Aerodynamic configuration design using response surface methodology analysis

摘要: An investigation has been conducted to determine a set of optimal design parameters for single-stage-to-orbit reentry vehicle. Several configuration geometry which had large impact on the entry vehicle flying characteristics were selected as variables: fuselage fineness ratio, nose body length camber value, wing planform area scale factor, and location. The parameter values chosen using response surface methodology (RSM) technique allowed minimum dry weight that met aerodynamic performance constraints landing speed, subsonic, supersonic, hypersonic trim stability levels. RSM utilized, specifically central composite method, is presented, along with general conceptual process. Results are presented an optimized several trade cases.