Engine System Loads Analysis Compared to Hot-Fire Data

Abstract

Verbatim from NASA NTRS. Not paraphrased, not summarized.

Early implementation of structural dynamics finite element analyses for calculation of design loads is considered common design practice for high volume manufacturing industries such as automotive and aeronautical industries. However with the rarity of rocket engine development programs starts, these tools are relatively new to the design of rocket engines. In the NASA MC-1 engine program, the focus was to reduce the cost-to-weight ratio. The techniques for structural dynamics analysis practices, were tailored in this program to meet both production and structural design goals. Perturbation of rocket engine design parameters resulted in a number of MC-1 load cycles necessary to characterize the impact due to mass and stiffness changes. Evolution of loads and load extraction methodologies, parametric considerations and a discussion of load path sensitivities are important during the design and integration of a new engine system. During the final stages of development, it is important to verify the results of an engine system model to determine the validity of the results. During the final stages of the MC-1 program, hot-fire test results were obtained and compared to the structural design loads calculated by the engine system model. These comparisons are presented in this paper.

Authors

• Frady, Gregory P. NASA Marshall Space Flight Center
• Jennings, John M. NASA Marshall Space Flight Center
• Mims, Katherine NASA Marshall Space Flight Center
• Brunty, Joseph NASA Marshall Space Flight Center
• Christensen, Eric R. Science Applications International Corp.
• McConnaughey, Paul R.