Radar transparent glass fabric reinforced polyetherimide/Cloisite 30B nanocomposites

High performance radar transparent materials (RTMs) are important materials for the fabrication of radomes, nosecones, etc. of high velocity aerospace vehicles. RTMs with good mechanical performance and temperature capability are required for such applications. Toward this, fabric reinforced nano‐reinforced matrix composites (FRNCs), using reinforcing E‐glass fabric in Cloisite 30B reinforced polyetherimide (PEI) nanocomposite matrix (GNRPEI), was prepared. The properties of GNRPEI were evaluated and compared with E‐glass fabric reinforced PEI composites (GRPEI) with special reference to their radar transparent character for aerospace applications. Tensile and flexural properties along with interlaminar shear strength of GRPEI were observed to be lower than those of GNRPEI. Thermal behavior of both the composites was similar in differential scanning calorimetry and thermal gravimetric analysis. But, in dynamic mechanical analysis, an increase in storage modulus and decrease in loss tangent were observed in GNRPEI compared to GRPEI. The values of dielectric constant and loss tangent of GNRPEI were lesser than those of GRPEI, but no significant difference was observed in the values of transmission and reflection losses for both the composites at 8–12 GHz frequency. FRNCs, based on organoclay reinforced PEI matrix, hold good promise as high performance RTMs. Copyright © 2010 John Wiley & Sons, Ltd.     

一种氯苯基硅油的合成及其摩擦磨损性能研究

合成了一种甲基封端、侧基含五氯苯基取代基团的有机聚硅氧烷(CPSO),考察了CPSO的粘温性能、倾点、饱和蒸气压及热稳定性能.采用OptimolSRV型微动摩擦磨损试验机评价了CPSO及空间用润滑油全氟聚醚(PFPE)和磷嗪(X-1P)在常温常压下用于GCr15/CuSn合金摩擦副润滑剂的摩擦磨损性能;采用CZM型真空摩擦试验机评价了3种润滑油在真空条件下用于GCr15/CuSn合金和GCr15/9Cr18摩擦副润滑剂的摩擦磨损性能.结果表明:在真空和常温常压条件下,CPSO的减摩和抗磨损性能均优于PFPE及X-1P;与此同时,CPSO具有极低的饱和蒸气压、很低的热挥发损失以及较好的热稳定性和低温流动性.故其在空间飞行器械运动部件润滑领域具有广泛的应用前景.     

300MeV质子同步加速器概念设计优化（英文）

目前处于设计阶段的哈尔滨工业大学空间辐照效应装置,其核心部件是由1台10 MeV的注入器、1台300MeV的同步加速器以及输运线构成的加速器装置。同步加速器中引出的质子束流被用于辐照研究。基于装置的概念设计,优化了其同步加速器部分的设计。设计了新的磁聚焦结构,优化了基于新的磁聚焦结构的多圈注入系统的凸轨变化模式,提高了注入效率。为了更好地优化引出束流的时间结构,慢引出系统采用了RF knock-out的方法。为了满足精准辐照的要求,研究了RF Kicker的频率调制,发现RF Kicker的双频调制能使得引出束流更均匀。A research complex for aerospace radiation effects research is in the designing stage in Harbin Institute of Technology. Its core part is a proton accelerator complex, which consists of a 10 MeV injector, a 300 MeV synchrotron and beam transport lines. The proton beam extracted from the synchrotron is utilized for the radiation effects research. Based on the conceptual design, the design study for optimizing the synchrotron has been done. A new lattice design was worked out, and the decreasing pattern of the bump of the multi-turn injection system was optimized to increase the injection efficiency. In order to improve the time structure of the extracted beam, a RF knock-out method is employed in the slow extraction system. To meet the requirement of accurate control of dose, the frequency modulation of the RF kicker is well investigated, and the dual frequency modulation has been found to have a better performance for a uniform spill.     

温度变化导致航天相机光学系统像面位移的研究

温度变化导致的像面位移会影响航天相机光学系统的成像质量。根据高斯光学理论,推导出了温度变化时的相机光学系统的像面位移公式,确定了温度敏感性最低的主、次反射镜的材料及与之相匹配的镜筒材料。最后计算和比较了在不同温度变化时的光学系统的传递函数。     

化学元素与航空航天

基于化学元素的视角，笔者总结了航空航天的推进剂、航空材料、能源、导航、生命保障系统等5个方面国内外的进展。航空航天的发展历程表明，高效环保的燃料、轻质高强的新材料、高功率密度的化学电源、更加精确的原子钟和可靠的生命维持系统，都需要化学元素的优化组合带来的新物质。     

某跨音风扇转子全三维设计与数值模拟

本文采用与三维流场分析程序相匹配的任意叶轮机通用叶片造型程序,进行某单级高通流、跨音、宽弦长风扇转子设计。在设计过程中,通过调整转子进口流量、出口总压、叶片最大相对厚度和前后缘厚度等参数沿径向的分布,弯度和最大弯度位置沿弦向的分布,从设计上减弱了叶片上部的激波强度、降低了激波及其关联的损失,克服了该转子叶尖高相对马赫数和低损失、高效率的矛盾。最终获得满足气动性能和结构强度的风扇转子.     

Optimal quasi-static shape control for large aerospace antennae

In this paper, we propose an on-line control approach which will adjust the steady-state shape of a large antenna arbitrarily close to any achievable desired profile. The method makes use of distributed parameter system theory and allows refocusing using a limited number of control actuators and sensors.The controller gains are calculated by approximating the solution to an infinite-dimensional optimal quasi-static control problem. We prove a very general convergence result for such quasi-static controllers here and apply it to the antenna controller to show convergence using any Galerkin (finite-element) approximation method.This research was partially supported by the National Science Foundation, the National Aeronautics and Space Administration, and the Air Force Office of Scientific Research under Grants ECS-80-16173, NAG-1-171, and AFOSR-83-0124, respectively.     

Turbulence modelling of problem aerospace flows

Unsteady Reynolds averaged Navier–Stokes (URANS) and detached eddy simulation (DES) related approaches are considered for high angle of attack NACA0012 airfoil, wing–flap, generic tilt‐rotor airfoil and double‐delta geometry flows. These are all found to be problem flows for URANS models. For DES fifth‐order upwinding is found too dissipative and the use of, for high speed flows, instability prone centred differencing essential. An existing hybrid ILES–RANS modelling approach, intended for flexible geometry, relatively high numerical dissipation codes is tested along with differential wall distance algorithms. The former gives promising results. The standard turbulence modelling approaches are found to give perhaps a surprising results variation. Results suggest that for the problem flows, the explicit algebraic stress and Menter shear stress transport (SST) URANS models are more accurate than the economical Spalart–Allmaras (SA). However, the explicit algebraic stress model (EASM) in its k–ε form is impractically expensive to converge. Here, SA predictions lack a rotation correction term and this is likely to improve these results. Copyright © 2005 John Wiley & Sons, Ltd.     

Suboptimal shape control for quasi-static distributed-parameter systems

We propose an on-line control approach which will adjust the steady-state shape of a large antenna arbitrarily close to any achievable desired profile. The method makes use of distributed-parameter system theory and allows refocusing using a limited number of control actuators and sensors.The controller gains are calculated by approximating the solution to an infinite-dimensional optimal quasi-static control problem. The controller gain calculation is computationally simpler than that proposed in a companion paper. The Galerkin (finite element) approximation method is used for model reduction. We prove that both gain and state convergence can be achieved by using the proposed approximation scheme.This work was partially supported by the Air Force Office of Scientific Research, Grant No. AFOSR 83-0124, and by the National Aeronautics and Space Administration, Grant No. NAG-1-515.     

Numerical solution of singular control problems using multiple shooting techniques

Algorithms for calculating the junction points between optimal nonsingular and singular subarcs of singular control problems are developed. The algorithms consist in formulating appropriate initialvalue and boundary-value problems; the boundary-value problems are solved with the method of multiple shooting. Two examples are detailed to illustrate the proposed numerical methods.The author would like to thank Professor Dr. R. Bulirsch, who stimulated and encouraged this work, which is part of the author's dissertation.