【作者】 程凤舟；

【导师】 陈士橹； 于本水；

【作者基本信息】 西北工业大学 ， 飞行器设计， 2002， 博士

【摘要】 本文主要研究拦截弹在拦截战术弹道导弹时，末段的制导和侧向力控制问题，包括大气层外动能拦截器在姿控与轨控发动机作用下的性能分析，和大气层内侧向力与气动力复合控制研究。研究内容及成果主要表现在以下几个方面： (一)大气层外动能拦截器分析 首先建立了动能拦截器运动学和动力学模型，以及轨控发动机和姿控发动机的推力模型，提出了拦截导引律的实现方法及轨控和姿控发动机的控制规律。在此基础上进行了动能拦截器拦截过程仿真，验证了动能拦截器能够直接碰撞命中弹道导弹的结论，并详细分析了在不同相对距离的初始条件下，航向误差对拦截性能的影响。 (二)大气层内复合控制问题 1．确定拦截弹模型。首先根据拦截任务的特点来确定拦截导弹的总体方案，包括导弹的气动布局，控制方式等。然后以基本满足方案要求的某型防空导弹为基础，对其几何尺寸、发动机等分系统进行改进，并通过分析导弹性能与侧喷发动机参数之间的关系，增加了姿控或轨控侧向装置，这样得到了本文的研究工作所需的导弹模型。 2．根据大量参考文献的结论，分析了侧向喷流射入拦截弹外流的流场特征，以干扰放大因子来描述干扰效应对力和力矩的影响，给出了放大因子的计算方法，进一步建立了喷流侧向力和空气动力作用下的导弹运动学和动力学模型。 3．设计气动力与侧向轨控直接力的复合控制系统。设计的轨控直接力作用于俯仰和偏航通道，而滚转通道没有直接力系统的作用，依靠气动舵面的偏转对滚转角进行稳定。复合控制采用对制导指令进行前向分解的方法，将复合控制系统分为两个并行的子系统，即气动力控制子系统和直接力控制子系统。采用古典控制理论来设计气动力控制系统，包括具有角速度反馈的稳定内回路、跟踪制导指令的外回路以及各校正环节的设计。仿真结果显示，复合控制系统的可用过载和动态性能都有明显提高。 4．为了解决拦截弹气动参数随飞行高度、速度、姿态的不同，变化范围大，控制系统难以准确建模的困难，基于纵向平面拦截弹模型，采用模型参考变结构控制理论设计了俯仰通道姿控复合控制系统，以可测量变量过载和角速度作为状态量建立了系统的状态方程，讨论了参考模型的选择方法，并对系统的性能作了仿真分析。 5．针对拦截战术弹道导弹这一特殊任务，分析了导引律设计面临的新问题，提出了以预测拦截命中点为思想的中制导段导引方法，研究了末制导段比例导引律弹道形状和过载分布特点，在此基础上为了改善比例导引律的缺陷，引入了目摘‘要标机动加速度和导弹轴向加速度等信息、，又寸比例导引律进行了修正，井对导引律中各参数进行了优化。采用质点弹道仿真的方法对经典比例导引律和本文提出的修爪比例导引律的性能进行了仿真分析，结果表明修正比例导引律的过载分响;合理，利于中末制导顺利交班，!衍且形式简单，具有实工}J价值。 6.在以上内容的基础上，建立了拦截弹末制导有关的六自}扫度数学模型和仿真模型，对不同初始条件F栏截飞机和战术弹道一导弹进行了数字仿真，分析了拦截.高速弹头时弹适的新特点，夕手采用蒙特卡洛法分析了不同误差因素作用卜的制导精度。结果表明，设计的复合控制系统较纯气动力控制系统性能有所提高，能够拦截中等再入速度的.f浅术弹道导弹弹头。更多还原

【Abstract】 The main works of this thesis are research of lateral force control and guidance of interceptors, emphasized on the terminal phase when intercepting the tactical ballistic missiles, including the performance analysis of extra-atmospheric kinetic-kill vehicle piloted by trajectory-control and attitude-control systems, and combined control of aerodynamics with lateral jets in atmosphere. The main work and achievements are described as follows:(1) The analysis of the extra-atmospheric kinetic-kill vehicleAt first, the motion model and dynamics model of the kinetic-kill vehicle is constructed, and the thrust performance of trajectory-control system and attitude-control system are presented, then the algorithms of realizing the guidance law, the methods of trajectory and attitude control are studied. The simulation of the terminal guidance procedure is carried out, and the results verified the conclusion that the interceptor can hit the target directly. At last, the effect of flight path angle error on interception performance is analyzed in detail.(2) The study of combined control methods of an intercepting missile in atmosphere1. The parameters choice of intercepting missile. The whole scheme of the interceptor is chosen at first according to the characteristics of the mission, including the aerodynamic configuration and the control style. And then based on a surface-to-air missile that satisfies the requisition nearly, by means of reconstructing its geometry size, subsystems such as engine, the interceptor model used to continue the following studies is established. Then the trajectory-control jet or attitude-control jet is added to the interceptor based on the analysis of the relationship between the missile performance and the thrust and configuration of the side jet.2. On the basis of looking up a lot of referenced works, the phenomenon that lateral jet injected into the external air stream surrounding an intercepting missile is analyzed. The effects of jet interaction on forces and moments are described by interaction amplification factor, and the algorithm to calculate the interaction amplification factor is presented, then the motion model and the dynamics model of interceptor are established according to the previous analysis.3. The combined trajectory control system is designed. The direct force is acting on the pitch channel and the yaw channel, and the roll channel is stabilized by the fin surface deflection. By means of guidance command decomposed forwardly, the combined control system is divided into two parallel subsystems: the aerodynamics subsystem and the direct force subsystem. The aerodynamics subsystem is designed employing classical control methodology, including the inner loop which adopt angular rate feedback to stabilizing the attitude, and the outer loop which track the guidance command, and the proper emendation nets are designed for each loop. The simulation results show that the available load and performance of transit response have improved obviously.4. To solve the problems caused by the varieties of the missile dynamics with the difference of flight height, velocity and attitude angle in modeling the missile, in this thesis, the theory of variable structure model reference adaptive control is used to design a pitch channel autopilot based on a longitudinal missile model, the status equation using the measurable parameters of load and angular rate is established, and the methodology to choosing the reference model is discussed also, and the performance of the controller is analyzed by means of simulation.5. Aiming at the specific mission that intercept the warhead of tactical ballistic missile, the new issue for designing the guidance law is analyzed, and a new guidance method that fit for the mid-course is presented, based on the idea of predicting the intercept point. To design a feasible terminal guidance law, the shortcoming existing in the proportional navigation when intercepting the warhead is firstly更多还原