A novel cooperative mid-course guidance scheme for multiple intercepting missiles

In the interception engagement,if the target movement information is not accurate enough for the mid-course guidance of intercepting missiles,the interception mission may fail as a result of large handover errors.This paper proposes a novel cooperative mid-course guidance scheme for multiple missiles to intercept a target under the condition of large detection errors.Under this scheme,the launch and interception moments are staggered for different missiles.The earlier launched missiles can obtain a relatively accurate detection to the target during their terminal guidance,based on which the latter missiles are permitted to eliminate the handover error in the mid-course guidance.A significant merit of this scheme is that the available resources are fully exploited and less missiles are needed to achieve the interception mission.To this end,first,the design of cooperative handover parameters is formulated as an optimization problem.Then,an algorithm based on Monte Carlo sampling and stochastic approximation is proposed to solve this optimization problem,and the convergence of the algorithm is proved as well.Finally,simulation experiments are carried out to validate the effectiveness of the proposed cooperative scheme and algorithm.     

GPS/INS系统航空制导炸弹半实物仿真系统研究

介绍了GPS/INS制导体制的航空制导炸弹半实物系统的关键技术、系统组成、功能以及半实物仿真系统的作用,可以应用于相同体制的半实物仿真试验室的建设和半实物仿真试验方案的设计。通过对某型制导炸弹半实物仿真方案设计和试验验证,充分验证了该仿真系统设计的正确性和可靠性。     

基于Radau伪谱方法的轨迹优化

研究了导弹在末制导阶段满足多约束条件下的轨迹优化问题。针对传统方法在处理复杂的非线性运动学、动力学约束上存在的困难,提出了一种基于Radau伪谱方法(RPM)的求解策略。首先,给出了考虑导弹速度和空气密度变化、终端和过程约束条件以及2种不同的性能指标函数的最优轨迹优化问题;其次,利用RPM将轨迹优化问题转化为非线性规划问题,采用序列二次规划算法求得最优解;最后,分2种初始条件对最大落角和最大终端速度的轨迹优化问题进行了仿真验证,结果表明:本文方法能够在较短的时间内生成一条满足多种约束要求的高精度的最优轨迹。     

Approach and landing guidance design for reusable launch vehicle using multiple sliding surfaces technique

An autonomous approach and landing (A&L) guidance law is presented in this paper for landing an unpowered reusable launch vehicle (RLV) at the designated runway touchdown.Considering the full nonlinear point-mass dynamics,a guidance scheme is developed in threedimensional space.In order to guarantee a successful A&L movement,the multiple sliding surfaces guidance (MSSG) technique is applied to derive the closed-loop guidance law,which stems from higher order sliding mode control theory and has advantage in the finite time reaching property.The global stability of the proposed guidance approach is proved by the Lyapunov-based method.The designed guidance law can generate new trajectories on-line without any specific requirement on off-line analysis except for the information on the boundary conditions of the A&L phase and instantaneous states of the RLV.Therefore,the designed guidance law is flexible enough to target different touchdown points on the runway and is capable of dealing with large initial condition errors resulted from the previous flight phase.Finally,simulation results show the effectiveness of the proposed guidance law in different scenarios.     

Distributed cooperative guidance for multiple missiles with fixed and switching communication topologies

This study investigates cooperative guidance problems for multiple missiles with fixed and switching directed communication topologies.A two-step guidance strategy is proposed to realize the simultaneous attack.In the first step,a distributed cooperative guidance law is designed using local neighboring information for multiple missiles to achieve consensus on range-to-go and leading angle.The second step begins when the consensus of multiple missiles is realized.During the second step,multiple missiles disconnect from each other and hit the target using the proportional navigation guidance law.First,based on the local neighboring communications,a sufficient condition for multiple missiles to realize simultaneous attack with a fixed communication topology is presented,where the topology is only required to have a directed spanning tree.Then,the results are extended to the case of switching communication topologies.Finally,numerical simulations are provided to validate the theoretical results.     

单兵火箭弹捷联导引滤波方法研究

为降低单兵制导火箭弹的成本,同时确保其具有较高的命中精度,进行了单兵火箭弹捷联导引滤波方法研究。首先,推导了视线角速度的解耦公式,去除了导引头测量信息中耦合的弹体姿态信息;然后,建立了视线运动方程和测量模型,为了解决测量信息与弹目距离和接近速度的弱相关性,使用一个时变Gauss-Markov随机向量代替视线运动方程中的非线性部分,采用UKF滤波方法得到可用于制导控制律设计的视线角速度的实时估计值;最后,通过正交仿真验证了所设计的单兵火箭弹捷联导引滤波方法的可行性。     

永磁同步电机弱磁与过调制控制策略研究

在前人研究的基础上,提出了一种提升永磁同步电机(PMSM)高速带载能力的控制策略。该控制策略能克服电机在最高转速时无法带载的弱点,可靠性高、易于实现。实现该控制策略的算法包含PMSM的弱磁控制和电压空间矢量的过调制控制,使电机能宽范围带载调速。为验证该控制策略,建立了内置式永磁同步电机(IPMSM)的仿真模型,搭建了试验平台,并进行了仿真和试验研究,验证了该控制策略的可行性和有效性。     

河南省实施创新驱动战略的问题与对策

河南省在人才素质、产业基础、资金投入、知识存量等创新资源方面存在不足，原因在于科研教育资源少、产业结构与创新资金投入体制不合理、知识创新激励机制不完善。提出了立足产业结构优化汇聚创新资源，依托三大载体，优化区域创新体系来实现创新驱动的战略框架，因此需要推进体制创新和基础平台创新、人才管理创新等。     

航空经济发展协同创新体系构建研究

郑州航空港经济综合实验区是一个全新的模式,在建设发展过程中,创新是关键。目前,实验区处于基础建设阶段,航空经济发展政产学研协同创新还面临着创新要素不足、效率不高、人才匮乏等问题,为此,做好航空经济发展协同创新体系顶层设计,还需要进一步推进创新要素集聚、打造协同创新生态、夯实协同创新基础、探索高校协同创新路径。     

超静定捆绑火箭传力路径的组合优化策略

为了获得新一代 大推力捆绑火箭捆绑方案的最优设计参数，针对超静定捆绑传力路径进行分析与优化设计。基于PATRAN的二次开发语言PCL对超静定捆绑火箭进行了参数化建模和仿真分析，并运用拉丁超立方试验方法对传力路径设计参数进行灵敏度分析。在此基础上提出了一种多目标粒子 群和序列二次规划算法的组合优化策略，确定了捆绑联接方案设计参数，实现了对捆绑联接装置和助推器结构载荷的高效优化。计算结果表明：组合优化策略能够将主捆绑联接结构的受力减少了30%左右，明显优于单独使用一种全局优化算法或局部优化算法的优化结果。本文研究成果将为新型捆绑火箭捆绑方案优化设计提供参考。