Sun M., Xu Q., Du S., Chen Z., Zhang D.
Nankai University, 300071 Tianjin, China; University of South Africa, Florida 1710, South Africa; Department of Automation and Intelligent Science, United States; Department of Electronic Science and Technology, Military Traffic Institute, United States; Department of Electrical and Mining Engineering, United States
Sun, M., Nankai University, 300071 Tianjin, China, Department of Automation and Intelligent Science, United States; Xu, Q., Nankai University, 300071 Tianjin, China, Department of Electronic Science and Technology, Military Traffic Institute, United States; Du, S., University of South Africa, Florida 1710, South Africa, Department of Electrical and Mining Engineering, United States; Chen, Z., Nankai University, 300071 Tianjin, China, Department of Automation and Intelligent Science, United States; Zhang, D., Nankai University, 300071 Tianjin, China, Department of Automation and Intelligent Science, United States, Department of Electronic Science and Technology, Military Traffic Institute, United States
A practical guidance and control strategy was presented to achieve a specified impact angle. The combined law includes a major part based on the line of sight and a supplementary part based on the line-of-sight rate. Mathematical manipulation verified that the pure guidance law with the line of sight has the specified terminal direction. The line-of-sight rate and the autopilot lag were used to raise the precision on the basis of the traditional three-loop acceleration control. The recursive estimation method was employed to check aerodynamic uncertainties. Comparative simulation results illustrated the effectiveness of the proposed method with the small navigation ratio.