Parameter adjustment and compensator design for missile guidance

Abstract EN

Guidedmissiles are to be very accurately pointed towards the target so as to hit them without any fail.

The task is not easy as there may be obstacles in the path followed by the missile and the target may be static or dynamic.

The spécifications are also very stringent.

Moreover, the requirements ofsteady state accuracy and the transient performance are often contradictory.

As such the design cannot be accomplished by open loop, on-offorlogicalcontrol.

The desiredperformance can be realized only by properly designed feedback controlsystem.

Proportionalfeedback generally fails to fulfil the transient and stability requirements.

The system is made stable and the transient performance is shaped by adding weighted derivative feedback (PD), integral feedback (PI) or a combination of them (PID).

Even if the transient requirements are fulfilled, it becomes difficult to maintain adequate stability margins.

Therefore, a compensator has to be cascaded in the forward or feedback path.

In this paper, the design ofa guided missile has been taken up.

Its block diagram and transfer function are given.

The gain has been fixed up to keep the steady state error within prescribed limits.

The transient performance has been shaped and stability ensured by adding a weighted amount of derivative feedback.

The required amount of stability margins have been realized by cascading a properly designed lead type compensatorin the forward path.