AN IMPROVED GUIDANCE ALGORITHM FOR SOLID PROPELLENT BALLISTIC MISSILES | ||
International Conference on Aerospace Sciences and Aviation Technology | ||
Article 33, Volume 4, ASAT CONFLENCE 14-16 May 1991 , CAIRO, May 1991, Pages 349-361 PDF (1.94 M) | ||
Document Type: Original Article | ||
DOI: 10.21608/asat.1991.25811 | ||
Authors | ||
S. GHONIEMY1; M. TANTAWY2; M. ELLEITHY3 | ||
1Asc.Prof. Guid.Dep.M.T.C. | ||
2Asc.Prof. D.S.S.C. | ||
3Ph.D. Air Def.College. | ||
Abstract | ||
Due to production tolerences and off-nominal environmental conditions, the thrust time profile of solid propellant rocket motors suffers from high uncertainties in both magnitude and burn-out time. This behaviour leads to higher uncertainties in the motion parameters of the missile at the shut-off (burn-out) point. Accordingly, the impact point is highly erroneous. This paper develops a guidance and control strategy for compensating the effects of the above-mentioned uncertainties in such a way as to minimize impact errors. | ||
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