A robust state dependent Riccati equation based guidance/control is investigated in this study. In order to have a better design tool in terms of required interceptor accelerations, the target intercept geometry is formulated in a set of polar coordinates. With this formulation, we formulate a cost function with state dependent weights. In this study, we investigate the effects of such cost functions on the levels of interceptor accelerations. We also synthesize a neural network based extra controller to achieve the robustness in the presence of the target acceleration. In this manner, we will not need target acceleration estimation explicitly in the guidance law.
S. N. Balakrishnan and M. Xin, "Robust State Dependent Riccati Equation Based Guidance Laws," Proceedings of the 2001 American Control Conference, 2001, Institute of Electrical and Electronics Engineers (IEEE), Jan 2001.
The definitive version is available at https://doi.org/10.1109/ACC.2001.946146
2001 American Control Conference, 2001
Mechanical and Aerospace Engineering
Keywords and Phrases
Riccati Equations; Control System Synthesis; Cost Function; Homing Missile Guidance; Intercept Geometry; Interceptor Accelerations; Missile Control; Missile Guidance; Neural Network Based Extra Controller; Neurocontrollers; Polar Coordinates; Robust Control; Robust State Dependent Riccati Equation Based Guidance Laws; State Dependent Weights
Article - Conference proceedings
© 2001 Institute of Electrical and Electronics Engineers (IEEE), All rights reserved.
01 Jan 2001