飞机武器系统易损性评价中几何描述研究

提出了飞机易损性评价中应提供的几何数据，建立了各类几何及拓扑变换的数学模型，用此模型可计算易损性评价所需的各个标准方位的几何数据。     

利用奇异酉几何构作新的带仲裁的认证码

利用有限域上奇异酉几何构作了一个新的带仲裁的认证码．并计算了这个码的参数。当编码规则按等概率分布选取时，计算出了各种攻击成功的概率。     

Interference-free wind tunnel testing of jet propelled missiles

Wind tunnel evaluation of the aerodynamic interaction effects between plume and the external flow past the missile body including the wake boundary (“slipstream”) over powered flight envelopes of rocket propelled vehicles can be greatly facilitated — or even made possible — by a methodology replacing the hot propellant by cold, inert gases. Model nozzle design is based on the second order matching of plume geometry and first order modeling of plume stiffness. Since modeled nozzles will have larger throat radii than the prototypes, one can use sting-supported, sting-fed model installations thus eliminating aerodynamic interference effects due to struts. The concepts of simulated altitude and simulated full-scale Reynolds Number greatly reduce wind tunnel occupancy time. Computer programs, covering all steps of evaluating prototype nozzle performance, model sting nozzle design, model test evaluation and interpretation have been developed. The modeling methodology is supported by experimental results obtained in an induction wind tunnel at the FFA, Bromma, Sweden and in the 16 T and VKF-A altitude tunnels at AEDC, Tullahoma, Tenn.     

终端区飞行程序与军航起落航线安全风险分析

为了对终端区内民航进离场程序与军航机场起落航线间的安全风险进行分析,提出了一种基于计算几何的两阶段三维分析方法。首先对终端区空域进行建模,并利用军航机场起落航线保护区确定军航机场活动范围。在此基础上,第一阶段利用计算几何方法分析军航机场活动区与进离场航线间在二维上是否存在安全风险;第二阶段利用Route距离分析在二维上存在安全风险的程序段与军航机场活动区的垂直安全间隔。以国内某终端区为例进行了实例分析,证明方法能科学高效地对进离场程序与军航机场起落航线间安全风险进行三维空间分析。     

石英半球谐振子精密成型技术

石英半球谐振陀螺以其轻质、低功耗、长寿命、高可靠、应用精度范围宽、成本低等优势，引起了惯性技术界的瞩目。半球谐振陀螺的核心器件——石英半球谐振子的成型技术是当前的研究重点。经不断试验和摸索，以范成球面弹性展成为基础，通过均衡磨削原则、磨头最大包络原则和三阶段37道工序的精细优化工艺流程，较好地实现了高精度微应力硬脆石英谐振子异形薄壁件的成型，形成了专用的结构成型中心，为石英半球谐振陀螺的核心半球谐振子球壳成型开创了一条可行途径。     

Control of a Spherical Robot: Path Following Based on Nonholonomic Kinematics and Dynamics

This paper presents the controller design for the path following of a spherical mobile robot,BHQ-1.Firstly,a desired velocity for the reference path is deduced from the kinematic model,which cannot be transformed into the classic chained form.Secondly,a necessary torque for the desired velocity is obtained based on the dynamic model.As to the kinematics,a one-dimensional function is selected to measure the two-directional tracking error,and the velocity of rolling forward is reasonably assumed to be constant;therefore the multiple-input multiple-output (MIMO) system is transformed into a single-input single-output (SISO) system.As to the dynamics,both exact dynamics and inexact dynamics with modeling error as well as bounded unknown disturbance are taken into account,based on which a proportional-derivative (PD) controller and a sliding mode controller with adaptive parameters are proposed respectively.Finally,convergence analysis and simulation results are provided to validate these controllers.     

非线性飞行控制方法研究概述

原理性地给出目前常用的几种非线性飞行控制方法，即：数值优化法，动态逆设计方法，微分几何法和滑态变结构设计方法，指出了非线性飞行控制提高战斗机机支动性和敏捷性有重要作用，同时也介绍了这几种方法在非线性飞行控制中应用情况。     

球面收敛二元喷管出口三角形锯齿对气动和红外特性的影响

通过数值计算研究,分析了喷管出口锯齿修型对涡扇发动机排气系统球面收敛二元喷管气动及红外特性的影响.结果表明:相对于基准喷管,喷口锯齿修型均造成排气系统推力系数和总压恢复系数的下降,且齿底角越大,推力系数的损失越大.比较而言,内缩型锯齿修型方式对排气系统气动性能的影响最小,但导致排气喷流和总体红外辐射强度在±15°探测角附近的较大增强;外伸型锯齿修型对排气系统气动性能的影响最大;30°齿底角的等面型锯齿修型综合性能较优,对推力系数和总压恢复系数的影响微弱,同时在-30°~0°,0°~30°的探测视角内体现出一定的红外辐射抑制作用.      

可变几何燃烧室技术发展

对航空发动机可变几何燃烧室的研究状况进行了总结,燃烧室中可变几何结构包括气流分配器、旋流器、掺混孔、火焰稳定器等。可变几何的概念提供了一种灵活控制燃烧室内部气流分配的可能性,为减少发动机尾气排放、提高燃烧效率、保持燃烧室工作的稳定性和可靠性提供了新的突破点。     

三维充液航天器的位置和姿态联合控制

考虑充液月球着陆器悬停避障阶段的控制问题,采用三维球摆作为液体晃动部分的等效模型.针对球摆与刚体耦合的三维动力学模型,给出动力学模型的矢量方程及各矢量在本体系的投影坐标,设计位置和姿态联合控制器.所设计的控制器可以稳定航天器刚体的位置和姿态,且只依赖刚体的位置和姿态,不依赖晃动角或者动力学方程,利于工程应用.利用LaSalle不变原理分析闭环系统的稳定性,给出期望姿态为竖直时系统渐近稳定的控制器参数选择依据.最后数值仿真验证控制方法的有效性.