Satellite launch system
View Patent ↗A system for launching aerospace payloads includes a wingless, unmanned modified lifting body spacecraft ( 100 ), with a payload compartment in the forward section of the spacecraft. The spacecraft is propelled by hybrid rockets clustered in the aft section of the spacecraft. Reaction control system (RCS) modules control the flight path and its associated avionics hardware and software. This system also includes a carrier aircraft ( 200 ) configured to air-launch the spacecraft. The carrier aircraft includes a flight operations control system, which monitors the spacecraft's payload and monitors and controls launch and flight operations of the spacecraft. A ground-based mission control system monitors and controls the spacecraft's payload and monitors and controls the launch and flight operations of the spacecraft.
1 . A system for launching aerospace payloads, comprising:
an unmanned lifting body spacecraft including a payload compartment in a forward section of said spacecraft,
rockets provided in an aft section of said spacecraft,
a reaction control system (RCS) module configured to control a flight path of said spacecraft, and associated avionics hardware and software;
chines comprising wye-shaped stabilizers, wherein each arm of the wye is canted outboard from the vertical, and wherein a horizontal arm of the wye is fitted with elevons; and
a carrier aircraft configured to air-launch said spacecraft.
2 . The system claim 1 , further comprising a transport dolly comprising a wheeled, concave chassis configured to support said spacecraft during transit and loading.
3 . The system of claim 2 , wherein the transport dolly comprises lead-in guidance components and a power supply.
4 . The system of claim 2 , wherein the transport dolly comprises a structural support for propellant boosters.
5 . The system of claim 1 , further comprising a truncated nose cone.
6 . The system of claim 1 , further comprising a payload bay.
7 . The system of claim 1 , further comprising a safety monitoring system, wherein the safety monitoring system comprises at least one sensor and at least one alarm.
8 . The system of claim 7 , wherein the at least one sensor monitors at least one of: a sealing mechanism, temperature, an oxidizer leakage, and fire.
9 . The system of claim 7 , wherein the at least one alarm is an audible alarm.
10 . The system of claim 1 , further comprising a physical interface that attaches to a set of hard points bound to load-bearing structural members of a carrier aircraft, wherein the physical interface secures and stabilizes said spacecraft with the carrier aircraft during takeoff and flight.
11 . The system of claim 1 , further comprising composite panels enclosing the payload compartment.
12 . The system of claim 11 , wherein the composite panels join at a horizontal chine line of said spacecraft.
13 . The system of claim 11 , wherein the composite panels are configured to be jettisoned via pyrotechnical charges during flight.
14 . The system of claim 1 , further comprising a computer-readable medium storing operational specifications for a spacecraft launch system.
15 . The system of claim 14 , wherein the operational specifications comprises one or more of: instructions for standard, irregular, and emergency procedures, a checklist for one or more phases of launch operations, and configuration data for spacecraft and carrier aircraft integration.
16 . The system of claim 1 , further comprising avionics hardware and software configured to perform one or more of: monitoring the payload and controlling said spacecraft.
17 . The system of claim 1 , wherein the RCS module comprises a pressurized tank of monopropellant, a catalyst chamber, and multiple exhaust ports.
18 . The system of claim 17 , wherein the monopropellant comprises concentrated hydrogen peroxide and the catalyst comprises tungsten mesh.
19 . The system of claim 1 , further comprising a propulsion module comprising the rockets, structural members, and avionics.
20 . The system of claim 1 , wherein said spacecraft is configured for suborbital and orbital missions.