Approach angle constrained and varying speed cooperative guidance against maneuvering targets

TY - JOUR

T1 - Approach angle constrained and varying speed cooperative guidance against maneuvering targets

AU - Ding, Xiangjun

AU - Wang, Jianan

AU - Liu, Junhui

AU - Shan, Jiayuan

N1 - Publisher Copyright: © 2025 China Ordnance Society. Publishing services by Elsevier B.V. on behalf of KeAi Communications Co. Ltd. This is an open access article under the CC BY-NC-ND license. http://creativecommons.org/licenses/by-nc-nd/4.0/

PY - 2026/3

Y1 - 2026/3

N2 - This paper addresses the three-dimensional (3-D) approach angle constrained cooperative guidance problem for speed-varying missiles against maneuvering targets. First, the guidance problem is formulated in a relative reference frame and a virtual control input is selected. Then, the cooperative guidance law is designed on the basis of a prediction-correction framework. The time-to-go under the baseline command is estimated by an efficient prediction method with a realistic aerodynamic model and a biased command is developed by utilizing the time-to-go predictions for synchronizing different missiles' impact times. The design of the biased command is decoupled into the individual design of its direction and magnitude. It is proved that the designed cooperative guidance law can make the time-to-go consensus error converge to zero before interception. Finally, the designed guidance law is validated through a series of numerical simulations.

AB - This paper addresses the three-dimensional (3-D) approach angle constrained cooperative guidance problem for speed-varying missiles against maneuvering targets. First, the guidance problem is formulated in a relative reference frame and a virtual control input is selected. Then, the cooperative guidance law is designed on the basis of a prediction-correction framework. The time-to-go under the baseline command is estimated by an efficient prediction method with a realistic aerodynamic model and a biased command is developed by utilizing the time-to-go predictions for synchronizing different missiles' impact times. The design of the biased command is decoupled into the individual design of its direction and magnitude. It is proved that the designed cooperative guidance law can make the time-to-go consensus error converge to zero before interception. Finally, the designed guidance law is validated through a series of numerical simulations.

KW - Approach angle constraint

KW - Cooperative guidance

KW - Maneuvering target

KW - Time-varying speed

UR - https://www.scopus.com/pages/publications/105023419293

U2 - 10.1016/j.dt.2025.09.030

DO - 10.1016/j.dt.2025.09.030

M3 - Article

AN - SCOPUS:105023419293

SN - 2096-3459

VL - 57

SP - 56

EP - 70

JO - Defence Technology

JF - Defence Technology

ER -