Missile autopilot design pdf

Design of a missile autopilot using adaptive nonlinear. For highly agile missile systems, other robust control methodologies were applied to the design of missile autopilot based on h. The missile plant model is characterized by a linear fractional transformation lft representation. Embryriddle aeronautical university press, 1996, pp. 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. Integrated design of agile missile guidance and autopilot systems. Multiinput multioutput nonlinear autopilot design for. Autopilot design for agile missile using timevarying control. Three loop lateral missile autopilot design in pitch plane.

Pdf mathematical models for a missile autopilot design. In 2, linear matrix inequalities are used to propose a systematic gain scheduling autopilot design that accommodates mass variation. Many nonlinear control methods have been proposed for the missile autopilot. Generally, no sin gle autopilot design can stabilize the missile and provide the performance required over the entire desired flight envelope. International conference on nonlinear problems in aviation and aerospace 1st, daytona beach, fl, may 1996, pp. Missile autopilot design by projective control theory metu. Pdf controller design for a twoloop missile autopilot. The design is based on a much more general and realistic missile model compared to the plethora of nonlinear. Missile autopilot design via x y z functional inversion. In 4, a power series expansion based method was used in the. Designing a guidance system in matlab and simulink matlab. The aim of this paper is to design autopilot with aerodynamics surfacesfinand thrust vector control by system characteristics reflection. The basic equations defining the airframe dynamics are non. Download pdf tacticalmissiledesign free online new.

The fundamental problem of feedback linearization technique is not able to cater the model uncertainty. 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. 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. Missile longitudinal autopilot design using a new suboptimal. Dynamic matrix flight control design for a nonlinear missile autopilot a. 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. A robust adaptive control approach to missile autopilot design. Comparisons of the design approaches and results are also discussed. Short range missile autopilot design using fuzzy control. 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. Currently, there are major research initiatives within the aerospace industry, dod and nasa to attempt interdisciplinary optimization of the whole vehicle design, while. Box 353, yuseong, daejeon, 305600, republic of korea abstract. Dynamic matrix flight control design for a nonlinear.

Robust missile autopilot design using dynamic inversion and pi control sungjin cho, seunghwan kim, donggyun choe agency for defense development, p. Missile autopilot designs considering both rigidbody dynamics and elasticbody dynamics are presented. Design of a roll autopilot for a skidtoturn guided missile. 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. Robust missile autopilot design using dynamic inversion. Pdf design of a missile autopilot using adaptive nonlinear. Its now at helpsimulinkslrefdesigningaguidancesysteminmatlabandsimulink.

Short range missile autopilot design using fuzzy control technique m. A missile is a highly agile system that exhibits nonlinear behavior. Control international journal of aeronautical and space sciences, vol. For aerodynamically controlled skid to run missile, the autopilot activates to move the controlsurfaces i. Threeaxis autopilot design for a high angleofattack missile using mixed h 2 h. 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. In order to motivate numerical approach to the feedback linearization method, the following will provide a brief outline of the technique. A two loop autopilot configuration has been chosen which is characterized by a dynamics. Nonlinear control problem for a missile autopilot is quick adaptation and minimizing the desired acceleration to missile nonlinear model. Design and flight test of a robust autopilot for the irist airtoair missile control engineering practice, vol.

The results show that the application of robust control techniques to the design of missile autopilots can improve the performance and stability robustness characteristics. Gainscheduled missile autopilot design using linear parameter varying transformations jeff s. Robust missile autopilot design using dynamic inversion and. The text combines detailed examination of key theories with practical coverage of methods for advanced missile guidance control systems. A number of nonlinear control methods have also been proposed for the missile autopilot design. Missile, threeloop auto pilot, pitch plane, pid controller. In these robust control designs, a set of controllers each satisfying. Robust nonlinear design of three axes missile autopilot via. Department of guidance, military technical college, cairo, egypt. Khargonekar 1998 missile autopilot design using hoc control with gain scheduling and dynamic inversion. Therefore how to design control strategy properly is an urgent problem. Pdf software tools for nonlinear missile autopilot design. The aim of the missile autopilot is to control acceleration normal to the missile body.

Guided missile, autopilot, linear quadratic design, full state feedback. L1 adaptive controller for a missile longitudinal autopilot. In 4, the wellknown h1 control method is incorporated into the gainscheduling approach in order to simplify the gainscheduling procedure. Dynamic inversion di was used for the innerloop design in. Robust h autopilot design for agile missile with timevarying. 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. Background on the application of feedback linearization technique to missile autopilot problem can be found in references.

The basic equations defining the airframe dynamics are. The uncertainties include parametric variations in the transfer function and timevarying disturbances. Ha, missile autopilot design via functional inversion and timescaled transformation, ieee trans. Mathematical models for a missile autopilot design dtic. Mracek, cp, cloutier, jr missile longitudinal autopilot design using the statedependent riccati equation method. Paper open access design of a roll autopilot for a skidto. Software tools for nonlinear missile autopilot design. Missile longitudinal autopilot design using the statedependent riccati equation method. Currently, there are major research initiatives within the aerospace industry, dod and nasa to attempt interdisciplinary optimization of. Antitank short range missiles can be categorized in the most widely used weapons in the recent ground battle field. Paper open access implementation and validation of autopilot. International journal of advances in engineering and. Then, a frequency domain loop shifting method is used to derive an h. Pdf missile design and systems engineering download full.

This report also considers a locally linearised state space model that. Then it addresses the design issues on the linearized system thus obtained. Cho, a new approach to autopilot design for highly nonlinear missiles, proc. 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. Analysis and design of missile two loop autopilot semantic. Due to the wide parameter variation and stringent performance requirements, missile autopilot design is a challenging task. First a new autopilot design model is presented for the interceptor missile with the blended aerodynamic lift and reaction jet. Agile missile autopilot design using nonlinear backstepping.

Download tacticalmissiledesign ebook pdf or read online books in pdf, epub, and mobi format. Pdf missile autopilot design for agile turn control during boost. Gainscheduled missile autopilot design using linear. Computeraided synthesis of nonlinear autopilots for missiles.

The missile autopilot design is formulated in section 3. The authors in 8 proposed missile autopilot design, using feedback linearization and a twotime scale separation technique. The key to the autopilot design is the decoupling of the missile maneuvers into lateral and longitudinal components and performing them. Pdf this paper presents the airtoair missile autopilot design for a 180 heading reversal maneuver during boostphase. Robust h autopilot design for agile missile with time. This paper presents a robust nonlinear autopilot design method based on dynamic inversion and pi control law. 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. Ahari a1, torabi a, karsaz a2 khorasan institute of higher education, mashhad, iran corresponding author. K m ali1, m abozied, i arafa and y z elhalwagy military technical college, cairo, egypt.

This report considers the derivation of the mathematical model for a missile autopilot in state space form. 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. Integrated design of agile missile guidance and autopilot systems p. A generic approach to missile autopilot design using state. 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.

Tactical missile autopilot design using nonlinear control. The typical missile autopilot is designed using system linearization and linear methods. This report considers the derivation of the mathematical models for a missile autopilot in state space form. In 1, a robust pole placement technique is used for an autopilot design. Pdf nonlinear missile autopilot design with thetad. The reaction jet can improve the response speed, but the structure of control system becomes more complex. Longitudinal nonlinear adaptive autopilot design for missiles. Implementation and validation of autopilot design for vertical missile systems. The block diagram of the proposed control system with required controller gains is. Full envelope missile autopilot design using gain scheduled. Modeling and simulation of advanced nonlinear autopilot. Missile autopilot design via x y z functional inversion and. Journal of guidance, control, dynamics, 21, 234243.

The online system identification is required to complete the cycle of adaptive autopilot design. 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. Pdf a computeraided design software package for nonlinear control synthesis is discussed. Second, considering the discrete property of the lateral pulse jet thrusters and the. Development of a trusted autopilot for these kinds of missiles is a very critical issue. 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. Integrated design of agile missile guidance and autopilot. High performance control of nonlinear systems requires the design of advanced, nonlinear control systems, such as those used in autopilot design. Nonlinear missile autopilot design with thetad technique article pdf available in journal of guidance control and dynamics 273. Autopilot design for agile missile using timevarying. 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. In the design and stability analysis of our autopilot, we assume perfect rollstabilization but consider.

Pdf nonlinear missile autopilot design with thetad technique. 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. Additional details onmissile autopilot design processusingthe feedback linearization method. Air force armament directorate, eglin air force base, florida 32542 this paper presents a gainscheduled design for a missile longitudinal autopilot. In this dissertation, a nonlinear autopilot design for a medium range bank to turn airtoair missile is presented. Paper open access implementation and validation of. Pdf controller design for a twoloop missile autopilot in. Constrained missile autopilot design based on model. Longitudinal nonlinear adaptive autopilot design for. Design of missile threeloop autopilot pitch using pid controller. The missile data used for the proposed system was of three loop autopilot. For each of the above cases, the normal acceleration command missile autopilot is evaluated using both time and. Robust missile longitudinal autopilot design based on.