气浮十字梁系统的气动-质量矩复合控制研究

推导了基于气动-质量矩复合控制的气浮十字梁三自由度运动动力学方程,对纵向运动模型进行了数学仿真和实物实验。通过数学仿真和实物实验的比较,验证了建立模型的准确性,并对共栖效应现象进行了研究,为深入探讨气动-质量矩复合控制奠定了基础。     

飞机电源系统参数测试软件的通用性设计

从自动测试系统通用性的角度出发,阐述了ATS软件通用性的实现及关键技术.利用MFC在组件技术的基础上完成了飞机电源系统通用参数测试软件功能组件开发,同时结合GL Studio完成了图形控件的设计和开发.借助于LabWindows/CVI,给出了通用测试软件集成的详细说明和方法步骤.     

零差激光干涉仪在超低频大振幅振动测量中的应用

介绍了利用正交的零差激光干涉仪测量安装于振动台面被测靶体的位移,实时计算出运动速度和加速度,从而实现对位移达1m的超低频振动传感器的实时绝对校准。     

空中声源水下声场的简正波建模方法

空水界面声信号传播特性是水下检测空中声源首先要研究的问题,文中讨论了空中声源在水下产生声场的简正波模型,仿真分析了空中声源的水下声场,比较了简正波方法与射线方法、快速场方法对空中声源在水下产生的声场传播损失。结论表明简正波方法适用于远场传播损失。     

弯管角度对爆轰波传播特性的影响

利用相关软件和数据,分析了爆轰波在弯管中传播时,弯管角度对其传播速度和爆轰压力所产生的影响。所得结论对于研究爆轰波在弯管巾的传播特性以及指导工程实践具有一定意义。     

四旋翼飞行器建模、控制与仿真

四旋翼飞行器在平面结构上具有4个平均分布且呈十字对称的推进器。建立了机体坐标系和惯性坐标系,根据飞行器的动力学特性建立该飞行器的数学模型;利用滑模控制的方法对所建立的模型进行研究;在满足李雅普诺夫稳定条件下,利用反演控制方法推导出控制滑模面,并建立滑模控制律;最后,在给定参数值的情况下,通过所建立的控制律对该飞行器的滑模控制进行了仿真。     

Gravitational wave detection on the Moon and the moons of Mars

The Moon and the moons of Mars should be extremely quiet seismically and could therefore become sensitive gravitational wave detectors, if instrumented properly. Highly sensitive displacement sensors could be deployed on these planetary bodies to monitor the motion induced by gravitational waves. A superconducting displacement sensor with a 10-kg test mass cooled to 2 K will have an intrinsic instrument noise of 10⁻¹⁶ m Hz^−1/2. These sensors could be tuned to the lowest two quadrupole modes of the body or operated as a wideband detector below its fundamental mode. An interesting frequency range is 0.1–1 Hz, which will be missed by both the ground detectors on the Earth and LISA and would be the best window for searching for stochastic background gravitational waves. Phobos and Deimos have their lowest quadrupole modes at 0.2–0.3 Hz and could offer a sensitivity h_min ? 10⁻²² Hz^−1/2 within their resonance peaks, which is within two orders of magnitude from the goal of the Big Bang Observer (BBO). The lunar and Martian moon detectors would detect many interesting foreground sources in a new frequency window and could serve as a valuable precursor for BBO.     

航空装备备件需求量的概率区间计算方法

科学合理地解决备件配置问题一直为人们所瞩目,备件配置数量的多少不仅影响装备的维修甚至影响装备的战备完好率。计算备件需求量的传统模型是概率模型,然而概率模型中的分布参数往往有一定程度的不确定性。本文对概率模型中含有有界不确定参数的备件需求量计算问题进行研究,根据航空装备备件的分类,分别提出了寿命服从指数分布、正态分布和威布尔分布部件的备件需求量的概率区间确定方法。所提出的方法较好地解决了分布参数有界不确定时航空装备备件的配置问题并能够充分保证备件的保障率,进而提高航空综合保障水平。最后,通过数值算例说明了该方法的有效性和实用性。     

错频叶盘结构振动模态局部化特性分析

利用"错频失谐(Mistuning)"是进行颤振抑制的有效手段,但是否会导致较大叶盘结构振动局部化是需要进一步研究的问题.本文以典型压气机叶盘结构为例,通过引入实际的两种错频失谐方案,分析研究了谐调和"错频失谐"情况下叶盘结构振动模态特性和模态局部化性质.研究表明,"错频失谐"会引起显著的振动局部化,因此实际叶盘失谐设计中需要综合考虑颤振抑制和失谐振动局部化两方面.      

Variable Structure Control of Catastrophic Course in Airdropping Heavy Cargo

The mathematical model of a transport aircraft would be subjected to a sudden change when heavy cargo is dropped off in airdropping, which exerts serious influences upon the safety of the aircraft. A variable structure controller is specially designed for handling the airdrop process. The nonlinear system is linearized by input-output feedback linearization using differential geometry theories. On this basis, an inner loop system for velocity and attitude tracking control is designed by using the exponentially approaching rule of the variable structure theory. The whole flight control system is integrated with the outer loop flight altitude control. Digital simulation evidences the applicability of the system to potentially catastrophic course in airdropping heavy cargo and provides robustness against system parameter perturbation.