The paper presents application of guidance system for small, smart mortar missile. The presented control system is simple and inexpensive. It is based on a set of one time used impulse control engines and linear coordinator rotating with controlled object. Engines are mounted around the missile. There are no movable devices on the projectile board. The correcting impulses from rocket engines are perpendicular to main symmetry axis of the flying object and influence directly the centre of gravity of the guided missile. In the paper, authors describe the whole control system of the missile. Particular attention is focused on seeker and control devices. Numerical analysis presents some cases of the missile controlled flights.
This paper presents the design methodology of a small guided bomb for Unmanned Aerial Vehicles. This kind of next-generation munition has recently gained a lot of attention in the military market. The bomb is planned to be equipped with inertial measurement unit and infrared seeker. The nose shape and fin optimization procedure was described shortly. Aerodynamic characteristics were calculated by means of theoretical and engineering-level methods. The flight dynamics model of the bomb was obtained and implemented in Simulink software. The numerical simulations of uncontrolled and controlled trajectories were compared. The results indicate that the usage of such a guided small munition, like the designed bomb, might improve significantly the offensive capabilities of Unmanned Aerial Vehicles.