空战多目标分配的指派模型

针对多机协同空战中的多目标分配问题,提出了一种以空战几何态势矩阵为基础,以我方总体几何优势最大为原则,兼顾载机多目标攻击能力的目标分配算法。给出了总体几何态势训算公式及计算流程,将目标分配转化成指派问题后通过lingo 8．0软件编程进行分析研究。仿真算例表明了模型的有效性。     

The Edison infrared space observatory

For five years, theEdison program has had the goal of developing new designs for infrared space observatories which will break the cost curve by permitting more capable missions at lower cost. Most notably, this has produced a series of models for purely radiative and radiative/mechanical (hybrid) cooling which do not use cryogens and optical designs which are not constrained by the coolant tanks. Purely radiatively-cooled models achieve equilibrium temperatures as low as about 20 K at a distance of 1 AU from the sun. More advancedEdison designs include mechanical cooling systems attached to the telescope assembly which lower the optical system temperature to 5 K or less. Via these designs, near-cryogenic temperatures appear achievable without the limitations of cryogenic cooling. OneEdison model has been proposed to the European Space Agency as the next generation infrared space observatory and is presently under consideration as a candidate ESA Cornerstone mission. The basic design is also the starting point for elements of future infrared space interferometers.     

Adiabatic demagnetisation refrigerators for future sub-millimetre space missions

Space worthy refrigeration capable of providing a 100 mK and below heat load sink for bolometric detectors will be required for the next generation of sub-millimetre space missions. Adiabatic demagnetisation refrigeration (ADR), being a gravity independent laboratory method for obtaining such temperatures, is a favourable technique for utilisation in space.We show that by considering a 3 salt pill refrigerator rather than the classic single salt pill design the space prohibitive laboratory ADR properties of high magnetic field (6 Tesla) and a<2 K environment (provided by a bath of liquid⁴He) can be alleviated, while maintaining a sufficient low temperature hold time and short recycle time. The additional salt pills, composed of Gadolinium Gallium Garnet (GGG) provide intermediate cooling stages, enabling operation from a 4 K environment provided by a single 4 K mechanical cooler, thereby providing consumable free operation. Such ADRs could operate with fields as low as 1 Tesla allowing the use of high temperature, mechanically cooled superconducting magnets and so effectively remove the risk of quenching.We discuss the possibility of increasing the hold time from 3 hours, for the model presented, to between 40 and 80 hours, plus reducing the number of salt pills to two, through the use of a more efficient Garnet.We believe the technical advances necessitated by the envisaged ADRs are minimal and conclude that such ADRs offer a long orbital life time, consumable free, high efficiency means of milli-Kelvin cooling, requiring relatively little laboratory development.     

过渡领域三维绕流直接统计模拟位置元法的一种新方案

本文发展了ＤＳＭＣ方法计算三维绕流位置元方法的新方案，其总体方案和实施细节都是在分析和探索的基础上由我们自己提出的，特别还解决了除气动力、矩总体量以外的气动加热和压力分布等局部分布量的计算所提出的新问题。对于表面位置元的标识、分子的进入及与表面碰撞的判断、网格初始划分与调整、分布量计算对模拟过程及信息存贮所提的特殊要求等进行了分析和讨论，并通过与准确结果的比较证明了采用的方案和技术的有效性。     

21世纪AMSS／GNSS空间段发展方向兼论卫星资源国际共享问题

航空移动卫星系统（ＡＭＳＳ）空间段采用单一的ＧＥＯ轨道卫星，未来将有ＭＥＯ和ＬＥＯ轨道卫星加入运行，仍然不排斥ＧＥＯ轨道卫星的使用。全球导航卫星系统（ＧＮＳＳ）空间段采用ＭＥＯ轨道卫星，未来将仍然以ＭＥＯ为主，可能有ＨＥＯ轨道卫星加入运行。２１世纪的空间段将为不同轨道卫星的多星座组合，采用一星多用、星座共用，形成多功能卫星和多功能星座。和平时期卫星资源的国际民间共建共营共享将更为普遍，要有全球观点，国内各行各业要有全局观点，对监测和增强系统统一筹建共用系统，防止分散投资、重复建设     

弹塑性接触有限元分析的凝缩法

 解决弹性接触问题可用一种新的弹塑性接触有限元计算方法,即有限元混合法与弹塑性有限元分析的凝缩法结合而成,能显著地节省计算时间。文中对涡轮盘榫槽与叶片榫头的接触问题进行了计算分析。     

空间站的在轨推进剂再加注问题

建立一个永久性空间站,在轨推进剂再加注将是一个十分重要问题。本文评述了国外研制的各种方案,介绍了先进的在轨推进剂再加注技术、特性和可能实施的方案。最后指出了在轨再加注中的一些技术难点。     

作战飞机的空-地攻击效能评估

用概率方法建立了描述单一飞机在威胁环境中攻击一个地面被动目标的数学模型,导出飞机对地攻击作战的任务成功率、目标被击毁率和飞机损失率等效能的表达式,给出用于效能评估的有关事件发生概率的计算公式,通过计算实例讨论了作战飞机空－地攻击效能的各种度量。     

直升机非线性运动方程及其数值分析

基于牛顿法建立了单旋翼带尾桨直升机的非线性运动方程，提出了一种求解直升机非线性运动方程的数值方法。建立方程时，用欧拉角描述直升机在空中的姿态，旋翼采用有挥舞铰且在铰上带有弹性约束的模型，桨盘处的入流采用线性模型，通过对一算例直升机的操纵响应进行数值仿真，将非线性与小扰动线性化的直升机运动方程进行了对比分析。结果表明：从操纵输入到随后的2s左右，非线性和小扰动线性化的直升机运动方程的计算结果非常接近，但在此之后，非线性运动方程的计算结果更能反映直升机的运动规律。     

不对称推力飞行的最小操纵速度分析

首先,叙述了发生不对称推力飞行的条件,在不对称推力飞行条件下的操纵方法,以及和最小操纵速度的关系。然后,从横航向运动方程入手,推导出了地面和空中最小操纵速度的计算公式,并以Ｈ６飞机为例进行了计算。结果表明：地面和空中最小操纵速度的大小主要取决于工作发动机推力形成的偏转力矩。最后,分析了影响最小操纵速度的因素,指出了考虑最小操纵速度时不对称推力飞行的特点,可供飞行人员参考。