条翼的钝头细长旋成体非对称绕流特性.结果表明,在边条翼上游区,后掠角增大使边条涡涡位更靠近前体物面且对称性更好,导致前体...     

三维不可压N-S方程的多重网格求解

应用全近似存储(Full Approximation Storage,FAS)多重网格法和人工压缩性方法求解了三维不可压Navi-er-Stokes方程.在解粗网格差分方程时,对Neumann边界条件采用增量形式进行更新,离散方程用对角化形式的近似隐式因子分解格式求解,其中空间无粘项分别用MUSCL格式和对称TVD格式进行离散.对90°弯曲的方截面管道流动和4:1椭球体层流绕流的数值模拟表明,多重网格的计算时间比单重网格节省一半以上,且无限制函数的MUSCL格式比TVD格式对流动结构有更好的分辨能力.     

基于雷诺应力模型的高精度分离涡模拟方法

基于Speziale-Sarkar-Gatski/Launder-Reece-Rodi(SSG/LRR)-ω雷诺应力模型发展了一类分离涡模拟方法,结合高精度加权紧致非线性格式在典型翼型及三角翼算例中进行了验证,并和传统基于线性涡粘模型的分离涡模拟方法进行了对比.结果表明:基于SSG/LRR-ω模型的分离涡模拟方法,提高了原雷诺应力模型对非定常分离湍流的模拟能力;同时相比于传统基于线性涡粘模型的分离涡模拟方法,尤其是在翼型最大升力迎角和三角翼涡破裂迎角附近,该方法在平均气动力预测的准确度、分离湍流模拟的精细度等方面更加优秀.     

双三角翼非定常俯仰运动实验与数值模拟

文章针对双三角翼大振幅正弦俯仰运动过程中的非定常载荷和流动特性开展了实验与数值模拟研究,并与相同主翼后掠角的单三角翼进行了对比.实验研究在低速回流式水槽中开展,所采用的实验模型为边条后掠角为75°,主翼后掠角为50°的双三角翼全模,俯仰运动的旋转轴位于主翼弦长的2/3处,振幅为0~60°,运动的缩减频率k=0.03,0.06,0.12,0.24,0.48.实验Reynolds数以主翼弦长为参考Re=1.69×104.在水槽的测力实验中,发现非定常流动力的迟滞现象,并且随着非定常运动缩减频率的增大,流动的迟滞效应也随之增大.与相同主翼后掠角的单三角翼相比,双三角翼的迟滞环在低缩减频率下更小,但随着缩减频率的增大,这种差距逐渐减小.在数值模拟研究中,采用DDES湍流模型对俯仰双三角翼的流场进行了数值模拟.流场结果表明,在较低的缩减频率下,主翼吸力面的前缘涡是影响气动力的主要因素,非定常流动力的迟滞效应主要与前缘涡在上仰过程中的延迟破裂和下俯过程中的延迟恢复有关;在较高的缩减频率下,机翼前缘涡对气动力的影响减小,由机翼俯仰角速度而产生的环量力成为了气动力的主导因素,因此在较高缩减频率下,单三角翼与双三角翼的升力特性趋于一致.      

用二维时域有限差分法计算机翼雷达散射截面

应用二维时域有限差分(FDTD)程序计算二维翼型NACA0012和金属方柱的双站雷达散射截面,与国内外文献上的结果进行比较,证明该程序的有效性.而后计算二维不同形状机翼的双站雷达散射截面(RCS)和不同后掠角时后掠翼和三角翼的双站RCS,得出不同形状机翼有不同的RCS分布;改变后掠角的大小可以改变机翼的RCS分布.因此,根据设计要求,可以通过选用不同机翼形状或不同大小的后掠角,使飞行器达到RCS减缩.     

基于SNGR方法的后缘噪声数值模拟

采用随机噪声产生和传播(SNGR)方法对后缘噪声进行数值模拟.SNGR方法结合随机方法和计算流体力学,耗费较少的计算资源就可以预测噪声水平.数值模拟时采用有限体积法求解雷诺平均Navier-Stokes(RANS)方程;采用有限差分法求解声学扰动方程,数值格式采用色散关系保持(DRP)格式,远场边界条件采用无反射边界条件.以二维平板和NACA0012翼型为例,编制程序,与参考结果对比表明,程序可以预测后缘噪声.     

弹体尾部轴对称干扰流场数值模拟

绕弹体的超声速气流与发动机喷流相互作用,在尾部形成复杂的干扰流场。本文用有限差分法求解全N-S方程,对这一复杂流场进行了数值模拟,得到了实验观察到的各种流场结构及其随喷口压力比的变化规律。外流M_∞=1.94,R_e∞=2.2×10⁵,喷流M_j=3.0,喷口压力比p_j/p_∞分别为1.03,0.527,0.15三种。差分算法为一种改进的Beam-Warming格式。计算底部压力和激波在喷流中心的反射位置与实验数据进行了比较,吻合较好。     

Mo-SiO2-C3H6催化反应体系的ESR动态表征

文章考察了Mo-SiO₂催化剂体系在丙烯歧化反应过程中的动态ESR波谱,发现在催化歧化反应过程中有两种Mo⁵⁺顺磁中心,一种为扰动八面体配位,g_||=1.89,g_⊥=1.94;另一种为扰动四棱锥配位,g_||=1.86,g_⊥=1.95。测得同位素^95,97Mo⁵⁺的各向异性超精细耦合常数A_||=90.3×10^-4cm^-1,A_⊥=44.8×10^-4cm^-1;观测到反应产生的积炭信号,g≈2.0O₂;氧阴离子自由基信号g₁=2.018,g₂=2.011,g₃=2.005。用LCAO-MO理论对上述Mo⁵⁺的ESR波谱进行计算,求得分子轨道系数,发现并总结出△g_||/△g_⊥与△g成直线关系,并建议用△g_||/△g_⊥=4(△E(B₂→E))/(△E(B₂→B₁)(β₁/ε)²之比值作为衡量C_4v扰动程度的尺度。     

Etching mask optimization of InAs/GaSb superlattice mid-wavelength infared 640×512 focal plane array

In this paper we focused on the mask technology of inductively coupled plasma(ICP) etching for the mesa fabrication of infrared focal plane arrays(FPA).By using the SiO_2 mask,the mesa has higher graphics transfer accuracy and creates less micro-ripples in sidewalls.Comparing the IV characterization of detectors by using two different masks,the detector using the SiO_2 hard mask has the R_0A of 9.7×10~6 Ω·cm~2,while the detector using the photoresist mask has the R_0A of3.2 × 10~2 Ω·cm~2 in 77 K.After that we focused on the method of removing the remaining SiO_2 after mesa etching.The dry ICP etching and chemical buffer oxide etcher(BOE) based on HF and NH4 F are used in this part.Detectors using BOE only have closer R_0A to that using the combining method,but it leads to gaps on mesas because of the corrosion on AlSb layer by BOE.We finally choose the combining method and fabricated the 640×512 FPA.The FPA with cutoff wavelength of 4.8 μm has the average R_0A of 6.13 × 10~9 Ω·cm~2 and the average detectivity of 4.51 × 10~9 cm·Hz~(1/2).W~(-1)at 77 K.The FPA has good uniformity with the bad dots rate of 1.21%and the noise equivalent temperature difference(NEDT) of 22.9 mK operating at 77 K.     

Measurement of the slope parameter for the neutral pion spectrum in KL → πππ decay

The π⁰ spectrum in the K_L⁰ → 3π decay was measured using a wire chambers magnetic spectrometer. In the usual approximation, the matrix element can be expressed as: M² ≈ 1 + 2a₀(M_K/M_π²)(2T_π⁰−T_π⁰max) + a₁(M_K²/M_π⁴)(2T_π⁰−T_π⁰max)². We obtained a₀ = −0.282 ± 0.011 and a₁ consistent with zero.     

非晶锂离子导体B2O3-Li2O-LiCl一Al2O3中VO2+的电子自旋共振

两种非晶锂离子导体B₂O₃-0.7Li₂O-0.7LiCl-xAl₂O₃-0.1V₂O₅(x=0.05和0.15)的电子自旋共振谱研究表明:(i)ESR线型是高斯型,证实V₂O₅添加量适当;(ii)超精细结构来源于VO²⁺络离子,具有四角对称性,属C_4v群。越精细耦合张量的平行分量平均值A_//=0.0175cm^-1,垂直分量A_⊥=0.0063cm^-1。由g_//(g_⊥)求出其基态²B_2g与第一激发态²E_g的能级间距△₁=2.46×10⁴ cm^-1,基态与第二激发态²B_1g的能级间距△₂=3.03×10⁴ cm^-1;(iii)变温实验证实:Al₂O₃组分较少(x=0.05)的非晶ESR强度比x=0.15的非晶高3倍至2倍,而Al₂O₃组分越多则ESR强度随温升下降越小。     

H$lt;sub$gt;2$lt;/sub$gt;$lt;sup$gt;+$lt;/sup$gt;在强激光场中的解离及其量子调控的理论研究

利用非波恩-奥本海默近似的三维含时量子波包法,理论研究了氢分子离子在强激光场中的解离动力学.通过分析H₂⁺在不同的初始振动态（ν=0–9）和激光场强度下的解离核动能谱,得到了H₂⁺的光解离机理及其随激光场的变化规律.研究结果表明：当激光场的强度I₁=5.0×10¹³ W/cm²时,分子的解离来源于高振动态ν=5–9,其解离机理主要是通过键软化、键硬化和阈下解离过程.当激光场的强度I₂=1.0×10¹⁴ W/cm² 时,H₂⁺在低振动态ν=3–4上的阈上解离起主导作用,而高振动态的键软化、键硬化和阈下解离所占的比重明显地下降了.研究结果为后续的量子调控的实验研究提供了科学的理论预测和指导. 关键词： 光解离 氢分子离子 含时波包法 核动能谱     

N=2 6-dimensional supersymmetric E6 breaking

We study the N=2 supersymmetric E₆ models on the 6-dimensional space–time where the supersymmetry and gauge symmetry can be broken by the discrete symmetry. On the space–time M⁴×S¹/(Z₂×Z₂′)×S¹/(Z₂×Z₂′), for the zero modes, we obtain the 4-dimensional N=1 supersymmetric models with gauge groups SU(3)×SU(2)×SU(2)×U(1)², SU(4)×SU(2)×SU(2)×U(1), and SU(3)×SU(2)×U(1)³ with one extra pair of Higgs doublets from the vector multiplet. In addition, considering that the extra space manifold is the annulus A² and disc D², we list all the constraints on constructing the 4-dimensional N=1 supersymmetric SU(3)×SU(2)×U(1)³ models for the zero modes, and give the simplest model with Z₉ symmetry. We also comment on the extra gauge symmetry breaking and its generalization.     

Existence and uniqueness of solutions to superdifferential equations

We state and prove the theorem of existence and uniqueness of solutions to ordinary superdifferential equations on supermanifolds. It is shown that any supervector field, X = X₀ + X₁, has a unique integral flow, Г: ^1¦1 x (M, A_M) → (M, A_M), satisfying a given initial condition. A necessary and sufficient condition for this integral flow to yield an ^1¦1-action is obtained: the homogeneous components, X₀, and, X₁, of the given field must define a Lie superalgebra of dimension (1, 1). The supergroup structure on ^1¦1, however, has to be specified: there are three non-isomorphic Lie supergroup structures on ^1¦1, all of which have addition as the group operation in the underlying Lie group . On the other extreme, even if X₀, and X₁ do not close to form a Lie superalgebra, the integral flow of X is uniquely determined and is independent of the Lie supergroup structure imposed on ^1¦1. This fact makes it possible to establish an unambiguous relationship between the algebraic Lie derivative of supergeometric objects (e.g., superforms), and its geometrical definition in terms of integral flows. It is shown by means of examples that if a supergroup structure in ^1¦1 is fixed, some flows obtained from left-invariant supervector fields on Lie supergroups may fail to define an ^1¦1-action of the chosen structure. Finally, necessary and sufficient conditions for the integral flows of two supervector fields to commute are given.     

Magnetic properties and composition range of non-stoichiometric m-type hexagonal ferrites prepared by ion exchange

Single crystals of Ba, Sr M-type hexagonal ferrites were prepared by ion exchange in Ba, Sr containing molten salts from single crystals of β″ -ferrites. A fast diffusion of the divalent Ba²⁺, Sr²⁺ is observed leading to a non-stoichiometric M-type ferrite with chemical formula: Ba_1+xFe_10.5Co_0.25O_17+x (0 ≤ x ≤ 0.25). x depending on the exchange reaction time. Saturation magnetization ranges from 19 to 64 emu/g depending on exchange conditions. The Curie temperature is (470 ± 5)°C. An easy axis direction (M_s c) has been determined in all cases. The observed anisotropy is considerably lower than that of M ferrite. The calculated anisotropy constants are, in 10⁶ erg/cm³, K₁ = 0.8 and K₂ = 1.0 at room temperature.     

Hamiltonian circle actions on symplectic manifolds and the signature

Let M be a symplectic manifold with a Hamiltonian circle action with isolated fixed points. We prove that σ (M) = b₀(M) − b₂(M) + b₄(M) − b₆(M) + … where σ (M) is the signature of M and b_i(M) is the ith Betti number of M.