This work focuses on a study of missile guidance in the form of trajectory shaping of a generic cruise missile attacking a fixed target which mu ·t be struck from above. The problem is reinterpreted using optimal control theory resulting in two formulations: I ) minimum time-integrated altitude and 2) minimum flight time. Each formulation entails nonlinear, two-dimensional missile flight dynamics, boundary conditions and path constraints. Since the thus obtained optimal control problems do not admit analytical solutions, a recourse to computational optimal control is made. The focus here is on informed use of the tools of computational optimal control, rather than their development. Each of the formulations is solved using a three-s...
This paper describes a missile guidance problem in which the objective is to guide an interceptor mi...
The inadequacy of the traditional sliding mode variable structure (SMVS) control method for cruise m...
Optimal control theory is applied to the study of missile evasion, particularly in the case of a sin...
This work focuses on a study of missile guidance in the form of trajectory shaping of a generic crui...
Numerical solution of constrained nonlinear optimal control problem is an important field in a wide ...
This paper presents trajectory shaping of a surface-to-surface missile attacking a fixed with termin...
This dissertation investigates advanced concepts in terminal missile guidance. The terminal phase of...
This dissertation studies the optimal guidance of homing missiles. The guidance objective is to dete...
This study outlines the set of equations constituting the necessary conditions that should be solved...
In Part I, a method is developed for determining the optimal control laws for a class of aerodynamic...
Recently, several authors have studied the problem of trajectory redesign for hypersonic aircraft. T...
This paper describes a missile guidance problem in which the objective is to guide an interceptor mi...
Optimal control will be used to derive four guidance laws for the purpose of defending an aircraft f...
The paper presents a near-optimal guidance law that has been developed using the direct method of ca...
Abstract lem. This paper describes two new types of deterministic optimal stopping control problems:...
This paper describes a missile guidance problem in which the objective is to guide an interceptor mi...
The inadequacy of the traditional sliding mode variable structure (SMVS) control method for cruise m...
Optimal control theory is applied to the study of missile evasion, particularly in the case of a sin...
This work focuses on a study of missile guidance in the form of trajectory shaping of a generic crui...
Numerical solution of constrained nonlinear optimal control problem is an important field in a wide ...
This paper presents trajectory shaping of a surface-to-surface missile attacking a fixed with termin...
This dissertation investigates advanced concepts in terminal missile guidance. The terminal phase of...
This dissertation studies the optimal guidance of homing missiles. The guidance objective is to dete...
This study outlines the set of equations constituting the necessary conditions that should be solved...
In Part I, a method is developed for determining the optimal control laws for a class of aerodynamic...
Recently, several authors have studied the problem of trajectory redesign for hypersonic aircraft. T...
This paper describes a missile guidance problem in which the objective is to guide an interceptor mi...
Optimal control will be used to derive four guidance laws for the purpose of defending an aircraft f...
The paper presents a near-optimal guidance law that has been developed using the direct method of ca...
Abstract lem. This paper describes two new types of deterministic optimal stopping control problems:...
This paper describes a missile guidance problem in which the objective is to guide an interceptor mi...
The inadequacy of the traditional sliding mode variable structure (SMVS) control method for cruise m...
Optimal control theory is applied to the study of missile evasion, particularly in the case of a sin...