Structure design of wrap-around deployable stabilizer for 300 mm class artillery rockets

• Main Authors: Muslimin, Ahmad Novi, Triharjanto, Robertus Heru, Ruyat, Yayat
• Format: Conference Proceeding
• Language: English
• Subjects: Aerodynamic loads; Artillery; Design criteria; Finite element method; Leading edges; Mathematical analysis; Rockets; Safety factors; Stress analysis; Thickness
• ISSN: 0094-243X; 1551-7616
• DOI: 10.1063/5.0184916

The performance indicators of the artillery rocket are its maximum range, accuracy, and damage radius of its warhead. The accuracy and maximum range, among others, are affected by the rocket’s fin stabilizer. The objective of the research is to obtain optimal design of 300 mm class artillery rocket fin stabilizer, which due to packaging constraint on its launcher vehicle, need to be folded during transportation and deployed during its launch. The design variables are the fin’s geometry, which will affect the stress due to aerodynamic loads on the fin. Three variations for the fin’s leading edge, i.e. 10 mm, 30 mm dan 50 mm, and three variations of the fin’s root thickness, i.e. 5 mm, 10 mm, dan 15 mm, are evaluated, which combined become 9 configurations. For each configuration, the aerodynamic loads are calculated using RASAero II at the assumed maximum speed of the rocket, 2.0 mach. The stress analysis was done using finite element method with two material variants, Al7075–T6 and A36 Steel. The design criteria that safety factor should be as according to NASA-STD-5001B. The results show 4 possible designs with two optimal fin configurations, having a leading edge of 30 mm with a root thickness of 5mm, which yield maximum Von Mises stress of 1.863 x 108 Pa, and with leading edge of 50 mm and root of 5 mm, with maximum Von Mises stress of 2.227 x 108 Pa.