面源红外诱饵对抗红外制导导弹干扰策略研究

面源红外诱饵使用的过程中,合理有效的干扰策略是干扰红外制导导弹的关键,针对这一问题,通过理论分析与仿真模拟相结合得到面源红外诱饵对抗红外制导导弹的干扰策略。首先以红外成像制导导弹为例,介绍红外制导导弹的仿真模型,然后将攻击过程分为锁定前与锁定后,以命中率为评价指标,得到两个阶段下的最佳干扰策略,包括诱饵的最佳释放时机、释放间隔以及载机应采取的机动动作等。     

Analytical impact time and angle guidance via time-varying sliding mode technique

To concretely provide a feasible solution for homing missiles with the precise impact time and angle, this paper develops a novel guidance law, based on the nonlinear engagement dynamics. The guidance law is firstly designed with the prior assumption of a stationary target, followed by the practical extension to a moving target scenario. The time-varying sliding mode (TVSM) technique is applied to fulfill the terminal constraints, in which a specific TVSM surface is constructed with two unknown coefficients. One is tuned to meet the impact time requirement and the other one is targeted with a global sliding mode, so that the impact angle constraint as well as the zero miss distance can be satisfied. Because the proposed law possesses three guidance gain as design parameters, the intercept trajectory can be shaped according to the operational conditions and missile׳s capability.To improve the tolerance of initial heading errors and broaden the application, a new frame of reference is also introduced. Furthermore, the analytical solutions of the flight trajectory, heading angle and acceleration command can be totally expressed for the prediction and offline parameter selection by solving a first-order linear differential equation. Numerical simulation results for various scenarios validate the effectiveness of the proposed guidance law and demonstrate the accuracy of the analytic solutions.     

Adaptive Dynamic Surface Control for Integrated Missile Guidance and Autopilot

Integrated guidance and control for homing missiles utilizing adaptive dynamic surface control approach is considered based on the three channels independence design idea.A time-varying integrated guidance and control model with unmatched uncertainties is first formulated for the pitch channel, and an adaptive dynamic surface control algorithm is further developed to deal with these unmatched uncertainties.It is proved that the proposed feedback controller can ensure not only the accuracy of target interception,but also the stability of the missile dynamics.Then, the same control approach is further applied to the control design of the yaw and roll channels.The 6-degree-of-freedom (6-DOF) nonlinear missile simulation results demonstrate the feasibility and advantage of the proposed integrated guidance and control design scheme.     

超音速巡航导弹飞行高度的串级控制与仿真

建立了超音速巡航导弹飞行高度的串级控制系统模型;利用最优参数整定法设计了副回路反馈补偿PD调节器;运用Matlab/Sisotool设计了主回路控制器.仿真结果表明,串级控制能较大程度地提高超音速巡航导弹飞行高度的控制性能.     

一种制导火箭炮弹的设计和技术探析

在分析国内外制导火箭炮弹研究现状的基础上,立足我军现有装备,提出了一种制导火箭炮弹的设计方案,确定了其工作原理,并对有关技术问题和系统设计建模与仿真方法进行了研究,对火箭弹制导化改造具有一定的参考价值。     

采用直接力的空空导弹越肩发射控制设计

针对空空导弹越肩发射的姿态控制需求,采用直接力控制装置,分别建立了小攻角模型和大攻角模型,利用滑模变结构控制方法设计了姿态控制律,所设计的控制律能够满足导弹越肩发射快速转弯的要求,仿真结果说明了此方法的有效性。     

大型导弹自排导热发射燃气流场研究

对大型导弹自排导热发射全过程的燃气流场进行了详细的仿真分析,揭示了发射过程的燃气流场规律,给出了发射过程导弹所受燃气温度和压力冲击的规律、时间及强度,仿真结果与试验结果吻合较好。研究表明,通过合理设计,大型导弹自排导热发射燃气流可通畅、顺利排导,作用在导弹的温、压载荷较小,时间较短,为大型导弹自排导热发射方式的可行性提供了研究依据。     

轴向高过载下固体推进剂结构完整性数值模拟

利用动力学有限元软件对轴向高过载状态下固体推进剂小变形时结构完整性进行了数值模拟。结果表明，最大轴向应力及应变均发生在固体推进剂和发动机接触区，周向及径向应力较小，但周向应变却相当可观。     

高超声速巡航飞行器振动建模及精细姿态控制

为保证超燃冲压发动机的良好进气环境,需要对高超声速巡航飞行器进行精细姿态控制,但弹性振动大大提高了精细姿态控制的设计难度。以高超声速巡航飞行器的纵向通道为例,文章分析弹性振动对飞行控制系统的影响,建立高超声速巡航飞行器的弹性模型,将精细姿态控制问题简化为超燃冲压发动机进气口当地攻角的精细控制问题,考虑机体/发动机耦合和气动热造成了气动参数和模态参数大范围摄动问题,基于H∞理论设计鲁棒控制系统。仿真表明,在考虑测量噪声、舵机非线性、参数大范围摄动的情况下仍然能够很好地跟踪刚体攻角,抑制弹性攻角,保证进气口当地攻角±0.6°的控制精度,满足高超声速飞行器精细姿态控制的要求。     

带视线角约束的多导弹有限时间协同制导律

针对多导弹在平面内从各自期望方向同时击中机动目标的问题,提出了一种带视线角约束且能打击机动目标的有限时间协同制导律。基于平面内的导弹-目标相对运动方程建立了考虑视线角约束的多导弹协同制导模型;在视线方向基于多智能体协同控制理论和积分滑模控制理论设计了多导弹分布式有限时间协同制导律,以保证所有导弹打击时刻有限时间趋于一致;在视线法向方向采用非线性干扰观测器对目标加速度在有限时间内进行估计,并基于有限时间滑模控制理论设计了带视线角约束的制导律,以保证导弹击中机动目标且其视线角有限时间内收敛到期望值。通过仿真验证了所设计的协同制导律可使多导弹从各自期望方向同时击中机动目标。