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李国飞 , 汤清璞 , 吴云洁 . 从飞行器无导引头的主-从式多飞行器协同制导方法 [J ] . 兵工学报 , 2023 , 44 ( 11 ): 3436 - 3446 . DOI: 10.12382/bgxb.2023.0678 http://doi.org/10.12382/bgxb.2023.0678 针对主-从式多飞行器多方位封锁协同打击目标问题,提出三维空间下当从飞行器无导引头时的协同制导方法。主飞行器通过给出的固定时间收敛攻击时间控制制导律实现对目标的指定时间命中,以主飞行器为基准提出球心和半径可动态自调整的目标封锁球面构型函数。以期望封控球面为参考,给出可实现对目标多方位覆盖封锁的同时命中协同制导律,并理论分析该方法的稳定性。仿真结果表明,新提出的方法可实现飞行器群于指定命中时刻同时命中目标,且主飞行器和无导引头的从飞行器可构成对目标的封锁态势。

LI G F , TANG Q P , WU Y J . Cooperative guidance method of leader and seeker-less follower flight vehicles [J ] . Acta Armamentarii , 2023 , 44 ( 11 ): 3436 - 3446 . (in Chinese) DOI: 10.12382/bgxb.2023.0678 http://doi.org/10.12382/bgxb.2023.0678 A three-dimensional cooperative guidance method is presented to investigate the problem of leader and seeker-less follower flight vehicles attacking on the targets by sector coverage. An impact time control guidance law with fixed-time convergence is presented for the leader to reach a target at desired impact time. A sector coverage configuration against target with dynamic self-adjusting center and radius is proposed with the leader as baseline. Finally,on the basis of the desired converge sector, the cooperative guidance law is given for the followers to reach the target simultaneously with multi-directional sector blockade. A theoretical analysis is given to prove the stability of the proposed method. The simulated results show that the proposed method can be used to make all the flight vehicles hit the target at appointed impact time, and the leader and the seeker-less followers can form the coverage situation towards the target.

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LI W , WEN Q Q , HE L , et al. Three-dimensional impact angle constrained distributed cooperative guidance law for anti-ship missiles [J ] . Journal of Systems Engineering and Electronics , 2021 , 32 ( 2 ): 447 - 459 . DOI: 10.23919/JSEE.2021.000038 http://doi.org/10.23919/JSEE.2021.000038 This paper investigates the problem of distributed cooperative guidance law design for multiple anti-ship missiles in the three-dimensional (3-D) space hitting simultaneously the same target with considering the desired terminal impact angle constraint. To address this issue, the problem formulation including 3-D nonlinear mathematical model description, and communication topology are built firstly. Then the consensus variable is constructed using the available information and can reach consensus under the proposed acceleration command along the line-of-sight (LOS) which satisfies the impact time constraint. However, the normal accelerations are designed to guarantee the convergence of the LOS angular rate. Furthermore, consider the terminal impact angle constraints, a nonsingular terminal sliding mode (NTSM) control is introduced, and a finite time convergent control law of normal acceleration is proposed. The convergence of the proposed guidance law is proved by using the second Lyapunov stability method, and numerical simulations are also conducted to verify its effectiveness. The results indicate that the proposed cooperative guidance law can regulate the impact time error and impact angle error in finite time if the connecting time of the communication topology is longer than the required convergent time.

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李东旭 , 王晓芳 , 林海 . 多高超声速导弹协同末制导律及可行初始位置域研究 [J ] . 弹道学报 , 2019 , 31 ( 4 ): 1 - 7 . DOI: 10.12115/j.issn.1004-499X(2019)04-001 http://doi.org/10.12115/j.issn.1004-499X(2019)04-001 针对多高超声速导弹以指定落角对目标进行饱和攻击的问题,提出一种具有攻击角度和攻击时间约束的末制导律,并基于此对导弹的末制导可行初始位置域进行研究。建立三维空间导弹运动模型,分别通过纵向通道和侧向通道制导指令实现落角和攻击时间控制,构成三维协同末制导律。考虑导弹过载和末速约束,采用上述制导律,以导弹末制导初始位置的坐标为设计变量,以实际攻击时间与理想攻击时间差为性能指标函数,建立并求解优化模型,得到导弹一维及二维可行末制导初始位置域。仿真结果表明:该三维协同制导律可使多导弹在同一指定时间以指定落角命中目标; 该位置域求解方法可求得给定约束条件下的各导弹末制导可行位置域。

LI D X , WANG X F , LIN H . Research on cooperative terminal guidance law and feasibleinitial position domain for multi-hypersonic missiles [J ] . Journal of Ballistics , 2019 , 31 ( 4 ): 1 - 7 (in Chinese). DOI: 10.12115/j.issn.1004-499X(2019)04-001 http://doi.org/10.12115/j.issn.1004-499X(2019)04-001 Aiming at the problem that multi-hypersonic missiles can realize saturation attack to the target with a specified impact angle,a terminal guidance law with constraints of impact angle and impact time was proposed,and the feasible initial position domain of terminal guidance of missiles was studied. A relative motion model of missiles in the three-dimensional space was established. The vertical and lateral guidance command was used to realize the impact angle control and the impact time control respectively,and a three-dimensional cooperative terminal guidance law was formed. Adopting the law,the constraints of final velocity and available overload of missiles were considered,and the initial position of terminal guidance of missiles was taken as a design variable,and the difference between the actual impact time and the ideal impact time was taken as the performance index function,and an optimization model was established. The model was solved to obtain one-dimensional and two-dimensional feasible initial position domains of terminal guidance of missiles. Simulation results show that the three-dimensional cooperative guidance law can make multiple-missiles hit the target at the designated impact time with the required impact angle,and the position domain solving-method can be used to obtain the feasible initial position domains for each missile under given constraints.