Abstract: A combination of a plurality of rockets having an area ratio preferably in the range of 10 to 20, embedded in the interior of a nozzle of a scramjet with a modified aerospike exhaust nozzle provides a synergistic increase in total thrust greater than the sum of the thrusts of the rockets and the scramjet while increasing the speed and altitude range within which the scramjet is operable while reducing size and weight of the scramjet and avoiding a need for external rockets to reach operational speed for the scramjet, and to help with force when the Scramjet starts to starve for thrust production, and as a rocket for orbital insertion after scramjet cutoff with much higher expansion than conventional bell nozzle rockets such as the space shuttle main engine (SSME).

Abstract: The present invention is a novel method of designing a space vehicle. Unlike all previous known methods of designing a space vehicle, the present invention relies upon Radial Deviation Parameter to devise the flow field which provides the aero-dynamic effect as well as serving as an energy source to propel the space vehicle. The present invention would provide a single stage to orbit vehicle, which is a noted advancement over the conventional multi-stage to orbit vehicle. Furthermore, the teaching of the Radial Deviation Parameter design method can also be applied to trans-continent flight vehicles.