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.
GHONIEMY, S., TANTAWY, M., & ELLEITHY, M. (1991). AN IMPROVED GUIDANCE ALGORITHM FOR SOLID PROPELLENT BALLISTIC MISSILES. International Conference on Aerospace Sciences and Aviation Technology, 4(ASAT CONFLENCE 14-16 May 1991 , CAIRO), 349-361. doi: 10.21608/asat.1991.25811
MLA
S. GHONIEMY; M. TANTAWY; M. ELLEITHY. "AN IMPROVED GUIDANCE ALGORITHM FOR SOLID PROPELLENT BALLISTIC MISSILES". International Conference on Aerospace Sciences and Aviation Technology, 4, ASAT CONFLENCE 14-16 May 1991 , CAIRO, 1991, 349-361. doi: 10.21608/asat.1991.25811
HARVARD
GHONIEMY, S., TANTAWY, M., ELLEITHY, M. (1991). 'AN IMPROVED GUIDANCE ALGORITHM FOR SOLID PROPELLENT BALLISTIC MISSILES', International Conference on Aerospace Sciences and Aviation Technology, 4(ASAT CONFLENCE 14-16 May 1991 , CAIRO), pp. 349-361. doi: 10.21608/asat.1991.25811
VANCOUVER
GHONIEMY, S., TANTAWY, M., ELLEITHY, M. AN IMPROVED GUIDANCE ALGORITHM FOR SOLID PROPELLENT BALLISTIC MISSILES. International Conference on Aerospace Sciences and Aviation Technology, 1991; 4(ASAT CONFLENCE 14-16 May 1991 , CAIRO): 349-361. doi: 10.21608/asat.1991.25811
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