The primary objective of this analysis is observing the behaviors of state variables, such as the angleofattack, velocity, and flight path angle, during the agile turn. Software tools for nonlinear missile autopilot design. The aim of this paper is to design autopilot with aerodynamics surfacesfinand thrust vector control by system characteristics reflection. High performance control of nonlinear systems requires the design of advanced, nonlinear control systems, such as those used in autopilot design. This report considers the derivation of the mathematical models for a missile autopilot in state space form. Design of missile threeloop autopilot pitch using pid controller. A tactical skid to turn missile autopilot is designed and implemented using a two step design process that results in an optimal output feedback with a fixed, low order dynamic compensator for reduced design and implementation cost. The missile plant model is characterized by a linear fractional transformation lft representation. Ahari a1, torabi a, karsaz a2 khorasan institute of higher education, mashhad, iran corresponding author.
In these robust control designs, a set of controllers each satisfying. Due to the wide parameter variation and stringent performance requirements, missile autopilot design is a challenging task. Shamma university of texas at austin, austin, texas 78712 and james r. Gainscheduled missile autopilot design using linear parameter varying transformations jeff s. Autopilot design for agile missile using timevarying control. Pdf controller design for a twoloop missile autopilot. Air force armament directorate, eglin air force base, florida 32542 this paper presents a gainscheduled design for a missile longitudinal autopilot. Introduction this paper presents the application of an l1 adaptive output feedback controller to longitudinal autopilot design for a missile in the presence of uncertainties in system dynamics.
Background on the application of feedback linearization technique to missile autopilot problem can be found in references. Design, modeling, guidance and control of a vertical launch surface to air missile submitted by raziye tekin in partial fulfillment of the requirements for the degree of master of science in electrical and electronics engineering department, middle east technical university by, prof. Box 353, yuseong, daejeon, 305600, republic of korea abstract. For aerodynamically controlled skid to run missile, the autopilot activates to move the controlsurfaces i. Comparisons of the design approaches and results are also discussed. Autopilot design for agile missile using timevarying. Missile autopilot design using artificial neural networks. Design of a roll autopilot for a skidtoturn guided missile. A number of nonlinear control methods have also been proposed for the missile autopilot design. Pdf this paper presents the airtoair missile autopilot design for a 180 heading reversal maneuver during boostphase. Dynamic matrix flight control design for a nonlinear missile autopilot a. This research work is an attempt towards achieving an approach for designing pi and pid controllers for a two loop missile autopilot system in pitch plain.
Paper open access design of a roll autopilot for a skidto. The reaction jet can improve the response speed, but the structure of control system becomes more complex. Robust nonlinear design of three axes missile autopilot. Then, a frequency domain loop shifting method is used to derive an h. The design is based on a much more general and realistic missile model compared to the plethora of nonlinear. Full envelope missile autopilot design using gain scheduled. Integrated design of the flight vehicle systems is an emerging trend within the aerospace industry.
Missile, threeloop auto pilot, pitch plane, pid controller. In this example the autopilot structure is a three loop design using measurements from an accelerometer placed ahead of the center of gravity, and a rate gyro to provide additional damping. Pdf design of a missile autopilot using adaptive nonlinear. Tactical missile autopilot design using nonlinear control. Robust nonlinear design of three axes missile autopilot via. Design and flight test of a robust autopilot for the irist airtoair missile control engineering practice, vol. Second, considering the discrete property of the lateral pulse jet thrusters and the. Mracek, cp, cloutier, jr missile longitudinal autopilot design using the statedependent riccati equation method. Integrated design of agile missile guidance and autopilot systems p. Computeraided synthesis of nonlinear autopilots for missiles. The text combines detailed examination of key theories with practical coverage of methods for advanced missile guidance control systems. In this paper, a flight path rate demand two loop autopilot in pitch plane called lateral autopilot is considered where the steady state gain of the autopilot system is nonunity. The missile autopilot design is formulated in section 3.
This paper presents a robust nonlinear autopilot design method based on dynamic inversion and pi control law. Design of a missile autopilot using adaptive nonlinear dynamic inversion conference paper pdf available in proceedings of the american control conference february 2005 with 97 reads. An autopilot is a closed loop system and it is a minor loop inside the main guidance loop. International journal of advances in engineering and. In 4, the wellknown h1 control method is incorporated into the gainscheduling approach in order to simplify the gainscheduling procedure. Short range missile autopilot design using fuzzy control. A systematic design methodology for the linear design of a lateral two loop autopilot for a class of guided missile which controls the lateral acceleration of the missile body using measurement from an accelerometer for output feedback and from a rate gyro to provide additional damping has been presented in 1. Dynamic matrix flight control design for a nonlinear. The results show that the application of robust control techniques to the design of missile autopilots can improve the performance and stability robustness characteristics. In this dissertation, a nonlinear autopilot design for a medium range bank to turn airtoair missile is presented. This report considers the derivation of the mathematical model for a missile autopilot in state space form.
Longitudinal nonlinear adaptive autopilot design for missiles. In 4, a power series expansion based method was used in the. Missile longitudinal autopilot design using a new suboptimal. International conference on nonlinear problems in aviation and aerospace 1st, daytona beach, fl, may 1996, pp. Robust missile autopilot design using dynamic inversion and. Three loop lateral missile autopilot design in pitch plane. In the design and stability analysis of our autopilot, we assume perfect rollstabilization but consider. Nonlinear missile autopilot design with thetad technique article pdf available in journal of guidance control and dynamics 273. Pdf a computeraided design software package for nonlinear control synthesis is discussed. Longitudinal nonlinear adaptive autopilot design for. Therefore how to design control strategy properly is an urgent problem. Introduction the missile flight control system is one element of the overall homing loop2.
In order to motivate numerical approach to the feedback linearization method, the following will provide a brief outline of the technique. Paper open access implementation and validation of. Generally, no sin gle autopilot design can stabilize the missile and provide the performance required over the entire desired flight envelope. Robust h autopilot design for agile missile with time. Ha, missile autopilot design via functional inversion and timescaled transformation, ieee trans. For highly agile missile systems, other robust control methodologies were applied to the design of missile autopilot based on h. Constrained missile autopilot design based on model. Many nonlinear control methods have been proposed for the missile autopilot. Guided missile, autopilot, linear quadratic design, full state feedback. Pdf missile autopilot design for agile turn control during boost. The uncertainties include parametric variations in the transfer function and timevarying disturbances. The missile data used for the proposed system was of three loop autopilot. The aim of the missile autopilot is to control acceleration normal to the missile body. Analysis and design of missile two loop autopilot semantic.
Integrated design of agile missile guidance and autopilot. Design of missile autopilot with aerodynamic lift and. For each of the above cases, the normal acceleration command missile autopilot is evaluated using both time and. Request pdf a robust adaptive control approach to missile autopilot design the huge developments in computational capabilities facilitate the design and implementation of adaptive and robust. A two loop autopilot configuration has been chosen which is characterized by a dynamics. In 2, linear matrix inequalities are used to propose a systematic gain scheduling autopilot design that accommodates mass variation. In 1, a robust pole placement technique is used for an autopilot design.
Pdf controller design for a twoloop missile autopilot in. The present work is an attempt to achieve a unity steady state gain of the autopilot system which generates a flight path rate output for a flight path rate command. The key to the autopilot design is the decoupling of the missile maneuvers into lateral and longitudinal components and performing them sequentially while maintaining zero sideslip angle. L1 adaptive controller for a missile longitudinal autopilot. Missile longitudinal autopilot design using the statedependent riccati equation method. Missile autopilot designs considering both rigidbody dynamics and elasticbody dynamics are presented. Missile autopilot design via x y z functional inversion and. The basic equations defining the airframe dynamics are non. Threeaxis autopilot design for a high angleofattack missile using mixed h 2 h. The fundamental problem of feedback linearization technique is not able to cater the model uncertainty. Pdf nonlinear missile autopilot design with thetad. Robust missile longitudinal autopilot design based on. Pdf software tools for nonlinear missile autopilot design.
An autopilot is a system of equations that takes commands and missile state measurements as inputs and computes a control command that stabilizes the missile and forces the missile state to track the command command autopilot actuator airframe sensors the combination of autopilot, actuator, airframe, and sensors is sometimes called the autopilot. Its now at helpsimulinkslrefdesigningaguidancesysteminmatlabandsimulink. Embryriddle aeronautical university press, 1996, pp. Robust missile autopilot design using dynamic inversion. The key to the autopilot design is the decoupling of the missile maneuvers into lateral and longitudinal components and performing them. Khargonekar 1998 missile autopilot design using hoc control with gain scheduling and dynamic inversion. A generic approach to missile autopilot design using state. Implementation and validation of autopilot design for vertical missile systems. Agile missile autopilot design using nonlinear backstepping. Design of a missile autopilot using adaptive nonlinear. Additional details onmissile autopilot design processusingthe feedback linearization method. The present work is concerned with improving the performance of an antitank guided missile system belonging to the first generation via adaptive synthesis of guidance systems. This report also considers a locally linearised state space model that.
Pdf missile design and systems engineering download full. A robust adaptive control approach to missile autopilot design. Modeling and simulation of advanced nonlinear autopilot. Missile autopilot design via functional inversion and timescaled transformation jaehyuk oh injoong ha seoul national university this paper presents a new approach to acceleration control of stt skidtoturn missiles. Control international journal of aeronautical and space sciences, vol. Antitank short range missiles can be categorized in the most widely used weapons in the recent ground battle field. The generic approach developed in this study for autopilot design can be easily extended to even more general cases, such as advanced missile control problems with thrust vectoring and reaction jets, and even other flight control design problems using the general form of the 6dof rigidbody equations of motion in the design of statedependent.
Multiinput multioutput nonlinear autopilot design for. The block diagram of the proposed control system with required controller gains is. Missile autopilot design by projective control theory metu. Dynamic inversion di was used for the innerloop design in. Designing a guidance system in matlab and simulink matlab. Department of guidance, military technical college, cairo, egypt. Journal of guidance, control, dynamics, 21, 234243. Download pdf tacticalmissiledesign free online new. Robust h autopilot design for agile missile with timevarying. It analyzes autopilot designs, seeker system designs, guidance laws and theories, and the internal and external disturbances affecting the performance factors of missile guidance control systems. The online system identification is required to complete the cycle of adaptive autopilot design.
First a new autopilot design model is presented for the interceptor missile with the blended aerodynamic lift and reaction jet. Missile autopilot design via x y z functional inversion. Pdf nonlinear missile autopilot design with thetad technique. Mathematical models for a missile autopilot design dtic. Currently, there are major research initiatives within the aerospace industry, dod and nasa to attempt interdisciplinary optimization of the whole vehicle design, while. K m ali1, m abozied, i arafa and y z elhalwagy military technical college, cairo, egypt. The typical missile autopilot is designed using system linearization and linear methods. A missile is a highly agile system that exhibits nonlinear behavior. The basic equations defining the airframe dynamics are.
Missile autopilot design using artificial neural networks 1 adel alsaraj, 2gene stuffle 1, 2, idaho state university abstract the power and speed of modern digital computers is truly astounding so that it enables carrying on complex tasks such as aerospace simulation, design and analysis, precisely. Nonlinear control problem for a missile autopilot is quick adaptation and minimizing the desired acceleration to missile nonlinear model. Integrated design of agile missile guidance and autopilot systems. Paper open access implementation and validation of autopilot. Gainscheduled missile autopilot design using linear. Cho, a new approach to autopilot design for highly nonlinear missiles, proc. Robust missile autopilot design using dynamic inversion and pi control sungjin cho, seunghwan kim, donggyun choe agency for defense development, p. Then it addresses the design issues on the linearized system thus obtained. Download tacticalmissiledesign ebook pdf or read online books in pdf, epub, and mobi format.