Advanced Computational Model for Rocket Plume Effects on Escape System Aerodynamic Characteristics

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Advanced Computational Model for Rocket Plume Effects on Escape System Aerodynamic Characteristics

S. G. Rock / S. D. Habchi

The focus of this SBIR project was to develop and adapt existing computational methodologies for three-dimensional comprehensive analysis of ejection seat aerodynamics, including rocket plume effects. This Phase I study (6 months) focused on analyzing ejection seat rocket propulsion systems and developing techniques to solve for rocket plume flows within the ejection seat environment. Various methods were investigated for prescribing boundary and initial conditions for the seat rockets. The selected method utilizes a model that prescribes 3D nozzle exit boundary profiles extracted from detailed rocket nozzle calculations. Also, a multi-domain gridding method that allows for many- to-one interface meshing was developed and tested for efficient and accurate rocket plume resolution within the 3D ejection seat computational environment. Basic rocket plume model validations were made to a jet-in-axial and jet-in- crossflow problems. Excellent agreement was obtained for the jet-in-axial flow and reasonable agreement was obtained for the jet-in-crossflow. Validations were also performed for the Pintle Escape propulsion system rockets. Good agreement with test data was obtained for thrust levels obtained for various pintle positions. 3D ejection seat with rocket power calculations were also made to demonstrate the feasibility of the approach and the potential use of the model.