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International Journal of Aerospace Engineering
Volume 2016, Article ID 6136178, 14 pages
Research Article

A New Impact Time and Angle Control Guidance Law for Stationary and Nonmaneuvering Targets

School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Received 25 January 2016; Accepted 2 August 2016

Academic Editor: Wen Bao

Copyright © 2016 Zhe Yang et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


A guidance problem for impact time and angle control applicable to cooperative attack is considered based on the sliding mode control. In order to satisfy the impact angle constraint, a line-of-sight rate polynomial function is introduced with four tuning parameters. And the time-to-go derivative with respect to a downrange orientation is derived to minimize the impact time error. Then the sliding mode control surface with impact time and angle constraints is constructed using nonlinear engagement dynamics to provide an accurate solution. The proposed guidance law is easily extended to a nonmaneuvering target using the predicted interception point. Numerical simulations are performed to verify the effectiveness of the proposed guidance law for different engagement scenarios.