An approach to integrated guidance/autopilot design is considered in this study. It consists of two parts: 1) recognizing the importance of polar coordinates to describe the end game in terms of problem description and measurement acquisition, the terminal guidance problem is formulated in terms of polar coordinates; 2a) through the use of the state transition matrix of the intercept dynamics, a closed form solution for the transverse command acceleration is obtained; and 2b) through a commonly used approximation on time-to-go and a coordinate transformation, a family of proportional navigation optimal guidance laws is obtained in a closed form. A typical element of such a guidance law is combined with the autopilot dynamics to result in a feedback control law in terms of output variables
S. N. Balakrishnan et al., "Analytical Guidance Laws and Integrated Guidance/Autopilot for Homing Missiles," Proceedings of the 2nd IEEE Conference on Control Applications, 1993, Institute of Electrical and Electronics Engineers (IEEE), Jan 1993.
The definitive version is available at https://doi.org/10.1109/CCA.1993.348311
2nd IEEE Conference on Control Applications, 1993
Mechanical and Aerospace Engineering
Keywords and Phrases
aerospace control; autopilot dynamics; closed form solution; feedback; feedback control; homing missiles; integrated guidance/autopilot; intercept dynamics; matrix algebra; measurement acquisition; missiles; navigation; polar coordinates; problem description; proportional navigation optimal guidance; state transition matrix; terminal guidance; transverse command acceleration
Article - Conference proceedings
© 1993 Institute of Electrical and Electronics Engineers (IEEE), All rights reserved.