Patent ID: 6543715
Filing Date: 2003-04-08
Classification: B64D,B64G

Abstract:
An aerospace system comprising a carrier aircraft, a launch vehicle and a payload, wherein the launch vehicle with liquid fuel propulsion units is placed inside a fuselage of the carrier aircraft within a transport and launch container with thermal insulation with the aid of support units in at least in two areas, an airtight pneumatic chamber is formed between a blind end of the transport and launch container and an end of the launch vehicle, which chamber incorporates airborne elements of units for supplying the launch vehicle with propellant and working mediums, elements of a draining unit, elements of a unit for replenishing the liquid fuel propulsion units with propellant, wherein all said draining and replenishing units electrical connections and airborne elements are connected to the end of the launch vehicle by pull-off couplings, wherein the transport and launch container is provided with a pneumatic ejection unit of the launch vehicle, made in the form of a high pressure source connected by stop valves to the pneumatic chamber and positioned in the transport and launch container, the otherâ€”free end of which is closed with a frangible membrane and is hermetically connected to the perimeter of the port in the fuselage for exit of the launch vehicle from the carrier aircraft.