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Cooperative guidance issues with impact time consensus against a maneuvering target are considered in this article. Different from the existing achievements, the expected impact time does not need to be predesigned, which is coordinated by multiple missiles using the neighboring information. First, the impact time consensus command is generated by using the maximum consensus algorithm of time-to-go for each missile. Second, an analytical cooperative guidance law with bias proportional guidance form is proposed for achieving impact time consensus. In addition, the convergence and the stability of the proposed algorithm and guidance law are analyzed. Third, an equivalent guidance experimental platform is constructed for testing the performance of the proposed cooperative guidance strategy. Finally, the numerical simulation and experimental results are presented to verify the effectiveness of the proposed theoretical cooperative guidance methods.
Yu et al. (Wed,) studied this question.