saranya bhavsingh missile bassics
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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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