טכניון מכון טכנולוגי לישראל
הטכניון מכון טכנולוגי לישראל - בית הספר ללימודי מוסמכים  
M.Sc Thesis
M.Sc StudentDaniel Reisner
SubjectGuidance of an Accelerating Exo-Atmospheric Interceptor
Missile
DepartmentDepartment of Aerospace Engineering
Supervisor Full Professor Shima Tal
Full Thesis textFull thesis text - English Version


Abstract

A guidance-to-collision law is presented. The guidance law is derived, using the optimal control methodology, for an accelerating exo-atmospheric interceptor. It is dependent on the zero-effort heading angle error and also on a variable denoted as zero-effort angle of attack. The guidance law enables an accelerating interceptor to fly towards the interception point along a straight line, after the initial heading error is nulled. In addition, the guidance-to-collision law enables interception of the target with a terminal aspect angle. Moreover, the trajectory imposed by this guidance law enables estimation of the target's acceleration by using bearings- only measurements. This is possible due to the line-of-sight rotation, making the range between the two vehicles observable. Using a non-linear two-dimensional simulation the performance of the guidance law is analyzed showing superior performance compared to that of classical proportional navigation.