Guidance of a homing missile via nonlinear geometric control methods

Abstract

This paper examines the guidance problem of an acceleration constrained homing missile when the initial missile heading is far from intercept course. A guidance strategy based on the theory of feedback linearization is presented, and simulation results are given comparing miss distance performance of the feedback linearized guidance law to proportional navigation. It is demonstrated that the feedback linearized guidance law is a viable option under these conditions.

Proportional navigation guidance using predictive and time delay control

“…The PPNG law (16), under certain assumptions, exhibits similarity with some of the known guidance laws appeared in literature. Bezick et al (1995) have presented the design of input-output feedback linearizing homing guidance law based on the geometric control theory where the relative range R from missile to target, is chosen as output of the system (12). In the present case with LOS rate as output, one can show that the guidance law (16) is a special case of the input-output feedback linearizing control law.…”

“…This fact has given rise to various variants of PNG such as the augmented proportional navigation (Nesline & Zarchan, 1981), modified proportional navigation (Ha, Hur, Ko, & Song, 1990), switched bias proportional navigation (Babu, Sarma, & Swamy, 1994) and proportional navigation based on predictive control (Talole & Banavar, 1998) as well as many optimal guidance laws (Asher & Matuszewski, 1974;Speyer, 1976;Salmond, 1996;Zarchan, 1997) which are derived by employing the optimal control theory. Formulation based on the well-known feedback linearization approach (Bezick, Rusnak, & Grey, 1995) is another example of advanced guidance strategy proposed for tactical missiles engaging maneuvering targets.…”

Sliding Mode and Inertial Delay Control Based Missile Guidance

“…For example, a formulation of a homing guidance law based on the conventional PNG to impact a target with a desired attitude angle can be found in [7]. Apart from these, guidance law formulations based on some specific theories for tactical missiles engaging maneuvering targets can also be found in the literature, e.g., formulations based on optimal control theory [8][9][10][11][12] and feedback linearization [13].…”

Design of three-dimensional nonlinear guidance law with bounded acceleration command

“…Nevertheless, it needs accurate target acceleration information which is often unknown or poorly estimated in practical applications. To deal with highly maneuvering and agile targets in the absence of its acceleration, some new guidance laws based on nonlinear control method and robust control method have been proposed, such as Lyapunov-based nonlinear guidance laws [20,12,26], nonlinear geometric guidance laws [1,27], differential game guidance laws [19,29], nonlinear H ∞ guidance laws [24,25], L 2 gain guidance law [31], and sliding-mode guidance laws * Corresponding author. Tel.…”