A Method Of Increasing The Kinematic Boundary Of Air To Air Missiles Using An Optimal Control Approach

Author : Robert D. Broadston
Publisher :
ISBN 13 : 9781423533528
Total Pages : 222 pages
Book Rating : 4.26/5 ( download)

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Download or read book A Method of Increasing the Kinematic Boundary of Air-to-Air Missiles Using an Optimal Control Approach written by Robert D. Broadston and published by . This book was released on 2000-09-01 with total page 222 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 : Ashley Trent
Publisher :
ISBN 13 :
Total Pages : 18 pages
Book Rating : 4.45/5 ( download)

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Download or read book Trajectory Generation Using a Modified Simple Shooting Method written by Ashley Trent and published by . This book was released on 2004 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: Recently, several authors have studied the problem of trajectory redesign for hypersonic aircraft. The usual procedure for solving such problems is to set it up as a constrained optimal control problem. Lu and Schierman used direct methods to numerically solve the optimal control problems. Alternatively, one could use Pontryagin's Minimum Principle to obtain first-order necessary conditions for the optimal control problem and obtain a two-point boundary-value problem (TPBVP). Originally created to solve two-point boundary value problems (TPBVPs), the Modified Simple Shooting Method (MSSM) has been shown to be superior, both in speed and accuracy, to known methods for solving TPBVPs. Since optimal control problems can be formulated with differential equations and boundary conditions, it seems feasible to propose that the MSSM could be used to solve problems in optimal control. Here, the original MSSM algorithm was altered and used in conjunction with Pontryagin's Minimum Principle in an attempt to solve an optimal control problem in trajectory generation. In this paper, the authors consider the problem of trajectory redesign of the unpowered reentry phase for a hypersonic air vehicle. They consider outer loop equations governing the motion of the center of mass and consider the angle of attack to be the input variable. The lift and drag forces for the aircraft considered were obtained from a polynomial neural network approximation of experimental data. Effector deflections were chosen so that the aircraft Underwent trimmed flight. (6 figures, 7 refs.).

Author : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher :
ISBN 13 :
Total Pages : 168 pages
Book Rating : 4.57/5 ( download)

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Download or read book Guidance and Control Aspects of Tactical Air-launched Missiles written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development and published by . This book was released on 1980 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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ISBN 13 :
Total Pages : 514 pages
Book Rating : 4.77/5 ( download)

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Download or read book International Aerospace Abstracts written by and published by . This book was released on 1996 with total page 514 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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ISBN 13 :
Total Pages : 892 pages
Book Rating : 4.48/5 ( download)

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Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.04/5 ( download)

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Download or read book The Optimal Central Guidance of Medium Range Air-to-Air Missile written by and published by . This book was released on 1995 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 : Henry F. Eide
Publisher :
ISBN 13 :
Total Pages : 50 pages
Book Rating : 4.16/5 ( download)

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Download or read book Results of Some Investigations of Differential Gain Theory Applied to Air-to-Air Systems. Volume IV. Intercepting an Accelerating Target Using Quasi-Optimal Control for Air-to-Air Systems written by Henry F. Eide and published by . This book was released on 1975 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The technique of quasi-optimum control, developed by B. Friedland is applied to the problem of intercepting an accelerating target with an air launched missile. The problem is first stated as an optimal control problem with non-linear system equations and a quadratic cost functional. Several techniques of finding feedback type optimal controls which have been developed by solving various approximations to the original problem are then described. None of these techniques makes explicit use of a measurement of lateral target acceleration. Three control techniques are then developed which use measurements of target acceleration to develop closed form controls. The first control is found by solving a linearized version of the original problem. The other two controls are quasi-optimum controls which use the solution of the linearized problem to obtain a new feedback type solution that is more nearly optimal for the original problem. Based on performance in simulations of typical attack geometries and target maneuvers, these three control techniques are found to be superior to previous techniques.

Author :
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ISBN 13 :
Total Pages : 354 pages
Book Rating : 4.15/5 ( download)

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Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1993 with total page 354 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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ISBN 13 :
Total Pages : 570 pages
Book Rating : 4.18/5 ( download)

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Download or read book Safety Science Abstracts Journal written by and published by . This book was released on 1978 with total page 570 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Author : LaVerne E. Leistikow
Publisher :
ISBN 13 :
Total Pages : 183 pages
Book Rating : 4.91/5 ( download)

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Download or read book Optimum Control of Air to Surface Missiles written by LaVerne E. Leistikow and published by . This book was released on 1967 with total page 183 pages. Available in PDF, EPUB and Kindle. Book excerpt: Design guidelines were developed to provide a basis for conducting design trades for a homing type air-to-surface missile with high terminal accuracy. Three basic homing guidance concepts, proportional, pursuit, and optimal guidance were evaluated on the basis of impact error. Two nominal trajectories were investigated. An optimal guidance law was developed for an ASM with realistic aerodynamic and sensor characteristics. This guidance law was based upon the use of a Kalman filter to obtain best estimates of the ASM state variable errors, and a control concept which minimizes the sum of the mean square impact error and the integral of a quadratic form of the autopilot control variables. A linearized differential equation program which computed the mean square impact error in the form of a covariance matrix deviation perpendicular to the nominal trajectory, was used for comparison of the guidance laws. A normal acceleration autopilot was designed to meet the mission requirements, and advanced bistable controller techniques were applied to obtain a quasi-adaptive autopilot which required no gain changes throughout the ASM midcourse and terminal phases. A limited state-of-the-art survey was conducted of homing and inertial sensors, and on-board digital computers suitable for a homing ASM.