A three-dimensional (3D) integrated guidance and control (IGC) design approach is proposed by using small-gain theorem in this paper. The 3D IGC model is formulated by combining nonlinear pursuer dynamics with the nonlinear dynamics describing pursuitevasion motion. Small-gain theorem and ISS theory are iteratively utilized to design desired attack angle, sideslip angle and attitude angular rates (virtual controls), and eventually an IGC law is proposed. Theoretical analysis shows that the IGC approach can make the LOS rate converge into a small neighborhood of zero, and the stability of the overall system can be guaranteed as well.
Cooperative Integrated Estimation-Guidance for Simultaneous Interception of Moving Targets
Intelligent Systems & Control (ISaC) Lab, Department of Aerospace Engineering, Indian Institute of Technology Bombay（智能系统与控制实验室，航空航天工程系，印度理工学院班加罗尔）；Guidance, Autonomy, Learning, and Control for Intelligent Systems (GALACxIS) Lab, Department of Aerospace Engineering and Engineering Mechanics, University of Cincinnati（智能系统引导、自主、学习与控制实验室，航空航天工程与工程力学系，辛辛那提大学）
Gain Scheduling LPV Control Scheme for the Autonomous Guidance Problem using a Dynamic Modelling Approach
1 Advanced Control Systems Group, Automatic Control Department, Universitat Polit\` e cnica de Catalunya (UPC), Rambla Sant Nebridi, 10, 08222, Terrassa, Spain 11pt 13.2pt This paper is a preprint of a paper submitted to IET Control Theory \& Applications. If accepted, copy of record will be available at the IET Digital Library.
Integrated Lander-Propulsion-GNC Framework for Autonomous Lunar Powered Descent
Turkuzaysan Inc.（Turkuzaysan公司）；Puura Inc.（Puura公司）；Final Proximity Space Systems Inc.（Final Proximity Space Systems公司）；TUBITAK Space Technologies Research Institute（TUBITAK空间技术研究研究所）
