Abstract
Anti-tank surface to surface guided missile systems are considered to be one of the most powerful weapons in the modern war. Due to their effectiveness against either fortifications or tanks in addition to their relative low weight, they are deployed in the field easily. One of the most challenges the engineers face while designing a guided missile is the autopilot design. The autopilot loop or the inner loop of the missile should steer the missile during its spatial flight till hitting the target even it is moving or stationary. A higher maneuver target was hit by the missile, the more reliable autopilot you design. On designing a mature autopilot, a promising mathematical model of the missile should be in hand and mathematical linearized model should be derived. This paper presents a mathematical representation of an anti-tank guided missile the mathematical linearized model as well so that the design of the missile autopilot is presented in the future work.
Highlights
The intended missile system uses the command line of sight (CLOS) guidance method to hit its target even this target is moving or stationary [10]
The operator has to keep the sight reticle on the target center and as a result, missile spatial position is measured and sensed via the sight or night detectors located in the ground station, the miss angle between the actual missile position and the virtual line of sight is calculated in missile guidance unit (MGU) and it generates the steering commands sent to the missile via the command wire [1]
The actual angle carried out by the missile in yaw plane is measured by the free gyro and the difference between the achieved missile angle and the commanded angle sent via the wire (∆ψ) is compensated by the inner loop compensation network as shown in figure 1 [1]
Summary
The intended missile system uses the command line of sight (CLOS) guidance method to hit its target even this target is moving or stationary [10]. The operator has to keep the sight reticle on the target center and as a result, missile spatial position is measured and sensed via the sight or night detectors located in the ground station, the miss angle between the actual missile position and the virtual line of sight is calculated in missile guidance unit (MGU) and it generates the steering commands sent to the missile via the command wire [1] These commands are received by the on-board missile electronics and in turn the missile control surface deflects according the angel commanded resulting in a new missile position. The paper ends with conclusion and references in the fourth and fifth section respectively
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