contributor author | Agus Budiyono | |
contributor author | Harapan Rachman | |
date accessioned | 2017-05-08T21:33:49Z | |
date available | 2017-05-08T21:33:49Z | |
date copyright | April 2012 | |
date issued | 2012 | |
identifier other | %28asce%29as%2E1943-5525%2E0000104.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/56248 | |
description abstract | This paper presents a high-performance and simple guidance method for a short-range missile. Missile control systems are designed along the estimated flight envelope of the missile based on coefficient diagram method. The linear time invariant (LTI) models are obtained by linearizing missile nonlinear model at specific operating points. The governing equations of motion are accurately modeled by taking into account the effect of the mass rate and the center of gravity shift. A novel algebraic approach called coefficient diagram method (CDM) is used to design normal acceleration and roll angle control systems. The proportional navigation law is considered as the guidance law. One case of engagement scenarios is studied and the missile performance is evaluated. The robustness of the proposed controller is tested against parameter uncertainties and wind disturbance. | |
publisher | American Society of Civil Engineers | |
title | Proportional Guidance and CDM Control Synthesis for a Short-Range Homing Surface-to-Air Missile | |
type | Journal Paper | |
journal volume | 25 | |
journal issue | 2 | |
journal title | Journal of Aerospace Engineering | |
identifier doi | 10.1061/(ASCE)AS.1943-5525.0000104 | |
tree | Journal of Aerospace Engineering:;2012:;Volume ( 025 ):;issue: 002 | |
contenttype | Fulltext | |