Author: Robert D. Broadston
Publisher:
ISBN: 9781423533528
Category :
Languages : en
Pages : 222
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Book Description
Current missile guidance laws are generally based on one of several forms of proportional navigation (PN). While PN laws are robust, analytically tractable, and computationally simple, they are only optimal in a narrow operating regime. Consequently, they may not optimize engagement range, time to intercept, or endgame kinetic energy. The advent of miniaturized high speed computers has made it possible to compute optimal trajectories for missiles using command mid-course guidance as well as autonomous onboard guidance. This thesis employs a simplified six degree of freedom (6DOF) flight model and a full aerodynamic 6DOF flight model to analyze the performance of both PN and optimal guidance laws in a realistic simulation environment which accounts for the effects of drag and control system time constants on the missile's performance. Analysis of the missile's kinematic boundary is used as the basis of comparison. A missile's kinematic boundary can be described as the maximum theoretical range at which it can intercept a target assuming no noise in its sensors. This analysis is immediately recognizable to the warfighter as an engagement envelope. The guidance laws are tested against non-maneuvering and maneuvering aircraft targets and against a simulation of a cruise missile threat. An application of the 6DOF model for a theater ballistic missile interceptor is presented.
Author: Yanjun Liang
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
The optimal control with exponential decay rate problem of the air-to-air missile system is studied. A nonlinear, coupling and uncertain dynamic model of the air-to-air missile with six degrees of freedom is considered. Because it is difficult to design the controller for the air-to-air missile control system, the nonlinear and coupling uncertain control system is simplified, and a linear model is obtained. Then, based on optimal control approach, an optimal controller with exponential decay rate is designed for the air-to-air missile. Numerical simulations illustrate the effectiveness of the proposed controller.
Author: N A Shneydor
Publisher: ISBS
ISBN: 9781904275374
Category : Science
Languages : en
Pages : 280
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Book Description
The continuing evolving capability of guided weapons demands ever more knowledge of their development. This modern and comprehensive book covers the control aspect of guidance of missiles, torpedoes, robots, and even animal predators, from the viewpoint of the pursuer. The text studies trajectories, zones of interception, the required manoeuvre effort, time of flight, launch envelopes, and stability of the guidance process. Mathematics at first-year university level is the only prerequisite. Acquaintance with feedback control theory would be helpful to the reader. Covers the control aspect of guidance of missiles, torpedoes, robots, and even animal predators, from the viewpoint of the pursuer Studies trajectories, zones of interception, the required manoeuvre effort, time of flight, launch envelopes, and stability of the guidance process
Author: Timothy J. Graves
Publisher:
ISBN:
Category :
Languages : en
Pages : 66
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Book Description
Optimal control theory is used to find the necessary conditions for maximizing the launch range of an air-to-air missile employing proportional navigation for guidance. Use of the first-order gradient technique provides an optimal solution for one- and two-dimensional intercept trajectories where thrust magnitude is the only control. A near-optimal, empirical method is developed and used for comparison. Results indicate that the launch range of the class of missiles considered is nearly insensitive to the thrusting schedule employed, suggesting that the low gain in launch range over present constant thrust methods may not warrant the increased complexity of an optimal design. Further, the results of the easier empirical method agree closely enough with the optimal method to suggest use of the empirical method in lieu of the gradient technique. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 514
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Book Description
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 168
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1050
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Book Description
Author:
Publisher:
ISBN:
Category : Guidance systems (Flight)
Languages : en
Pages : 168
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Book Description
In recent years, the development of high speed microcomputers makes it possible to apply optimal control theory to the missile guidance system. Although, numerous research papers have been published on this subject, hardly any of them deal with the concept of central guidance control. Here, an optimal central guidance principle that satisfies the needs of missiles with various speeds and guiding time is proposed. The major purpose of central guidance control is to guide the missile and enable it to maintain an optimal geometric position in relation to its target as soon as the target is locked on to by the missile head guidance. In order to reach the necessary maximum gravity force, the missile must have a certain minimum velocity which is contingent upon target's maximum gravity force, height and distance between them. For distant and low altitude targets the major factor is missile' speed. It's better to use a central guidance that can maximize the residual speed of the missile. For closer targets, the timing is very important, since the missile has to destroy the target before it launches a counter attack. Therefore, central guidance control that can minimize the intercepting time has to be applied. By solving the boundary value of nonlinear equations, these guidance rules can be obtained. Here, we will introduce the mathematical model of medium range air to air missiles, and discuss guidance principles of self searching. At the end, we will introduce the central guidance principle.
Author: Shaul Gutman
Publisher: AIAA (American Institute of Aeronautics & Astronautics)
ISBN:
Category : History
Languages : en
Pages : 328
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Book Description
This book is concerned with dynamical systems under a large uncertainty, and uses a min-max approach to achieve worst-case design. The book consists of two parts. The first part deals with robust control. It begines by developing linear controls to achieve relative stability (pole clustering) under parameter uncertainty. Surprisingly, the largest robustness radius in the parameter space is sometimes discontinuous (fragile) with respect to the control parameters. Then, the book discusses the control of nonlinear uncertain systems under matching conditions. The second part uses differential games to develop optimal guidance for homing missiles against maneuvering targets. The target maneuver is bounded, but otherwise, arbitrary. Using miss distance as the cost, the book develops closed form guidance laws, as well as miss distance formulae. In this way, the control loop (autopilot) and the guidance loop are coupled. A parameter study reveals the basic difference between minimum phase (canards) and non minimum phase (tail control) missiles. It also shows the influence of the autopilot parameters on the miss distance.
