This paper describes the implementation of proportional navigation (PN) method as short range missile guidance to pursue a target with less maneuverability. The second stage of RKX-200EB, one of controllable rockets designed by LAPAN, model is used to generate missile non-linear dynamics 6 degree of freedoms. The guidance is developed by using classical proportional navigation together with constant bearing course approach on an existing close-loop model with PID control. The target dynamics is given as the simple motion in the X-Y plane and X-Z plane of flat-earth ENU (East North Up) reference. While the missile is evaluated along NED (North East Down) frame of reference, the PN and the target is evaluated in the ENU frame of reference. Thus, the conversion between two coordinates must be well defined. This paper observes the simulation of PN in non-linear missile model, RKX-200EB, carried by MATLAB/SIMULINK software in three-axis nonlinear 6 degree of freedom. The results show that the missile can pursue the target in X-Y and X-Z plane with miss distance less than 5 meters. Consequently, PN can be implemented to RKX-200EB to pursue a less maneuverable target.
Guidance and control of 2nd stage RKX-200EB missile using proportional navigation approach
THE 8TH INTERNATIONAL SEMINAR ON AEROSPACE SCIENCE AND TECHNOLOGY – ISAST 2020 ; 2020 ; Bogor, Indonesia
AIP Conference Proceedings ; 2366 , 1
13.09.2021
10 pages
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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