Impact point prediction guidance parametric studyfor 155 mm rocket assisted artillery projectilewith lateral thrusters

Adrian Szklarski , Mariusz Jacewicz , Robert Głębocki

Abstract

The modified configuration of the 155 mm rocket assisted projectile equipped withlateral thrusters was proposed. Six degree of freedom mathematical model was used toinvestigate the quality of the considered projectile. Impact point prediction guidancescheme intended for low control authority projectile was developed to minimize thedispersion radius. Simple point mass model was applied to calculate the impact pointcoordinates during the flight. Main motor time delay impact on range characteristicswas investigated. Miss distance errors and Circular Error Probable for various lateralthruster total impulse were obtained. Monte-Carlo simulations proved that the impactpoint dispersion could be reduced significantly when the circular array of 15 solidpropellant lateral thrusters was used. Single motor operation time was set to be 0.025 s.Finally, the warhead radii of destruction were analyzed
Author Adrian Szklarski (FPAE / IAAM)
Adrian Szklarski,,
- The Institute of Aeronautics and Applied Mechanics
, Mariusz Jacewicz (FPAE / IAAM)
Mariusz Jacewicz,,
- The Institute of Aeronautics and Applied Mechanics
, Robert Głębocki (FPAE / IAAM)
Robert Głębocki,,
- The Institute of Aeronautics and Applied Mechanics
Journal seriesArchive of Mechanical Engineering, [Archiwum Budowy Maszyn], ISSN 0004-0738, e-ISSN 2300-1895
Issue year2020
Vol67
No1
Pages31-56
Publication size in sheets1.25
ASJC Classification2210 Mechanical Engineering; 2211 Mechanics of Materials
Abstract in original languageThe modified configuration of the 155 mm rocket assisted projectile equipped withlateral thrusters was proposed. Six degree of freedom mathematical model was used toinvestigate the quality of the considered projectile. Impact point prediction guidancescheme intended for low control authority projectile was developed to minimize thedispersion radius. Simple point mass model was applied to calculate the impact pointcoordinates during the flight. Main motor time delay impact on range characteristicswas investigated. Miss distance errors and Circular Error Probable for various lateralthruster total impulse were obtained. Monte-Carlo simulations proved that the impactpoint dispersion could be reduced significantly when the circular array of 15 solidpropellant lateral thrusters was used. Single motor operation time was set to be 0.025 s.Finally, the warhead radii of destruction were analyzed
DOIDOI:10.24425/ame.2020.131682
URL https://journals.pan.pl/dlibra/publication/131682/edition/115014/content
Languageen angielski
Score (nominal)20
Score sourcejournalList
ScoreMinisterial score = 20.0, 18-06-2020, ArticleFromJournal
Publication indicators WoS Citations = 0; Scopus SNIP (Source Normalised Impact per Paper): 2018 = 0.69
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