GENERALIZED VEHICLE PERFORMANCE CLOSURE MODEL FOR TWO -STAGE -TO -ORBIT LAUNCH VEHICLES

A generalized, fully integrated multidisciplinary performance closure model for analyzing and designing Two -Stage -To -Orbit (TSTO) Launch Vehicles is presented. The model is developed under NASA's Advanced Engineering Environment (AEE) to allow NASA to perform independent assessments of the emerging architectures and technologies. It covers a large s et of architecture concepts such as reusable, expendable, series burn, parallel burn, cross feed, no cross feed, single booster, multiple boosters and common boosters. The model accommodates a broad range of different design assumptions and mission objecti ves. The analysis disciplines integrated in the model include weights, sizing, CAD based parametric geometry, rocket propulsion, ascent trajectory, high - speed aerodynamics, and structure. Different types of analysis tools running on different platforms are integrated together using Phoenix Integration's ModelCenter and Analysis Server framework, and the entire closure process can be run in a fully automated fashion.