Abstract: Horizontal take-off and horizontal landing (HTHL) two stage to orbit (TSTO) reusable launch vehicle (RLV) system using turbine based combined cycle engines (TBCC) is one of the most possible approaches to decrease launch cost and shorten launch operation cycle. Aerodynamic configurations for TSTO vehicle system should satisfy overall requirements covering all fly speed range and airspace range under the strictly restriction of overall sizing and mass, including aerodynamic characteristics, stability and controllability, thermal safety, maintenance, and reliability. Design consideration of a TSTO vehicle system is proposed, and several vehicle configurations for the first and the second stages are sketched separately according to each vehicle mission, propulsion selection, fight mode, and overall constraints. Advantages and disadvantages of the possible vehicle configurations are analyzed. Operation envelops for two upgraded concepts are re-designed to meet the equilibrium condition of lift and weight. To ensure the safety of stage separation, and improve lift-drag efficiency and directional stability, V tails and foldaway wingtips are adjusted, through which a new TSTO system concept is primarily ideated. Further efforts are also proposed.