Improved estimation of random vibration loads in launch vehiclesRandom vibration induced load is an important component of the total design load environment for payload and launch vehicle components and their support structures. The current approach to random vibration load estimation is based, particularly at the preliminary design stage, on the use of Miles' equation which assumes a single degree-of-freedom (DOF) system and white noise excitation. This paper examines the implications of the use of multi-DOF system models and response calculation based on numerical integration using the actual excitation spectra for random vibration load estimation. The analytical study presented considers a two-DOF system and brings out the effects of modal mass, damping and frequency ratios on the random vibration load factor. The results indicate that load estimates based on the Miles' equation can be significantly different from the more accurate estimates based on multi-DOF models.
Document ID
19930046984
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mehta, R. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Erwin, E. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Suryanarayan, S. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Krishna, Murali M. R. (Analytical Services and Materials, Inc. Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
February 1, 1993
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
AIAA PAPER 93-1092
Meeting Information
Meeting: AIAA, AHS, and ASEE, Aerospace Design Conference