Bent-biconic single-stage-to-orbit vehicle conceptual study

A new design concept is proposed for an all-propulsive, vertical-takeoff/horizontal-landing, reusable single-stage-to-orbit space transportation system. The vehicle is to carry an unmanned payload of 11 tons to a 400-km orbit inclined at 51 deg. It is shaped in a bent-biconic geometry, has no wings but horizontal and vertical stabilizers, and relies on a para-wing for landing. Its tripropellant propulsion system uses both RP1-LOX and LH2-LOX. The vehicle is sized and the weights of its components are estimated using an existing methodology. The ascent and entry flight scenarios are calculated, and their features are compared with those of the existing reference winged-body design. The bent-biconic design is found to be competitive with the reference design in its performance. The new design is advantageous in that it can avoid aerodynamic instabilities at transonic speed range and is free from the problem of excessive heating at the wing leading edge as a result of shock/boundary-layer interactions, leading to a lighter liftoff weight. However, the viability of this new design is dependent on further development of para-wing technology.