Abstract: A method and a system of assembling a launch vehicle vertically on an aboveground platform are presented in the present invention. The method of the present invention enables a rapid assembly of the launch vehicle; thus substantially reducing the final cost of the launch vehicle. The system of the present invention includes a plurality of specially designed tools that enable the rapid assembly of the launch vehicle.

Abstract: An orbital assist module and an interstage for a launch vehicle. The orbital assist module includes a cylindrical outer wall and a support structure secured to an inner surface of the cylindrical outer wall. The support structure defines a plurality of fuel tank supporting zones, at least one of the zones supporting a fuel tank by means of securing formations. A plurality of nozzles are connected to the fuel tanks by means of fuel lines and a plurality of valves are mounted in the fuel lines. The interstage comprises a cylinder having a leading and a trailing end and an explosive connector at the leading end for connecting the interstage to a trailing end of a launch vehicle motor. A connecting bracket is secured to the trailing end of the cylinder for connecting a second launch vehicle motor to the cylinder.

Abstract: A launch vehicle pedestal and an umbilical mast in which the pedestal includes a launch mount pedestal and four pedestal adapters. The launch mount pedestal includes a launch vehicle support base having an exhaust opening. Four legs extend downwardly from the support base and pedestal connecting means are secured to lower ends of each of the legs. The four pedestal adapters serve to secure the legs to existing launch vehicle support posts, the pedestal adapters each having adapter connecting means complementarily engageable with the pedestal connecting means. The umbilical mast comprises a plurality of round cylindrical segments connected by means of connectors at their ends. The connectors comprise radially extending flanges with circumferential holes in them. The mast further includes an access door and at least one opening in at least one of the segments for electrical cables and an air conditioning duct.

Abstract: A launch vehicle system includes at least one primary solid fuel motor, a shroud for housing a payload and an attitude control system. The attitude control system is connected intermediate the primary solid fuel motor and the shroud. It has a circular outer wall and liquid fuel motors for exerting thrust along a longitudinal axis of the rocket system, and for controlling pitch, roll and yaw of the shroud. The attitude control system includes a support structure defining three pairs of fuel tank supporting zones, each zone having laterally extending supporting brackets connected to the outer wall. The attitude control system also includes connecting tubing for connecting outlets of sets of fuel tanks consisting of one, two and three pairs of fuel tanks to the liquid fuel motors.