【作者】 苗静；

【导师】 姚郁；

【作者基本信息】 哈尔滨工业大学 ， 控制科学与工程， 2011， 硕士

【摘要】 动能拦截器采用直接侧向力/气动力复合控制,为导引头的视线转率提取带来了新的问题。一方面,直接侧向力的冲击作用不仅会引起弹体的弹性振动,还会使弹体姿态剧烈变化,使所提取的视线转率信息中包含的弹体姿态耦合误差增加,甚至导致导引头丢失目标。另一方面,高精度的末端控制要求在直接侧向力开启前导引头能够有效测量,进而提高了导引头跟踪系统的带宽要求。为此,本文针对直接侧向力/气动力复合控制带来的测量问题,对制导信息的提取进行了以下几方面的研究:首先,针对弹体弹性振动问题,以欧拉自由梁模型为基础,采用振型叠加法研究了弹体的弹性形变和质点振动加速度,提出了弹性附加角速率的概念,并指出了弹性效应加剧了导引头伺服稳定系统中质量偏心干扰力矩对测量的影响。其次,针对弹体姿态的快速变化问题,建立了直接侧向力作用下的弹体姿态控制模型,从系统传递函数的角度研究了弹体姿态角速率的频率特性,创新性地定义了λ-能量分布范围,并给出了求解弹体姿态角速率λ-能量分布范围的方法。再次,针对动能拦截器对导引头系统带宽的要求,采用线性化方法分析了末制导系统的带宽,进而提出了对随动平台式导引头角跟踪回路的带宽指标。然后,对平台式导引头的跟踪特性和去耦特性进行了分析,并提出了对回路设计的要求。最后,结合弹体姿态干扰特性和跟踪带宽指标,采用多回路思想,设计了导引头稳定平台跟踪系统,并通过基于库伦摩擦+粘滞摩擦模型的摩擦补偿,提高了视线转率信息的提取精度。本文较全面地分析了直接侧向力/气动力复合控制导弹制导信息提取的特殊问题,并在此基础上进行了去耦设计,对提高制导信息提取精度和实现高精度拦截具有较强的指导意义。更多还原

【Abstract】 Dual control of lateral jets and aerodynamic fins is used in kinetic kill vehicles, bringing new problems to line of sight rate extraction from seeker. On the one hand, thrust reaction of lateral jets will cause not only the elastic vibration of the missile body, but also significant change of missile attitude, which increases decoupling error of the extracted line of sight rate or even cause the miss of the target. On the other hand, high precision end-game control of homing guidance requires the seeker measuring effectively before lateral jets ignite, which raises the level of bandwidth of seeker’s tracking loop. Therefore, extraction of terminal guidance information is focused in this dissertation considering about the end-game measuring problem caused by dual control of lateral jets and aerodynamic fins. The main contributions are the following:Firstly, for the elastic vibration problem, dynamic responses and vibration acceleration of missile body are investigated with the superposition method of mode of vibration based on Euler- Bernoulli beam, and an additional angle rate caused by flexibility is also defined. According to the research, it is indicated that elastic effect increases influence of mass eccentricity disturbance torque in stabilized platform of seeker.Secondly, considering the significant change of missile attitude, jets control model of missile attitude is established, according to which, frequency characteristic is investigated from the perspective of system transfer function, aλ-energy frequency distribution range is defined creatively and a method of calculating it is given for missile body attitude changing rate.Thirdly, considering bandwidth requirement of seeker’s tracking loop, linearization method is used to analyze bandwidth of terminal guidance system by which bandwidth index of tracking loop of seeker is proposed.Fourthly, tracking and decoupling ability is analyzed according to the model of seeker with stabilized platform to present the requirement of control design.At last, tracking system of seeker with stabilized platform is designed using multi-loop method combining missile attitude disturbance characteristic and tracking bandwidth index. Friction compensation is designed based on the coulomb friction plus viscous friction model to improve the precision of line of sight extraction.The special problems of terminal guidance information extraction caused by dual control of lateral jets and aerodynamic fins are focused in this dissertation comprehensively. Analysis and designs are done to improve precision of terminal guidance information measuring. Schemes and conclusions proposed have instructional significance to high precision end-game interception.更多还原