Simulation and Analyses of Staging Maneuvers of Next Generation Reusable Launch Vehicles

Abstract

NASA has initiated a comprehensive stage separation tool development activity to address the technology needed for successful development and operation of next generation reusable launch vehicles. As a part of this activity, ConSep simulation tool is being developed. This paper discusses the application of this tool to the staging maneuvers of two-stage-to-orbit (TSTO) vehicles. Simulation and analyses are performed for two bimese TSTO concepts, one staging at Mach 3 and the other at Mach 6. The TSTO bimese vehicles used in this study are sized for international space station class payload. The proximity and isolated aerodynamic databases used in the simulation were generated using the data from wind tunnel tests conducted at NASA Langley Research Center. ConSep is a MATLAB–based front end to the commercially available ADAMS solver, an industry standard package for solving multi-body dynamic problems. Nomenclature α angle of attack, deg ∆α relative difference in angle of attack, deg CA, CN, axial and normal force coefficient CA,b, CN,b basic (isolated) axial and normal force coefficient CA,int, CN,int interference axial and normal force coefficients ∆CA,δ,∆C axial and normal force coefficient increments due to elevon deflection e N,δ e CL, CD lift and drag coefficients Cm pitching moment coefficient C mb basic (isolated) pitching moment coefficient ∆C m,int interference pitching moment coefficient Cm,δe pitching moment increment due to elevon deflection Cmd command δe elevon deflection, deg γ flight path angle, de