Rocket Flight Loads Determination

Design and analysis of UTAT’s DEFIANCE rocket

Emerson Vargas Niño, Fred Chun
Last updated on Jan 11, 2024
Slides

Abstract: Developed and validated rocket structural loading models at max-Q using Python and OpenFOAM CFD simulations , executed on the Niagara supercomputer, leading to 12" reduction in propellant tank length to ensure 2x safety factor during flight

CFD Overview:

  • Validated CFD approach using data from a similar NACA geometry at similar flight conditions to Defiance at max-Q
  • Used hybrid mesh generator Pointwise
  • Used inviscid, compressible solver in open-source CFD platform OpenFOAM
  • Run in parallel using 320 to 480 processors on Canada’s fastest supercomputer, Niagara

Initial CFD validation results. 'Experimental geometry modifications' were inadvertently omitted, which led to small deviations in the results. Additionally, this initial meshing method utilized a cut-cell approach which was suboptimal and caused the sharp discontinuities seen in the data.
Initial CFD validation results. ‘Experimental geometry modifications’ were inadvertently omitted, which led to small deviations in the results. Additionally, this initial meshing method utilized a cut-cell approach which was suboptimal and caused the sharp discontinuities seen in the data.
Defiance CFD Results - Rocket pressure field
Defiance CFD Results - Rocket pressure field
Defiance CFD Results - Rocket nosecone pressure field
Defiance CFD Results - Rocket nosecone pressure field
Defiance CFD Results - Rocket tail pressure field
Defiance CFD Results - Rocket tail pressure field

Rockets
Emerson Vargas Niño
Emerson Vargas Niño
Aerospace Engineer and Educator

Developing advanced solutions and leading multidisciplinary teams