Cahn-Hilliard方程的行波解

主要利用奇异摄动方法,得到一维Cahn-Hilliard方程行波解形式的内、外解.两者匹配得到整体行波解.这个结果的特点是,它不仅将高阶偏微分方程的解用内外解匹配好,而且完全满足方程的边界条件和初始条件.当长时间变化时, Cahn-Hilliard方程的解以行波结构为极限状态.此结果很好地解释Cahn-Hilliard方程的现有理论及数值结果,实际模型和方程的性质也完全符合.     

三轴稳定通信卫星在地球指向模式下的陀螺标定

本文介绍三轴稳定通信卫星在地球指向模式下的陀螺标定方法和计算公式。转移轨道远地点火后及同步轨道在三轴稳定地球指向模式下的陀螺标定是利用地球敏感器、太阳敏感器和速率积分陀螺信号的遥测值标定陀螺常值漂移。     

一种基于Star算法的多路视频稳像方法研究

目前,基于特征点匹配的稳像算法中存在特征点提取速度慢、误匹配率高,以及多目相机的多路视频稳像太过耗时、实时性不好的问题,提出了一种基于Star特征点提取算法的多路视频快速稳像方法。首先采用Star算法提取视频当前帧特征点,然后采用光流法结合当前帧特征点信息跟踪预测下一帧对应的特征点,以加快特征点提取速度,同时减少所提取的特征点错误匹配率。通过对匹配的特征点求取相应的仿射变换矩阵获取帧间运动矢量,进而采用卡尔曼滤波器对帧间运动矢量进行滤波处理,以滤除其中的相机随机抖动矢量并保留相机的主观运动矢量。最后依据滤波后的运动矢量进行图像补偿得到稳定的图像序列。针对复眼导引头存在的多路视频抖动情况,基于OpenMP并行开发库,利用多核处理器的优势,实现了多路抖动视频的并行实时稳像。所设计的数字稳像算法在PC平台下对4路抖动视频（OTB100的BlurCar系列视频,分辨率为640×480,帧率为30 FPS）并行稳像的结果参数为：峰值信噪比（Peak Signal-to-Noise Ratio,PPSNR）平均提升了4.62 dB,单帧耗时平均为14.51 ms。经仿真实验证实,算法的计算效率和特...     

尾缘吹气式火焰稳定器流场计算

用修正的ｋ－ε模型、ＳＩＭＰＬＥＲ方法,对二元管道中新型火焰稳定器后冷态流场进行了数值模拟,研究了气流参数及稳定器几何参数变化对回流区结构的影响。为研究、分析新型稳定器燃烧性能,设计新型稳定器提供了依据。     

螺旋桨升力线理论的匹配渐近展开法分析

在固连于螺旋桨桨叶的非惯性坐标系中,对大展弦比叶片的螺旋奖建立了升力线模型。在匹配渐近展开法分析中引入一假想速度位,导出固连坐标系中的控制方程、边界条件和Ｂｅｒｎｏｕｌｌｉ方程。由匹配渐近展开法的分析表明,在螺旋桨的进距比不是太小的情况下,螺旋桨的升力线理论在固连于螺旋桨桨叶的非惯性坐标系中仍然成立。     

空气节流对超燃冲压发动机燃烧室起动点火影响的数值研究

利用空气节流在流场中产生激波串,有效地辅助燃料实现起动点火.非定常Navier-Stokes方程数值模拟研究了空气节流对超燃冲压发动机燃烧室起动点火的影响,分析了起动点火时间段(0~1.0ms)内空气节流 对流场参数的影响.数值模拟结果表明:在燃烧室入口马赫数为2.0、静温为548.8K、静压为101555.9 Pa,乙烯燃料当量比为0.5,先锋氢辅助点火的条件下,距离发动机入口845mm处,节流流量为入口空气流量的30%,有效地实现了发动机的起动点火,无空气节流情况下的发动机点火效果不佳,火焰最终熄灭.      

MEMS偏航角速度传感器在旋转导弹稳定回路中的应用

在旋转导弹稳定回路中,采用MEMS偏航角速度传感器用于弹体偏航角速度的测量,偏航角速度传感器是旋转导弹控制回路的重要组成部分。提出了一种全新的MEMS偏航角速度传感器技术方案,解决了MEMS偏航角速度传感器正交耦合、力学环境适应性、波形畸变等问题,实现了旋转导弹偏航角速度信号的精确测量。     

Full mode flight dynamics modelling and control of stopped-rotor UAV

The Stopped-Rotor(SR) UAV combines the advantages of vertical take-off and landing of helicopter and high-speed cruise of fixed-wing aircraft. At the same time, it also has a unique aerodynamic layout, which leads to great differences in the control and aerodynamic characteristics of various flight modes, and brings great challenges to the flight dynamics modelling and control in full-mode flight. In this paper, the flight dynamics modelling and control method of SR UAV in full-mode flight is st...     

Robust H∞ controller design for attitude stabilization of flexible spacecraft with input constraints

This paper addresses the attitude stabilization and vibration suppression problem for flexible spacecraft subject to model parameter uncertainty, controller perturbations, external disturbances and input constraints. The attitude model of flexible spacecraft is described and converted into a state space form in terms of passive and active vibration suppression schemes. A novel state feedback controller is proposed based on the exactly available expectation of a new variable, which is introduced to model a randomly occurring controller gain perturbation. Based on Lyapunov stability theory, sufficient conditions for the existence of the nonfragile H_∞ controller considering input constraints are given based on linear matrix inequalities (LMIs) in terms of additive perturbation and multiplicative perturbation. Then, the developed controller subject to required constraints can be obtained, where the nonfragile property is fully considered to improve the tolerance to uncertainties in the controller. Numerical simulations are performed to demonstrate the effectiveness and superiority of the proposed control strategy in attitude stabilization and vibration suppression, where it should be noted that the passive vibration suppression scheme is superior for high natural frequencies while the active vibration suppression scheme is superior for low natural frequencies. Moreover, the low natural frequencies have more influence on the performance of attitude stabilization and vibration suppression.     

Experimental research of air-throttling ignition for a scramjet at Ma 6.5

An experimental investigation on ignition characteristics with air-throttling in an ethylene-fueled scramjet under flight Ma 6.5 conditions was conducted.The dynamic process of air-throttling ignition was explored systematically.The influences of throttling parameters,i.e.,throttling mass rate and duration,were investigated.When the throttling mass rate was 45% of the inflow mass rate,ambient ethylene could be ignited reliably.The delay time from ignition to throttling was about 45–55 ms.There was a threshold of throttling duration under a certain throttling mass rate.It was shorter than 100 ms when the throttling mass rate was 45%.While a 45%throttling mass rate would make the shock train propagate upstream to the isolator entry in about10–15 ms,four lower throttling mass rates were tested,including 30%,25%,20%,and 10%.All of these throttling mass rates could ignite ethylene.However,combustion performances varied with them.A higher throttling mass rate made more ethylene combust and produced higher wall pressure.Through these experiments,some aspects of the relationships between ignition,flame stabilization,combustion efficiency,and air-throttling parameters were brought to light.These results could also be a benchmark for CFD validation.