Homing missiles have gained wide popularity in the field of guidance and control regarding the short and medium range purposes in recent years.
Author: Bulent Ozkan
Publisher: LAP Lambert Academic Publishing
Homing missiles have gained wide popularity in the field of guidance and control regarding the short and medium range purposes in recent years. In this study, the three-dimensional formulation of the Proportional Navigation Guidance (PNG) law is done. Another contribution of this study is the derivation of the Linear Homing Guidance (LHG) and the Parabolic Homing Guidance (PHG) laws. Then, all these three methods are implemented on both the considered missile model for the uncanted and canted tail wing configurations, and a generic single-body missile model. Also, the acceleration, rate and angular autopilots are designed in order to realize the guidance commands generated by these guidance laws on the considered missile models. Finally, the overall guidance and control models are constructed by integrating the obtained models and then numerous computer simulations are carried out to test the performance of the system in different scenarios.
As a complementary part of the work, the design of a target state estimator is made as a first order fading memory filter. Finally, the entire guidance and control system is built by integrating all the models mentioned abo.
DYNAMIC MODELING, GUIDANCE, AND CONTROL OF HOMING MISSILES ÖZKAN, Bülent Ph. D., Department of Mechanical Engineering Supervisor: Prof. Dr. M. Kemal ÖZGÖREN Co-Supervisor: Dr. Gökmen MAHMUTYAZICIOÐLU September 2005, 236 pages In this study, the dynamic modeling, guidance, and control of a missile with two relatively rotating parts are dealt with. The two parts of the missile are connected to each other by means of a roller bearing. In the first part of the study, the governing differential equations of motion of the mentioned missile are derived. Then, regarding the relative rotation between the bodies, the aerodynamic model of the missile is constructed by means of the Missile Datcom software available in TÜBÝTAK-SAGE. After obtaining the required aerodynamic stability derivatives using the generated aerodynamic data, the necessary transfer functions are determined based on the equations of motion of the missile. Next, the guidance laws that are considered in this study are formulated. Here, the Linear Homing Guidance and the Parabolic Homing Guidance laws are introduced as alternatives to the Proportional Navigation Guidance law. On this occasion, the spatial derivation of the Proportional Navigation Guidance law is also done. Afterwards, the roll, pitch and yaw autopilots are designed using the determined transfer functions. As the roll autopilot is constructed to regulate the roll angle of the front body of the missile which is the controlled part, the pitch and yaw autopilots are designed to realize the command signals generated by the guidance laws. The guidance commands are in the form of either the lateral acceleration components or the flight path angles of the missile. Then, the target kinematics is modeled for a typical surface target. As a complementary part of the work, the design of a target state estimator is made as a first order fading memory filter. Finally, the entire guidance and control system is built by integrating all the models mentioned abo.
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.
Author: N A Shneydor
Category: Technology & Engineering
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
Most important, emerging from this work is a new structure for adaptive control and a unifying framework for developing midcourse and terminal homing missile guidance schemes under uncertainty.
The objective of this three year study is to develop robust and adaptive guidance and controls laws for homing missiles, mechanizable with near- future computer technology, which can satisfy system objectives in the presence of large uncertainties and nonlinearities. Over the past years, considerable progress has been made in resolving some of the fundamental issues in homing guidance. Of particular importance, new filter structures which were tailored to the passive homing engagement, and new target models and kinematic pseudo- measurements, which modified the new filter algorithm and induced a new adaptive homing guidance law, were developed. During the last three years in support of these important innovations, robust filters and control schemes which further enhance system performance were developed based upon a stochastic control problem known as the linear-exponential-Gaussian-problem and a related deterministic approach called the disturbance attenuation problem. Most important, emerging from this work is a new structure for adaptive control and a unifying framework for developing midcourse and terminal homing missile guidance schemes under uncertainty.
The integrated guidance-control law for homing missiles is obtained as a solution of finite-interval optimal control problems. The model of Reference  includes filter design as part of the integrated design process comprising design ...
Author: Rafael Yanushevsky
Publisher: CRC Press
Category: Technology & Engineering
Written by an expert with more than 30 years of experience, Modern Missile Guidance contains new analytical results, obtained by the author, that can be used for analysis and design of missile guidance and control systems. This book covers not just new methods nor is it merely a compilation of older methods, although it includes both. The book discusses, in a logical progression, with its clear elucidation of the guidance laws, the entire field from missile dynamics to modeling and testing missile guidance and control systems. In contrast to existing books that discuss very simple and often unrealistic guidance system models, this book presents missile guidance models that describe more precisely the dynamics of the missile flight control system, making analytical results more effective in practice. The analysis of missile guidance system models in the time-domain and in the frequency-domain allows the generation of different guidance laws that supplement each other. Taking modern, rigorous approach that leads to improved performance in missile guidance applications, the book examines new guidance laws, and corresponding algorithms for generating and testing these laws, and includes effective new software programs developed by the author. The author provides an innovative presentation of the theoretical aspects of modern missile guidance that quite possibly cannot be found in any other book. It delineates new ideas that, once crystallized, will significantly improve missile systems performance.
In: AIAA Guidance, Navigation and Control Conference, Keystone, CO, August 21-24, pp. 2006–6697. AIAA (2006) Chen, R.H., Speyer, J.L., Lianos, D.: Homing Missile Guidance and Estimation under Agile Target Acceleration.
Author: Daniel Choukroun
Category: Technology & Engineering
This book presents selected papers of the Itzhack Y. Bar-Itzhack Memorial Sympo- sium on Estimation, Navigation, and Spacecraft Control. Itzhack Y. Bar-Itzhack, professor Emeritus of Aerospace Engineering at the Technion – Israel Institute of Technology, was a prominent and world-renowned member of the applied estimation, navigation, and spacecraft attitude determination communities. He touched the lives of many. He had a love for life, an incredible sense of humor, and wisdom that he shared freely with everyone he met. To honor Professor Bar-Itzhack's memory, as well as his numerous seminal professional achievements, an international symposium was held in Haifa, Israel, on October 14–17, 2012, under the auspices of the Faculty of Aerospace Engineering at the Technion and the Israeli Association for Automatic Control. The book contains 27 selected, revised, and edited contributed chapters written by eminent international experts. The book is organized in three parts: (1) Estimation, (2) Navigation and (3) Spacecraft Guidance, Navigation and Control. The volume was prepared as a reference for research scientists and practicing engineers from academy and industry in the fields of estimation, navigation, and spacecraft GN&C.
AIAA J. of Guidance, Control and Dynamics 30, 804–815 (2007) Hu, Y., Ge, S., Su, C.: Stabilization of uncertain nonholonomic ... D.G., Radke, J.J., Mack, R.E.: Time-to-go prediction for homing missiles based on minimum-time intercepts.
Author: Yuanqing Xia
Category: Technology & Engineering
“Compound Control Methodology for Flight Vehicles” focuses on new control methods for flight vehicles. In this monograph, the concept of compound control is introduced. It is demonstrated that both Sliding Mode Control (SMC) and Active Disturbance Rejection Control (ADRC) have their own advantages and limitations, i.e., chattering of SMC and the observability of extended state observer (ESO), respectively. It is shown that compound control combines their advantages and improves the performance of the closed-loop systems. The book is self-contained, providing sufficient mathematical foundations for understanding the contents of each chapter. It will be of significant interest to scientists and engineers engaged in the field of flight vehicle control.
Author: United States. Bureau of Naval PersonnelPublish On: 1971
Table of weapon characteristics Weapon or projectile Propulsion incorporated Guidance - control system incorporated Vehicle Usual type of target Delivery unit Guidance - control system in vehicle Bomb release Aircraft gear . Rocket ...
The guidance system interprets the information and generates its own correction signals , which cause the missile to remain ... Homing guidance systems control the path of the missile by means of a device in the missile that detects and ...
Author: United States. Naval Education and Training CommandPublish On: 1977
The purpose of the homing section is to track the target and develop guidance signals . The TDD senses the presence of the target when it ... Two auxiliary - power supply ( APS ) gas generators 115 Chapter 4 - MISSILE GUIDANCE AND CONTROL.
Author: United States. Naval Education and Training Command
Battin , R. H. , and Vaughan , R. M. , “ An Elegant Lambert Algorithm , ” Journal of Guidance , Control , and Dynamics , Vol . 7 , Nov.- Dec. ... Modern Homing Missile Guidance , ” Journal of Guidance and Control , Vol . 4 , Jan. - Feb.
Author: United States. Bureau of Naval PersonnelPublish On: 1958
9 CHAPTER HOMING SYSTEM OF MISSILE GUIDANCE This is a continuation of the descriptions of guidance systems . ... The homing guidance group consists of general guidance control systems in which the path of the missile can be changed ...
Author: United States. Bureau of Naval PersonnelPublish On: 1959
Block diagram of guidance - control ... The missile containing this section is a semiactive homing weapon which employs Doppler radar ( the basic features of which are discussed in chapter 6 , GF 3 & 2 , NavPers 10379 ) .
STANDARD SHIPBOARD MISSILE Prime Contractors : Pomona Division of General Dynamics Corporation ( guidance , control and ... diameter .67 feet ; span over fins 3.3 feet ; launch weight 400 pounds ; guidance semi - active homing radar .
A missile guidance system for maintaining a missile in a such that a side surface and said trailing surface of said ... said guidance system including : ( a ) programmed guidance means for controlling said missile to said attitude ...
Optimal Controllers for Homing Missiles, Report No. RE-TR-68-15, U.S. * Command, Redstone Arsenal, Alabama, September 1968. nd Yang, C.C.; Analytical Solution of 3D Realistic True Proportional Navi|al of Guidance, Control, and Dynamics, ...
Author: George M. Siouris
Publisher: Springer Science & Business Media
Category: Technology & Engineering
Airborne Vehicle Guidance and Control Systems is a broad and wide- angled engineering and technological area for research, and continues to be important not only in military defense systems but also in industrial process control and in commercial transportation networks such as various Global Positioning Systems (GPS). The book fills a long-standing gap in the literature. The author is retired from the Air Force Institute and received the Air Force's Outstanding Civilian Career Service Award.
for advanced missile guidance systems ( AD - 782080 ) 23 p2883 N 74-34359 User's guide for a Monte Carlo point target terminal homing simulation program ( AD - 781992 ) 24 p 3002 N 74-35293 MISSILE DESIGN Solid propellant ballistic ...
J Guidance - Young - Bok Kim Dept of Marine Eng , Col of Xiao ( Sch of Elec and Electron Eng , Nanyang Control Dyn ... beam entire process also serves as a good case study for law for homing missiles guidance solutions is highlighted .