Abstract—This paper presents a finite element model for strength analysis of a missile’s missile control component under different conditions like pitch, roll and Yaw. Characteristics of stress distribution and high stress locations are determined according to the model. The high random vibration loads imparted on Missile control component by the other hardware during launch create an adverse design requirement that all hardware have a natural frequency greater than that of the Missile control component, in order to avoid damage and failure due to dynamic coupling. Maximizing natural frequency is generally accomplished by creating as stiff and lightweight a design as possible. However, designing for the resultant high loads also requires a high stiffened structure. These two opposing design requirements drive an optimization between a lightweight and high strength structure. This paper also presents a finite element analysis for strength analysis of a missile’s Missile control component under random loading conditions. Static, Modal RSA and Power spectrum density (PSD) analysis will be carried out to plot graph of the PSD value versus frequency, where the PSD may be a displacement PSD, velocity PSD, acceleration PSD, or force PSD. Based on the results obtained, optimization of the control component was also done in this project.

Index Terms—Missile control component, FEA, Guided missile

Cite: Vuyyuru Murali Krishna and P V Anil Kumar, "Design Optimization of a Missile Control Component Used in a Guided Missile," International Journal of Mechanical Engineering and Robotics Research, Vol.3, No.4, pp. 596-603, October 2014.