跨音压气机转子多目标气动优化设计

采用基于雷诺平均N-S方程的全三维流场模拟程序和基于多目标遗传算法的数值优化程序,对跨音压气机转子NASA Rotor37进行了优化设计。对所开发的三维N-S方程求解程序进行了实验验证,完善了多目标遗传算法与响应面方法相结合的具有全局寻优能力的优化程序,以总压比和绝热效率最大为设计目标,应用该优化方法对NASA Rotor37进行考虑中弧线和厚度分布的多目标气动优化设计。结果表明:在满足流量约束的条件下,绝热效率提高了0.7%,总压比提高了0.66%,并且优化设计时间大幅减小。     

航天嵌入式软件整数溢出的形式化验证方法

整数溢出引起的软件系统安全性问题屡见不鲜,已有的模型检测技术由于存在状态空间爆炸、不能有效支持中断驱动型程序检测等缺点而少有工程应用.结合真实案例,对航天嵌入式软件整数溢出问题的分布和特征进行了系统性的分析.在有界模型检测技术的基础上,结合整数溢出特征,提出了基于整数溢出变量依赖的程序模型约简技术;同时,针对中断驱动型程序,结合中断函数特征抽象,提出了基于干扰变量的中断驱动程序顺序化方法.经过基准测试程序和真实航天嵌入式软件实验,结果表明：该方法在保证整数溢出问题检出率的前提下,不仅能够提高分析效率,还使得已有的模型检测技术能够适用于中断驱动型程序整数溢出检测.     

Examination of superplastic forming combined with diffusion bonding for titanium: Perspective from experience

Superplastic forming (SPF) combined with diffusion bonding (DB) has been used successfully for the fabrication of titanium aerospace hardware. Many of these applications have been for military aircraft, whereby a complex built-up structure has been replaced with monolithic parts. Several methods for applying the two- and four-sheet titanium SPF/DB processes have been devised, including the welding of sheets prior to forming and the use of silk-screened stop-off (yttria) to prevent bonding where it is undesirable. Very little progress has been made in the past few years toward understanding and modeling the SPF/DB process using constitutive equations and data by laboratory testing. Concerns that engineers face in designing for fatigue life, acceptable design loads, and damage tolerance are currently being studied, but the database is very limited. This is a summary of past work found in the literature and forms the foundation for additional research. This paper was presented at the International Symposium on Superplasticity and Superplastic Forming sponsored by the Manufacturing Critical Sector at the ASM International AeroMat 2004 Conference and Exposition, June 8–9, 2004, in Seattle, WA. The symposium was organized by Daniel G. Sanders, The Boeing Company.     

飞机铝合金型材结构FSW焊接

提出了搅拌摩擦焊接（Friction Stir Welding,FSW）技术的3个基本要素,对铝合金型材FSW焊接件在航空结构中的几个典型应用进行了分析.并简要介绍了中国搅拌摩擦焊中心在铝合金型材搅拌摩擦焊接方面的研究成果.中国搅拌摩擦焊中心的研究表明,采用搅拌摩擦焊技术焊接铝合金能够得到比较满意的接头强度.     

船载测控雷达偏馈信号动态控制系统的设计

为了满足船载统一测控系统沟通无线偏馈射频链路进行遥测误码率测试的要求,进一步构建系统联调联试的动态射频信号环境,设计了船载测控雷达偏馈信号动态控制系统。通过系统监控台手动或自动远程控制位于天线背部中心体的数控衰减器,可实现雷达天线在对冷空的情况下接收偏馈射频信号幅度的变化,也可实现船载测控雷达系统联调过程中模拟目标动态变化情况,进而分析对系统跟踪性能的影响。该系统经过数次海上测控任务的检验,证明其方法科学有效、操作方便快捷、运行稳定可靠,达到了充分检验设备性能、提高任务准备效率的目的。     

A globally asymptotically stabilizing trajectory tracking controller for fully actuated rigid bodies using landmark‐based information

In this paper, we address the problem of designing a control law based on sensor measurements that provides global asymptotic stabilization to a reference trajectory defined on the . The proposed control law is a function of the angular velocity, of vector measurements characterizing the position of some given landmarks, and of their rate of change. We provide sufficient conditions for the existence of synergistic potential functions on SO(3) which are pivotal in the generation of a suitable hybrid control law. We also provide sufficient conditions on the geometry of the landmarks to solve the given problem. Finally, the proposed solution is simulated and compared with a continuous feedback control law. Copyright © 2014 John Wiley & Sons, Ltd.     

数字孪生增强的领域自适应航天器多余物检测

由于标注数据的短缺,对航天器多余物进行在线检测受到了较大的限制。文章研究了多余物的物理特性,在航天器的数字孪生系统中构建相应的多余物模型,提出了一种结合数字孪生技术增强的跨域自适应航天器多余物检测方法。该方法通过数字孪生技术获取航天器的实时数据,并借助于历史标注数据中的相似结构,以跨域自适应技术辅助实时在线推理的进行。设计了一种新型的跨域自适应模型,该模型采用共享网络结构以及门控机制,从而在复杂任务中更有效地挖掘先验知识,实现了跨域自适应技术与数字孪生技术的有机结合,以实现更高效、准确和实时的预测。此种方法可以全面地检测航天器各个部件的多余物状态。     

卫星多体制测控地面测试系统设计

随着航天技术的不断发展,卫星功能日趋复杂,对卫星测控分系统的功能提出更高的需求,要求同时支持对地非相干扩频测控、中继测控、扩跳频测控及测量数传测控体制,对卫星测控系统地面测试平台多体制支持、通用化及自动化测试能力、可靠性提出了更高要求;本文研究了卫星多体制测控地面测试平台系统设计方法,采用了多通道测控地检通道复用、基于数据库的通用化配置及自动化测试技术,应用于某遥感卫星的地面测试,测试结果表明：该平台运行稳定,取得了良好的使用效果,满足了卫星多体制测控地面测试需求;     

Fracture mechanics modelling of constant and variable amplitude fatigue behaviour of field corroded 7075‐T6511 aluminium

For ageing airframe structures, a critical challenge for next generation linear elastic fracture mechanics (LEFM) modelling is to predict the effect of corrosion damage on the remaining fatigue life and structural integrity of components. This effort aims to extend a previously developed LEFM modelling approach to field corroded specimens and variable amplitude loading. Iterations of LEFM modelling were performed with different initial flaw sizes and crack growth rate laws and compared to detailed experimental measurements of crack formation and small crack growth. Conservative LEFM‐based lifetime predictions of corroded components were achieved using a corrosion modified‐equivalent initial flaw size along with crack growth rates from a constant K_max‐decreasing ΔK protocol. The source of the error in each of the LEFM iterations is critiqued to identify the bounds for engineering application.     

航天发射任务组织指挥工作相关问题研究

加强新形势下航天发射任务组织指挥能力建设是满足我国当前高密度多样化发射任务要求的重要内容。分析了航天发射任务组织指挥工作的建设需求,在此基础上对航天发射任务组织指挥工作需要解决的关键问题进行了查找和反思,提出新形势下组织指挥工作的总目标以及建设的原则,同时针对存在的问题给出相应的建议和改进措施。