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Advanced Reentry Aeroheating Simulation Framework

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX16CM45P
Agency Tracking Number: 155426
Amount: $124,955.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: S3.07
Solicitation Number: N/A
Solicitation Year: 2016
Award Year: 2016
Award Start Date (Proposal Award Date): 2016-06-10
Award End Date (Contract End Date): 2016-12-09
Small Business Information
13290 Evening Creek Drive South, Suite 250
San Diego, CA 92128-4695
United States
DUNS: 000000000
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Eric Blades
 Senior Technical Advisor
 (256) 325-1116
Business Contact
 Joshua Davis
Title: Director, New Technology
Phone: (858) 480-2028
Research Institution

Vehicle reentry presents numerous challenges that must be carefully addressed to ensure the success of current and future space exploration missions. As they enter the atmosphere, these vehicles are subjected to extreme hypersonic environments typified by large structural loads, high heat fluxes and temperatures, and an aggressive aerothermal environment where nonequilibrium dissociated gases may cause chemical ablation at the vehicle's surface. These hypersonic flows involve highly nonlinear fluid-thermal interactions such as very strong shocks, high aeroheating, and shock boundary layer interactions. The extreme environments result in nonlinear, coupled interactions between the vehicle's structure and the environment. Traditionally, designs of reentry vehicles and their components have been analyzed by different engineering disciplines in an uncoupled manner, leading to a simplified superposition of different independent analyses. Depending on the assumptions, this can potentially lead to overconservatism or omission of multiphysics phenomena such as the deformation of structural skin panels which alters the local flow field and results in higher aerodynamic and heat loading. To alleviate these problems, ATA Engineering proposes to develop an innovative approach utilizing an existing multiphysics framework that enables a more complete simulation of the aeroheating environment throughout the flight trajectory in the continuum regime is proposed. In Phase I, we will demonstrate feasibility of solving these problems in ATA's multiphysics simulation environment by coupling CHAR (a 3D, implicit charring ablator solver), Loci/CHEM (a computational fluid dynamics solver for highspeed chemically reacting flows), and Abaqus (a commercial nonlinear structural dynamics package) to create a fully coupled aerothermoelastic charring ablative solver. Phase II will involve enhancements to enable full trajectory simulation and tool validation with experimental data.

* Information listed above is at the time of submission. *

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