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DESIGN AND IMPLEMENTATION OF

FRACTIONAL ORDER PIDCONTROLLER FOR AEROFIN CONTROL SYSTEM

Under The Guidance Of Sri. RAVI KUMAR JATOTH

Asst. Prof. E.C.E DeptNIT WARANGAL

OUT LINE OF PRESENTATION:

• Problem formulation • Introduction • Forces on Airplane or missile• control of missiles• Missile dynamics• dynamics controlling • fin effects on missile

Problem formulation

INTRODUCTION

• A missile can be defined as any object that can be thrown, projected or propelled toward a target.

• Missiles can be classified into two different categories .

– Unguided Missiles After firing, they get completely out of control.– Guided Missiles Guided missiles, can be used effectively both for distant

and arbitrarily moving targets

GUIDED MISSILES

• the guidance and control problem involves– Dynamic Modeling– Guidance– Control

FORCES ON AIRPLANE OR MISSILE

weight• Weight is a force caused by the gravitational attraction of earth • It Depends on– Mass of parts of the missile it self – Fuel– Payload on board

lift

• Lift is a mechanical force generated by a solid objective moving through a fluid.

• Lift acts perpendicular to motion.

drag

• Drag is a mechanical force generated by solid objective moving through a fluid.

• Drag acts in direction that is opposite to the motion of the missile

thrust

• Force which moves an missile through the air

• Thrust is used to over come the – Drag of an missile and– Weight

And is generated by the engines of the missile

CONTROL OF MISSILES

• The mission of a missile control system, or a missile autopilot, is to ensure the stability,

high performance and that the missile flies in accordance to the demands of the guidance law

• Depending on the missile dynamics– i.e. body angles (yaw, pitch and roll angles)

MISSILE DYNAMICS

• The three critical missile dynamics parameters are the angles of rotation in three dimensions about the vehicle's center of mass, known as Pitch, Roll and yaw

Rotation of a reference frame using Yaw-Pitch-Roll

DYNAMICS CONTROLLING

• Aerodynamic control surfaces can be in the form of canards , wings, tails

• Canard - controlled missile wing controlled missile

• tail controlled missile

FIN and EMA ACTUATORS IN MISSILE

FIN EFFECTS ON MISSILE

Problem formulati on

FOPID CONTROLLER

• To construct a more robust control system the integral and differential parts should be fractional

• The differential equation of the FOPID controller is

• The transfer function of the FOPID controller is represented

• function which is optimised by FOPID

• Where R is the rise time

• po is the percent overshoot

• S is the settling time

• ess is the steady-state error

• are proportionality constants

Thank You

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