TY - CONF
T1 - Parallel finite element simulation of the flare maneuver of large ram-air parachutes
AU - Kalro, V.
AU - Garrard, W.
AU - Tezduyar, T.
N1 - Funding Information:
This research was sponsored by ARO under grant DAA H04-93-G-0514, by ARPA under NIST con- tract 60NANB2D1272 and by the Army High Performance Computing Research Center under the auspices of the Department of the Army, Army Research Laboratory cooperative agreement number DAAH04- 95-2-0003/contract number DAAH04-95-C-0008, the content of which does not necessarily reflect the position or the policy of the government, and no official endorsement should be inferred. CRAY C90 time was provided in part by the University of Minnesota Supercomputer Institute.
Publisher Copyright:
© 1997, American Institute of Aeronautics and Astronautics, Inc.
PY - 1997
Y1 - 1997
N2 - Currently, there is a requirement to develop large gliding parachutes which could deliver payloads upto 21 tons. Due to the scale effects which influence the dynamic behavior of such parachutes (thus ruling out testing of scaled down models), conventional methods such as drop tests and wind tunnel evaluations are unfeasible or very costly for design purposes. This motivates us to look towards high-performance computing tools as a viable alternative to predict the behavior of such parachutes based on first principles analysis. In this paper we present a methodology to simulate the flare maneuver of ram-air parachutes using stabilized space-time finite element formulation of the Navier-Stokes equations. A special mesh moving scheme is designed to accommodate the translational, pitching and flap motion during the flare maneuver. This scheme is highly parallelizable and is coupled to previously developed optimized parallel methodologies for solving systems with millions of coupled, nonlinear equations in reasonable turn-around times. These computations are carried out on a 512-node Thinking Machines CM-5 supercomputer.
AB - Currently, there is a requirement to develop large gliding parachutes which could deliver payloads upto 21 tons. Due to the scale effects which influence the dynamic behavior of such parachutes (thus ruling out testing of scaled down models), conventional methods such as drop tests and wind tunnel evaluations are unfeasible or very costly for design purposes. This motivates us to look towards high-performance computing tools as a viable alternative to predict the behavior of such parachutes based on first principles analysis. In this paper we present a methodology to simulate the flare maneuver of ram-air parachutes using stabilized space-time finite element formulation of the Navier-Stokes equations. A special mesh moving scheme is designed to accommodate the translational, pitching and flap motion during the flare maneuver. This scheme is highly parallelizable and is coupled to previously developed optimized parallel methodologies for solving systems with millions of coupled, nonlinear equations in reasonable turn-around times. These computations are carried out on a 512-node Thinking Machines CM-5 supercomputer.
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U2 - 10.2514/6.1997-1427
DO - 10.2514/6.1997-1427
M3 - Paper
AN - SCOPUS:84976480104
SP - 19
EP - 26
T2 - 14th Aerodynamic Decelerator Systems Technology Conference, 1997
Y2 - 3 June 1997 through 5 June 1997
ER -