THE Comprehensive Survey for the Numerical Simulation of the 4th Generation Rocket Ejection Seat Thrust Vector Control System

摘要

The objective of this work was to develop and adapt existing computational methodologies for 3D comprehensive analysis of ejection seat aerodynamics, including rocket plume effects. 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. Validations were performed for Aerojet's Pintle Escape Propulsion system(PEPS)rockets. Three dimensional ejection seat calculations with rocket power were also made to demonstrate the feasibility of the approach and the potential use of the model.