简易控制火箭靶弹总体设计

为模拟火箭靶弹平飞和俯冲类目标的运动特性,设计了火箭靶弹总体方案,建立了火箭靶弹总体设计数学模型,进行了火箭靶弹参数优化设计.基于大射程火箭弹,通过调整原型火箭弹气动外形和结构组成,加装鸭式控制舵面,进行俯仰角程序控制,在被动飞行段实现有攻角飞行,可延长滞空时间,实现准平飞弹道.简易控制火箭靶弹具有高供靶精度、低成本和低风险等显著特点.     

基于变结构控制的气动力/直接力切换控制设计

为了减小脉冲发动机工作时喷流与外流场对弹体和气动舵面产生的耦合作用,提高气动力／直接力复合控制系统的性能,文中提出一种气动力／直接力切换控制方案,即在导弹末端攻击目标时断开气动力控制回路,只用直接侧向力控制。采用变结构控制设计飞行控制系统,实现气动力与直接力的平滑切换。数字仿真结果表明该方法能有效地提高导弹自动驾驶仪的快速性、鲁棒性,减小直接力机构与气动舵面之间的操纵耦合,显著改善导弹的脱靶量。     

单组舵控火箭弹控制能力及精度研究

简易控制弹药由于其成本低、精度高,一直是国内外研究灵巧弹药的一个重要方向。文中在某常规火箭弹上加上两片气动舵,对火箭弹弹道进行数值仿真。主要分析了舵起控时间和舵偏角大小对修正能力的影响,并计算了舵的修正能力和控制精度。结果表明:在文中的假设条件下,选择10°舵偏角,出炮口47.55s时进行控制,能保证弹箭稳定飞行且修正能力最强,舵机的控制精度在0.8%以内。     

大攻角飞行的自动驾驶仪设计问题

符号说明α导弹攻角β导弹侧滑角ψ偏航角φ航向角γ滚动角δ_y沿偏航方向的舵偏角δ_x沿滚动方向的舵偏角V导弹的飞行速度m导弹的质量a_z横向加速度I_x(I_y)弹体沿x(y)轴方向的转动惯量F_k由k引起的侧向力系数k=β,δ_x,δ_yM_i~j 由i引起的沿j方向的力矩系数i=β,ψ,δ_x,δ_y,γj= x,ya,b,c,d气动系数A,B,D系数矩阵K反馈矩阵e误差量一、大攻角飞行的气动交链随着飞行目标速度的增加,要求地空导弹显著地增加机动性能和提高制导精度。对于用气动力控制的导弹,为了提高在高空低动压飞行的机动过载,需要增加导弹飞行的攻角;而在大攻角飞行时,导弹将产生明显的气动交链影响,因而给自动驾驶仪的设计造成困难。     

基于地磁传感器的点火脉冲选择策略分析

采用小型脉冲推力器组修正弹道偏差是提高火箭弹射击精度，减小落点散布的有效方法。但脉冲推力器的点火时机对射弹落点的控制能力有很大的影响，如何从脉冲发动机组中选择点火是弹道修正过程中的关键环节。文中在旋转弹有控弹道模型的基础上，提出了一种借助于地磁传感器测量，来控制脉冲推力器适时点火的策略。地磁传感器测量的数据不仅用于解算弹体飞行姿态，同时可通过计算给出点火脉冲发动机选择的方向基准。     

滑翔增程弹鸭式舵的气动设计与分析

为了保证滑翔增程弹箭在滑翔飞行过程中有效地增程,必须对滑翔弹箭的舵面进行气动设计与分析.阐述了制导炮弹舵面参数确定的原则,研究了滑翔增程弹舵面几何参数的选择、舵面尺寸确定的方法.仿真结果表明,采用该方法确定的舵面气动性能能够保证滑翔增程弹在滑控段飞行过程中稳定性适当,静稳定性储备量约在4%左右;操纵性较好,舵面偏转10°,能够产生约6°的平衡攻角;稳定性与操纵性、舵偏角和平衡攻角匹配较好,为滑翔增程弹舵面的气动设计提供了参考.     

鸭式布局大翼面火箭弹气动特性研究

具有较大翼面的鸭式布局平飞火箭弹,在对火箭弹结构设计时,既要保证其在大马赫数范围内飞行具有较大的升阻比满足平飞要求,又要满足滚转控制能力的要求.针对这个问题,采用数值流体力学分析手段,运用fluent软件仿真分析了在差动舵偏角δ=20°时翼面不同后掠角对火箭弹气动特性的影响.仿真结果表明:在舵偏角和攻角同时作用下,翼面后掠角χ=50°时火箭弹升阻比较大,滚转控制能力也最好.     

高旋火箭弹增程稳定性设计及气动特性分析

针对旋转稳定火箭弹提高射程和增大飞行速度带来的飞行不稳定问题,进行了基于稳定飞行的转速设计,并利用FLUENT软件和用户自定义函数UDF,在旋转壁面边界条件下对火箭弹进行气动特性仿真,分析了火箭弹阻力系数、升力系数和马格努斯效应随攻角的变化规律。结果表明:在设计转速为2827.43rad/s下,气动仿真和外弹道仿真结果能够满足火箭弹飞行稳定性要求,从而为火箭弹增程设计提供了依据。     

火箭弹折叠尾翼的质量优化设计

火箭弹作为一种飞行武器,弹体应具有良好的气动性能.弹翼作为火箭弹结构的重要部分,可以产生飞行升力和对弹体的操纵力,并能加强弹体飞行的稳定性.火箭弹尾翼的质量与其飞行性能相关,此以火箭弹尾翼的质量为优化目标,进行尾翼的轻量化设计.根据火箭弹飞行的空气动力学要求,在尾翼面积不变的条件下以尾翼翼根厚度和展向厚度变化量作为设计变量,以翼面受气动载荷时的最大挠度和翼面展开时间为约束变量.通过理论分析和数值计算,给出了设计变量的设计可行域,得到了尾翼质量的优化设计结果,其优化后质量比优化前减少41%.     

基于Anti-Windup回馈推力矢量飞行控制系统研究

针对带推力矢量飞机大迎角机动飞行控制问题,文中主要研究推力矢量与气动舵面融合控制策略问题。结合串级链式推力矢量控制分配和Anti-Windup抗饱和控制结构,提出了一种基于Anti-Windui回馈推力矢量飞行控制系统设计结构,该控制策略合理分配操纵面的偏转指令,实现推力矢量和气动舵面的协调偏转。仿真结果表明,采用Anti-Windup抗饱和控制结构的推力矢量/气动舵面控制融合结构,对完成飞机在纵向平面内的过失速机动动作,有更好的控制效果。     

Open Rule-setting System Applied to Conceptual Design of Engines

Open rule-setting method advanced in this paper concentrates on providing designers of engines with a convenient way to express their design innovations and develop the expected prototypes in the early CAD stage, and constitute effective models for the following analysis process of CAE and CAPP. The problems arisen in the process of conceptual design with the traditional experience-based development method are analyzed. Based on those analyses, open rule-setting method is presented and some associated technical problems are discussed. The functional framework of open rule-setting system was built as software engineering methods. The speciality of the engine product as a kind of complex product and the requirement of the engine product based on its structural particularity to rule-setting system are considered carefully. A demonstration is supplied to illustrate how the open rule-setting method enhances the efficiency and quality of the engine conceptual design.     

Research on Linux Network Device Driver

By analyzing the working principle of Linux network device driver, discussing the Linux network driver structure and its key technologies, the general network driver structure and its design methodologies in Linux system are summarized. Through modifying the network device driver of Linux device driver 3rd version snull, c and improving the COW technology, the Zero-Copy technology in Linux （kernel version 2.6.11 ） is implemented. In the end, the success test tells us that the thorough analysis of network device driver is the foundation of many applications, and it also provides a certain improvement to a lot of real applications, even to military application development.     

Algorithm for Multi-laser-target Tracking Based on Clustering Fusion

Multi-laser-target tracking is an important subject in the field of signal processing of laser warners. A clustering method is applied to the measurement of laser warner, and the space-time fusion for measurements in the same cluster is accomplished. Real-time tracking of multi-laser-target and real-time picking of multi-laser-signal are introduced using data fusion of the measurements. A prototype device of the algorithm is built up. The results of experiments show that the algorithm is very effective.     

Influence of Installing Error on the Surface Shape Precision of the Axial Symmetry Aspheric Workpiece in Lapping

A method to calculate the surface shape error, which is caused by the installing error between the workpiece and the lapping tool in the process of form lapping, is proposed. The mathematical model which the installing translation error influences on the workpiece surface shape error is established. The changing rule of the error is simulated through the calculating example of the paraboloid workpiece. The results indicate that the surface shape error of the workpiece is increasing with the increase of the installing translation error, it is also increasing gradually along the center point of the curve surface to the edge, and the influence is severer to the curve surface with great curvature than that of the small curvature when the translation error is the same.     

Experimental Research on Output Performances of Giant Magnetostrictive Actuator

The paper introduces the performances of magnetostrictive actuators and its applications, discusses the design methods for the structure and internal magnetic circuit of a giant magnetostrictive actuator, and makes tests on the output displacement and force characteristics for an actuator using homemade magnetostrictive material. The experimental result shows that the actuator has satisfactory output precisions and ranges in transient and stable states, and can be used in lowfrequency vibration control system of precise equipment.     

Overview of Anti-tank Mines

First the different anti-tank mines laying possibilities are shortly summarized： hand emplaced, with mine layers, ground or helicopter relatively topographical well defined, and with cluster systems of projectiles, rockets and aircraft dispensers. Then examples of the three generations of anti-tank mines are presented：Ⅰ generation： detonating only beneath the track; Ⅱ generation： detonating beneath the track and belly; Ⅲ generation： mines with off-route actions. Weight and cost comparisons are strongly favoring the off-route Ⅲ-generation mines.     

A Finite Element Analysis on Static Strength of a Complex Section

A static finite element analysis （FEA） of an impulsive controller section is presented. The boundary condition and a part of the loads are applied. Considering the grades of the stress around the holes being large, the dense grids are adjusted accordingly. Four cases with different loads are compared, thus the influences of different loads on the section are analyzed. Numerical results show that the maximum stress of the section is lower than the strength limit of the material, and the section will not be broken with the static loads.     

Discussion on Mechanism of Breech-Blow Caused by Propellant Charge

From the view point of launch safety caused by fracture of propellant charge, this paper points out that the safety criterion of pressure wave is inadequate to evaluate the launch safety of propellant charge based on the initial negative differential pressure and sensitivity tests. Generally, the maximum barrel pressure does not depend upon the intensity of pressure wave correspondingly. The pressure wave intensity can not describe the fracture degree of propellant charge in chamber and reflect the mechanical environment of propellant charge fracturing exactly and wholly. The evaluation criterion for launch safety of propellant charge should be built on the basis of depicting the fracture degree of propellant bed.     

Experimental Studies of Toxicity on HNIW and Its Intermediates

The polycyclic nitramine hexanitrohexaazaisowurtane（HNIW） is a compound of high energy density. HNIW can replace 1, 3, 5-trinitro-1, 3, 5-triazacyclohexane（RDX） or HMX, hut its toxicity is unknown. In this paper, HNIW, hexabenzylhexaazaisowurtzitane （HBIW）, tetraacetyldibenzulhexaazaisowurtzitane （TADBIW）, tetraacetyldiformylhexaazaisowurtzitane（TADFIW） and tetraacetylhexaazaisowurtzitane（TAIW）, which are intermediates of the synthesis of the HNIW, were selected as the tested objects in acute toxicity test, acute eye stimulation test and skin irritation test according to the standards of ＂chemical product testing method-401 ： acute oral toxicity test＂, ＂chemical product testing means-405： acute eye irritation/corrosion test＂ and ＂chemical product testing means-404： acute dermal irritation/corrosion test＂ of National Circumstance Protect Bureau. The results show that all of the five objects have no toxicity, no stimulation to eye and skin under the tested conditions.     

Dynamic Simulation for Missile Erection System

In order to study the dynamic characteristics of the missile erection system, it can be considered as a rigid-flexible coupling multi-body system. Firstly, the actual system is abstracted as an equal and simplified one and then the forces applied to it are analyzed. Secondly, the rigid-flexible coupling dynamic simulation for erection system is accomplished by use of the system simulation software, for example Pro/E, ADAMS, ANSYS, MATLAB/Simulink, etc. Finally, having the aid of simulation results, the kinetic and dynamic characteristics of the flexible bodies in erection system are analyzed.The simulation considering the erection system as a rigid-flexible coupling system can provide valuable results to the research of its kinetic, dynamic and vibrational characteristics.