Terminal Guidance Technique For Infrared/Ultraviolet Dual-band Rose Scanning Quasi Imaging Mode Of The Rolling Missile

For the infrared-guided weapons, it requires that the infrared guidance system not only has the capable of guiding missile hitting the targets with high precision, but also can select the vital parts or weak points of the target as the point of attack, so that enhancing the ability to destroy the target.In the final stages of flying to the enemy plane,that is the distance of missle and target is within a few hundreds meters,the infrared-guided missile trajectory will constitute the collision line on target. At this stage, as for the missile with non-targeted terminal guidance technology, the off-axis angle of the infrared seeker device is essentially unchanged and continued until missile crushing the infrared radiation center, near which the warhead is detonated. All above is equivalent to attacking on t he false targets — exhaust flow, and cause the misses on real vital parts. Otherwise, the infrared seeker with point source or line scanning system, due to the smaller scanning field of view, limited accessing target information and the other factors, the seeker can only detect the thermal radiation center which is near to the engine nozzle of the targets(aircrafts). when closing to the target,the special terminal guidance method — the terminal correction technology is adopted, making the seeker guidance system guided to the vital parts, further improving the guidance accuracy, kill probability and operational effectiveness.In order to finsh the terminal guidance design of a certain type of infrared missile, which will hit the vital parts with high accuracy, this paper combine with the rose scanning quasi imaging mode of the missile, the infrared / ultraviolet dual-band detection scheme is introduced. the control model of terminal guidance is researched; the control method and process are determined; the recognition algorithm of infrared / ultraviolet rose scanning quasi imaging is designed, which can determine the forword phase and size of the target, and the encounter time of missile and target is calculated based on the infrared energy growth slope which is detected by infrared seeker in real time. All above are implemented in the seeker control software, and the accuracy of pre-push is verified based on t he existing different flight trajectory data. At last, the encounter time algorithm and infrared/ultraviolet quasi image processing algorithm are designed, which will implement terminal guidance function of missile on high maneuver target.