飞机百年发展与空气动力学

飞机的发明是人类历史的一个重大转折点，飞机改变了人类社会的面貌。它使交通运输和商业往来方式发生了革命；它使战争模式发生了根本性变化；它是促进科技进步的动力；它是人类太空飞行的起点，航空与飞机将永远都是人类历史上最伟大的成就之一，回顾了飞机百年发展的基本情况和取得的主要成就，着重指出空气动力学对于飞机发展所起到的重要作用，并对未来飞机发展进行了展望。     

Three polymorphs of 3‐(3‐phenyl‐1H‐1,2,4‐triazol‐5‐yl)‐2H‐1‐benzopyran‐2‐one formed from different solvents

The polymorphic study of 3‐(3‐phenyl‐1H‐1,2,4‐triazol‐5‐yl)‐2H‐1‐benzopyran‐2‐one, C₁₇H₁₁N₃O₂, was performed due to its potential biological activity and revealed three polymorphic modifications in the triclinic space group P, the monoclinic space group P2₁ and the orthorhombic space group Pbca. These polymorphs have a one‐column layered type of crystal organization. The strongest interactions between the molecules of the studied structures is stacking between π‐systems, while N—H…N and C—H…O hydrogen bonds link stacked columns forming layers as a secondary basic structural motif. C—H…π hydrogen bonds were observed between neighbouring layers and their role is the least significant in the formation of the crystal structure. Packing differences between the polymorphic modifications are minor and can be identified only using an analysis based on a comparison of the pairwise interaction energies.     

航空器供油问题中完全逆序类中的多项式时间可解类

航空器供油问题是一类非线性组合优化问题,其目标函数为分式形式,该问题目前不存在多项式时间算法,也未被证明是NP完全问题。一般可以用置换来刻画n架飞机的一个供油顺序。该问题中有一类实例被称为“完全逆序类”,“完全逆序类”用动态规划算法求解计算时间为O(n2ⁿ),具有指数时间复杂度。本文通过对该“完全逆序类”问题做进一步分析,发现在“完全逆序类”中也存在着多项式时间可解的情况。定理1研究一类一次可解的情况,若问题满足定理1的条件,则求解一次即可找到其最优解;定理2研究一类多项式时间可解的情况,当问题满足定理2的条件时,其最优解可在多项式时间内获得。     

联邦滤波在飞机组合导航中的应用

研究了中等精度捷联惯导系统(SINS),大气数据系统(ADS)和塔康系统(TACAN)构成的机载组合导航系统.在分析SINS、ADS、TACAN各自特点的基础上,提出了SISN/ADS/TACAN组合导航系统的联邦滤波方案,并建立了相应的组合导航系统的数学模型.以一条典型的飞行轨迹进行了全航线的仿真研究,仿真结果为:基于联邦滤波的SINS/ADS/TACAN组合导航系统的位置精度约为70 m(CEP),速度精度约为0.75 m/s(1),航向精度为约为 (1)和姿态精度约为 (1),由此可见基于联邦滤波的SINS/ADS/TACAN组合导航系统可以充分利用各机载导航子系统信息,满足飞机导航定位的精度要求.     

一飞机发动机动力特性分析

确定计算模型时，发动机定子按实际刚度，采用NASTRAN70．0程序对发动机整机进行了动力分析，分析结果与试验进行了比较，吻合度优于美国GE公司计算结果。作者认为造成偏磨故障的原因是弹性环压死，使压气机转子与定子反向平动的第六阶临界转速上升到接近放气阀门关闭时转速所致。根据动力响应计算结果，装配工艺采取措施后，克服了此偏磨故障。     

Concomitant Polymorphism in an Organic Solid: Molecular and Crystal Structure and Intra- and Intermolecular Potential Contributions to tert-Butyl and Methyl Group Rotation

We investigate the relationship between structure (crystal and molecular) and tert-butyl and methyl group dynamics in 2-(tert-butyl)-9-(4-(tert-butyl)phenyl)anthracene. Powder and single-crystal X-ray diffraction, taken together, show that different polycrystalline samples recrystallized from different solvents have different amounts of at least four polymorphs (crystallites having different crystal structures), of which we have identified three by single crystal X-ray diffraction. The molecules in the asymmetric units of the different crystal structures differ by the dihedral angle the tert-butylphenyl group makes with the anthracene moiety. Ab initio electronic structure calculations on the isolated molecule show that very little intramolecular energy is required to change this angle over a range of about 60° which is probably the origin of the concomitant polymorphism (crystals of more than one polymorph in a polycrystalline sample). Solid state ¹H nuclear magnetic resonance (NMR) spin-lattice relaxation experiments support the powder and single-crystal X-ray results and provide average NMR activation energies (closely related to rotational barriers) for the rotation of the tert-butyl groups and their constituent methyl groups. These barriers have both an intramolecular and an intermolecular component. The latter is sensitive to the crystal structure. The intramolecular components of the rotational barriers of the two tert-butyl groups in the isolated molecule are investigated with ab initio electronic structure calculations.     

飞机姿态测量误差对测量船校飞精度的影响

通过对校飞数据处理方法及实测数据的分析,阐述了飞机姿态测量误差对测量船校飞精度的影响,并针对校飞飞机的姿态测量提出了新的方法。     

Concomitant polymorphism in an organometallic ruthenium(II) complex with an N,N′‐donor ligand

The simultaneous crystallization of different polymorphs, i.e. concomitant polymorphism, is a phenomenon which, when properly recognized and studied, can provide useful information for a variety of disciplines. It is rare for ruthenium complexes, although it has been observed. In the synthesis of the ruthenium(II) complex chlorido(η⁶‐p‐cymene)(dimethyl 2,2′‐bypyridine‐4,5‐dicarboxylate‐κ²N,N′)ruthenium(II) hexafluoridophosphate, [RuCl(C₁₀H₁₄)(C₁₄H₁₂N₂O₄)]PF₆, concomitant polymorphs were crystallized under the same conditions. The colour of both crystals was orange, but the shapes, as well as the orientation of the p‐cymene and methoxycarbonyl groups, were different. The crystal structures of both isomers show approximately the same bond lengths. In the asymmetric unit, there is one cation and one anion. Due to the absence of strong hydrogen bonds, only weak intermolecular interactions were observed. The Hirshfeld surface and two‐dimensional fingerprint plots of both isomers satisfactorily explain the difference in the melting points.     

The Gauss Theorem for Domain Decompositions in Sobolev Spaces

This paper belongs to a broad line of research leaded by Herrera, which encompasses a good number of numerical methods such as Localized Adjoint Method (LAM), Eulerian-Lagrangian LAM (ELAM) and Trefftz-Herrera Method. The results presented in this paper are required in order to incorporate Herrera's general theory in a Sobolev-space setting. In particular, this article introduces a class of partitions (or domain decompositions) whose internal boundaries belong to a category of manifolds with corners, here also presented. Then a version of Gauss (or divergence) theorem, in a wider sense, is established and an explicit integral formula is associated for any given linear partial differential operator L, its adjoint and concomitant. The structure of the bilinear concomitant induced by L is first determined. Then the required formula is given over that class of domain decompositions. Finally, an integral formula well on the way of the Green-Herrera formula is settled.     

CFD computations of NAL experimental airplane with rocket booster using overset unstructured grids

Flows around the NAL jet‐powered experimental airplane with a small rocket booster under the fuselage are computed by solving the Euler equations using the overset unstructured grid method. The main objective of the present study is to evaluate the effect of a small rocket booster, which accelerates the airplane to supersonic speed, on the aerodynamic performance of the airplane during the ascent flight and the booster separation. Two unstructured meshes, one for the airplane and one for the booster, overlap. For the accurate separation simulation, the two bodies are in contact at first, and then the booster mesh is contact mesh is moved relative to the airplane mesh to evaluate flow interactions between two bodies. Copyright © 2005 John Wiley & Sons, Ltd.