A space launch system comprising a shuttle or a rocket having: a nose section (101, 916) comprising a nose coupling surface; a tail section comprising a tail coupling surface facing the nose coupling surface; and a mast (102, 602, 702) coupling the nose and tail sections (101, 103), the mast (102, 602, 702) being configured to expand and retract to displace the nose and tail sections (101, 103) within a range of distances from one another while the shuttle or rocket is in orbit, wherein expansion of the mast allows for release of a releasable payload module while in orbit, and retraction of the mast allows for the shuttle or rocket to retract into a retracted state while in orbit; wherein in the retracted state, the nose and tail sections (101, 103) are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to a smaller extra payload module which is integrated with and configured to return with the orbiter located between the nose and the tail sections (101, 103), the extra payload module being integrated with and configured to return from orbit with the shuttle or rocket when the shuttle or rocket is in the retracted state; and the shuttle or rocket further comprising aerodynamic surfaces located on either one or both of the nose and tail sections (101, 103), wherein the aerodynamic surfaces are configured such that the shuttle or rocket, in its retracted state, is capable of effectuating a horizontal landing, wherein the aerodynamic surfaces are configured only to support a load of the shuttle or rocket and if provided with the smaller extra payload module which is integrated with and configured to return with the orbiter for landing in its retracted state and wherein the aerodynamic surfaces are incapable of supporting loads in addition to the load of the shuttle or rocket in its retracted state. a nose section (101, 916) comprising a nose coupling surface; a tail section comprising a tail coupling surface facing the nose coupling surface; and a mast (102, 602, 702) coupling the nose and tail sections (101, 103), the mast (102, 602, 702) being configured to expand and retract to displace the nose and tail sections (101, 103) within a range of distances from one another while the shuttle or rocket is in orbit, wherein expansion of the mast allows for release of a releasable payload module while in orbit, and retraction of the mast allows for the shuttle or rocket to retract into a retracted state while in orbit; wherein in the retracted state, the nose and tail sections (101, 103) are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to a smaller extra payload module which is integrated with and configured to return with the orbiter located between the nose and the tail sections (101, 103), the extra payload module being integrated with and configured to return from orbit with the shuttle or rocket when the shuttle or rocket is in the retracted state; and the shuttle or rocket further comprising aerodynamic surfaces located on either one or both of the nose and tail sections (101, 103), wherein the aerodynamic surfaces are configured such that the shuttle or rocket, in its retracted state, is capable of effectuating a horizontal landing, wherein the aerodynamic surfaces are configured only to support a load of the shuttle or rocket and if provided with the smaller extra payload module which is integrated with and configured to return with the orbiter for landing in its retracted state and wherein the aerodynamic surfaces are incapable of supporting loads in addition to the load of the shuttle or rocket in its retracted state.