【作者】 郝波；

【导师】 谷良贤；

【作者基本信息】 西北工业大学 ， 飞行器设计， 2004， 硕士

【摘要】 本文主要研究了直接侧向力技术在大气层外动能拦截器和大气层内防空导弹中的应用。研究的内容及成果主要表现在以下几个方面： （一）直接侧向力在大气层外动能拦截器中的应用 首先确定了动能拦截器的总体方案，分别建立目标运动和动能拦截器运动的数学模型，以及轨控和姿控发动机的推力模型。根据导引律的实现方法和导引头的工作要求，设计了轨控和姿控发动机的控制规律。在此基础上对动能拦截器的拦截过程进行仿真，验证了动能拦截器对弹道导弹的直接命中能力。 （二）直接侧向力在大气层内防空导弹中的应用 1、针对防空导弹末端飞行失控问题，提出了建立末端直接侧向力控制的新思路。对直接侧向力最佳作用位置、最佳作用方式、最佳应用范围进行了分析。同时对防空导弹直接侧向力应用范例——美国的ERINT-1导弹侧向力特性进行了分析比较。 2、从半主动导引头副瓣波束影响、导引头最大跟踪角速度限制以及导弹响应延迟特性三个方面，分析了造成防空导弹末端失控的主要原因。并利用导引头失效前的状态建立了末端控制信号。 3、根据大量参考文献和试验数据，分析了侧向喷流的干扰特性，并给出不同状况下干扰因子K_cn的变化曲线，在上述工作的基础上，建立了带有姿控侧向力装置的防空导弹模型和弹道计算模型。 4、论文最后根据前面建立的数学模型，对防空导弹垂直转弯段、比例导引段以及末端直接力控制段进行了仿真计算，结果表明进行末端直接侧向力控制可以有效减小拦截目标时的脱靶量，提高命中精度。更多还原

【Abstract】 The main works of this thesis are research of the direct lateral force’s application, on the exoatmosphere kinetic-kill vehicle and on the inner-atmosphere airdefence missile. The main works and achievements are described:(1) The application of direct lateral force on the exoatmosphere kinetic-kill vehicle.At first, the collectivity project of the exoatmosphere kinetic-kill vehicle is specified, the motive model of the exoatmosphere kinetic-kill vehicle and target are constructed, and the thrust performance of trajectory-control engine and attitude-control engine are presented. According to the method of implementing the guidance law and the need of seeker, the control laws of trajectory and attitude control are designed. The terminal guidance procedure is simulated, and the results validated the capability of the exoatmosphere kinetic-kill vehicle to hit the target directly.(2) The application of direct lateral force on the inner-atmosphere airdefence missile.a. Aimed to solve problem of airdefence missile end control invalidation, a new idea of building direct lateral force control in terminal trajectory is presented, and the optimal action position, mode and range are analyzed. At the same time, the example of applying the direct lateral force-ERINT-1 (America)- is analyzed and compared.b. From analyzing the side, lobe, the angular velocity of sight line of autoloading seeker, and the response delay of missile, the main reasons of airdefence missile end control invalidation are made sure. According to the state of seeker before it work failed, the signal of end controlling is built.c. Based on a lot of referenced documents and tunnel experiment data, the phenomenon of lateral jet interception are analyzed, and the diagrams of the interaction factor ’Kcn’ is presented. Following, the airdefence Missile model, trajectory model including attitude-control direct lateral force are constructed.d. In the end of this thesis, on the basis of the mathematical model, three segments of trajectory: the vertical turn, the PN guidance and the direct lateral force control in terminal trajectory are simulated. The results show that with the direct lateral force control reduces in terminal trajectory, the miss-distance is reduced and the precision is improved.更多还原