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Missile Guidance Seminar Report
Missile guidance concerns the method by which the missile receives its commands to move along a certain path to reach a target. On some missiles, these commands are generated internally by the missile computer autopilot. On others, the commands are transmitted to the missile by some external source. The missile sensor or seeker, on the other hand, is a component within a missile that generates data fed into the missile computer. This data is processed by the computer and used to generate guidance commands. Sensor types commonly used today include infrared, radar, and the global positioning system. Based on the relative position between the missile and the target at any given point in flight, the computer autopilot sends commands to the control surfaces to adjust the missile's course.
Missiles are the one of the major weapon in the wars. The word missile comes from the Latin verb mittere, meaning "to send". The first missiles to be used operationally were a series of missiles developed by Nazi Germany in World War II. Most famous of these are the V-1 flying bomb and V-2.
Missiles are self-propelled aerial projectiles containing explosives. For the efficient elimination of target we want to direct it to the target accurately. For this purpose we are using guidance technologies. Missiles are classified according to three basis. One is based on application, which are surface to surface, surface to air, air to surface and air to air. The second one is based on area of operation, which are tactical, support and strategic. The third one is based on flight characteristics, which are aerodynamic and ballistic.
Guided missiles have a number of different system components, which are guidance, control, armament and propulsion sections. Guidance system directs its manoeuvres. Control system execute the manoeuveres. Armament system carries the explosive charge and fusing & firing sections. Propulsion system propels the missile. In all of these components guidance system is the brain of the missile. Every missile guidance system consists of an attitude control system and a flight path control system. A novel formulation of sliding mode control (SMC) based proportional navigation (PN) guidance law is presented. Unlike conventional SMC-based guidance laws, the law presented here does not need any knowledge of bounds of target acceleration. The target acceleration is estimated using the so-called inertial delay control (IDC). Closed- loop stability for the guidance loop is established. Simulations are carried out by considering highly-maneuvering targets and constant as well as varying missile velocity and the results are presented to demonstrate the effectiveness of the proposed formulation.
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