Defining an appropriate flight vibration specification is a critical issue at an initial design phase, for optimized design of components in a surface-to-air missile (SAM). As the related document (MIL-STD-810G) doesn’t provide detailed value, appropriate procedures for estimation of flight vibration specification are required for design of a surface-to-air missile. In this study, the method-making appropriate specification without an actual flight test is introduced. Comparison between a theoretical approach using the beam theory and FEA is conducted to attain a natural vibration frequency under thrust force. Transient response analysis using commercial S/W is conducted to establish an envelope curve for flight vibration.
This research analyzes bucket elevator roller chain pins by finite element (FE) analysis and static structural analysis for a lightweight pin design. The stress distribution of light weight roller chain pins under static load is analyzed for safety factors and damping effect. The results show that the stress distribution is higher on the plate than on the bush pin. In order to compare experimental and FE analysis results, a light weight design approach was used to produce a prototype base pin. Because the inner diameter of the pin was different, the impact damping effect was most appropriate when the inner diameter was 34.05 ㎜, and it is used as basic research data on the impact of the roller chain and sprocket.
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