Patent ID: 7080809

Claim:
A space transportation launch system comprising: a first vehicle and a second vehicle, the first vehicle and second vehicle each having a body defined by a top end, a lower end, a first side, an opposing second side, and a bottom surface, the first and second vehicle being releaseably connected in a vertical launch configuration wherein the bottom surface of each vehicle is joined facing each other; the body of the first vehicle containing at least one liquid rocket engine with a main fuel supply and a nozzle and at least one solid fuel rocket engine; the body of the first vehicle being larger than the body of the second vehicle; the at least one solid rocket engine being linearly aligned with the first side or the opposing second side and having a nozzle and a fuel tank, the solid rocket engine nozzle extend outward from the lower end of the body, the fuel tank extending linearly upward from the nozzle, the at least one liquid rocket engine being linearly aligned next to the at least one solid rocket engine, the liquid rocket engine nozzle extending outward from the lower end of the first vehicle body, the main fuel supply extending linearly upward from the liquid nozzle, the second vehicle being a trans-atmospheric lifting body orbiter wherein an integrated delta wing is formed on the lower end of the first side and the opposing second side of the body of the second vehicle to generate lift; and the first vehicle having means for separating from the second vehicle and landing.