航空材料质量信息管理系统

针对航空材料的特点，对航空材料质量信息管理系统进行了研究。联系我国飞机制造企业实际，阐述了航空材料质量信息流程、质量信息管理系统及其运行过程     

起落架四点布局无人机地面运动研究

以国内某四轮无人机为研究对象,在考虑摩擦力、侧向力和角速率等各种因素的情况下,全面分析研究了四轮无人机地面滑跑时的运动特点和受力情况,建立了六自由度刚体飞行器地面运动的动力学方程和运动学方程。在此基础上,对全量非线性模型进行了起飞、着陆时地面运动的仿真,该仿真结果表明了系统模型的正确性。     

基于联合隐马尔科夫模型的SAR图像去噪方法

提出一种联合隐马尔科夫模型的SAR图像去噪方法。基于贝叶斯准则估计隐马尔科夫树状模型的参数集合,得到各小波系数的期望值和收缩系数;引入二阶马尔科夫随机场模型去除小波系数尺度内的相关性,根据每个小波系数邻域内所有小波系数的隐状态和收缩系数,计算得到新的收缩系数,并对各小波子带的小波系数进行收缩,从而有效复原无噪声图像。实验表明,方法具有很强的噪声抑制能力,相对隐马尔科夫模型大幅提高了等效视数,且较好地保持了边缘。     

智能化建筑(小区)网络与设备管理的特点与内容

智能化建筑(小区)是一种崭新的人居环境，它给物业管理带来诸多不同以往的特点，尤其是在网络和设备管理方面。信息的流畅性与安全设施的完善使得物业管理工作较为舒适，网络设备功能的多样性使整体物业费用下降，但设备的先进性要求管理者具有较高素质。智能化网络与设备管理的核心工作是保持其长期、持续运行。这要求物业管理从以往的定性检查深入到对系统每个零部件物理层的定量化检测，保证网络与设备运行所需要的相关环境和条件，并对信息资源进行安全保护。     

H6飞机最大起飞质量数学模型的研究

正确确定最大起飞质量，对于轰炸机和大型运输机的起飞安全有着非常重要的意义。确定最大起飞质量，以往多采用作图的方法，由于影响最大起飞质量的因素比较复杂，所以比较准确的数学模型未曾建立。近几年来对这个问题进行了多方面的探讨，得出一个计算Ｈ６最大起飞质量比较准确的数学模型。此数学模型的建立为其它轰炸机、运输机最大起飞质量的计算开辟了一条新路，对工程应用具有一定的参考价值。     

舰载飞机飞行品质规范编制的原则,依据和设想

根据我国航空事业发展的需要，以及现行国军标（ＧＪＢ１８５－８６）所存在的不足之处，论述了编制舰载飞机飞行品质规范的必要性。进而提出了编制此规范应遵循的基本原则和主要依据，最后阐述了舰载飞机飞行品质规范的初步设想。     

细观损伤力学新进展

概述了细观损伤力学的当前状态，对存在的一些问题作了简要评述，并提出了若干修正方案。从应用的角度出发，对细观损伤力学未来的发展趋势进行了粗线条的观测。     

多波相参调制信号激励下的系统参数辨识

探讨了用来辨识飞行器上线性系统参数的新激励－－多谐波相参调制信号（ＳＰＨＳ）的性质及其在参数辨识中的具体应用。实验中运用系统辨识、参数估计、镜像映射原理，供助ＭＡＴＬＡＢ方便的矩阵运算能力，辨识了一个系统参数，结果说明此方法编程实现简洁、迅速，辨识精度高，适合系统的快速参数辨识。     

Backstepping design of missile guidance and control based on adaptive fuzzy sliding mode control

This paper presents an integrated missile guidance and control law based on adaptive fuzzy sliding mode control. The integrated model is formulated as a block-strict-feedback nonlinear system, in which modeling errors, unmodeled nonlinearities, target maneuvers, etc. are viewed as unknown uncertainties. The adaptive nonlinear control law is designed based on backstepping and sliding mode control techniques. An adaptive fuzzy system is adopted to approximate the coupling nonlinear functions of the system, and for the uncertainties, we utilize an online-adaptive control law to estimate the unknown parameters. The stability analysis of the closed-loop system is also conducted. Simulation results show that, with the application of the adaptive fuzzy sliding mode control, small miss distances and smooth missile trajectories are achieved, and the system is robust against system uncertainties and external disturbances.     

Dynamic modeling of a hose-drogue aerial refueling system and integral sliding mode backstepping control for the hose whipping phenomenon

Dynamic modeling of a hose-drogue aerial refueling system（HDARS） and an integral sliding mode backstepping controller design for the hose whipping phenomenon（HWP） during probe-drogue coupling are studied. Firstly, a dynamic model of the variable-length hose-drogue assembly is built for the sake of exploiting suppression methods for the whipping phenomenon.Based on the lumped parameter method, the hose is modeled by a series of variable-length links connected with frictionless joints. A set of iterative equations of the hose＇s three-dimensional motion is derived subject to hose reeling in/out, tanker motion, gravity, and aerodynamic loads accounting for the effects of steady wind, atmospheric turbulence, and tanker wake. Secondly,relying on a permanent magnet synchronous motor and high-precision position sensors, a new active control strategy for the HWP on the basis of the relative position between the tanker and the receiver is proposed. Considering the strict-feedback configuration of the permanent magnet synchronous motor, a rotor position control law based on the backstepping method is designed to insure global stability. An integral of the rotor position error and an exponential sliding mode reaching law of the current errors are applied to enhance control accuracy and robustness. Finally,the simulation results show the effectiveness of the proposed model and control laws.