Asymptotic Behaviour and Stability Problems in Ordinary Differential Equations. By L. Cesari. Pp. 271. DM. 68. 1959. (Springer, Berlin)

The missile guidance law utilizing variable structure control is proposed. The acceleration command input is determined considering the target acceleration as an uncertainty. The proposed guidance law uses only the information for the target acceleration bound; therefore, the precise measuring of target acceleration during the maneuver is not required, and the robustness to the target maneuver is achieved. It is also shown that the proposed guidance law can be classie ed into the augmented true proportional navigation or the augmented realistic true proportional navigation guidance law. Numerical simulations show that the proposed guidance law yields better performance compared to existing guidance laws. ROPORTIONAL navigation guidance (PNG) was e rst developed during the 1950s, and during the 1970s and 1980s various PNG laws such as pure proportional navigation (PPN), true proportional navigation (TPN), the optimal guidance law (OGL), generalized TPN (GTPN), and realistic TPN (RTPN) have been developed. 1;2 Lots of studies have been performed to obtain analytical solutions as well as to analyze the capture regions of the guidance laws. With the development of accurate avionic sensors, augmented proportional navigation (APN) and the predictive guidance law (PGL) utilizing the information about target acceleration were also proposed. By analyzing the various guidance laws, the characteristics of the guidance laws, capture regions, and pursuing performance were compared. 1;2

Design of Missile Guidance Law via Variable Structure Control

New missile guidance law is proposed via variable structure control. The acceleration command is determined considering the target acceleration information as uncertainty. Target and missile are assumed to be point masses moving in the two dimensional plane. According to the property of the missile acceleration command, the proposed guidance laws are classified into IPN type and RTPN type. Moreover, it is shown that the conventional proportional guidance laws can be derived from the proposed guidance law. Numerical simulation results show that the proposed guidance law exhibits better performance compared to the conventional proportional guidance laws.

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. aT L*A(r) LgLkfh(x) N'

Guidance of a homing missile via nonlinear geometric control methods

Optimal sliding-mode guidance with terminal velocity constraint for fixed-interval propulsive maneuvers

A coplanar pursuit-evasion game of kind in the atmosphere between a coasting pursuer and a maneuvering evader of constant speed is considered. The aerodynamic forces acting on the pursuer are modeled in two different forms: one for small and the other for large angles of attack. For both models the adjoint equations can be integrated analytically starting at the circular target set of the game. This allows one to determine the optimal strategies of the pursuer and the evader on the boundary of the capture set, called the "barrier." On the barrier the existence of singular surfaces for the evader are observed. A representative example of barrier trajectories starting oh the dispersal surface is given.

Qualitative study of a planar pursuit evasion game in the atmosphere

A horizontal pursuit-evasion game of kind in the atmosphere between a coasting pursuer with a final velocity constraint and a maneuvering evader of constant speed is considered. For this model, which is suitable to describe short range missile engagements, the adjoint equations can be integrated analytically. This allows us to determine the optimal strategies of the players on the boundary of the capture set, called the barrier, as a function of the current and final values of the state variables. The main effect of the pursuer's final velocity constraint, an important realistic parameter, neglected in previous studies, is a substantial reduction of the capture zone. However, based on this game solution, a feedback guidance law, suitable for real-time implementation, can be synthesized and compared to other guidance laws. The results show that the corresponding capture set is much larger than the firing envelope of a similar missile guided by proportional navigation with the same final velocity constraint.

M. Guelman

Papers

Qualitative study of a planar pursuit evasion game in the atmosphere

Game Optimal Guidance Law Synthesis for Short Range Missiles

Guidance for asteroid rendezvous