A low cost, on demand, dedicated launch system is provided for placing micro
satellites
or space-based instruments at orbital and sub-orbital altitudes and velocities.
The invention describes a space launch vehicle (SLV) that incorporates a single,
integrated guidance, navigation, and control unit (GNCU) that performs all guidance
and control for the SLV from main stage ignition to orbital insertion. The GNCU
can remain with the payload after orbital insertion to provide satellite station
keeping and orbital maneuvering capability. The use of a single integrated avionics
unit for all guidance, navigation, and control simplifies the SLV, reducing weight
and significantly reducing cost. In addition, this architecture allows for a combined
launch and satellite bus system as the GNCU can also be used as a satellite bus.
This further reduces cost and increases the payload capacity to orbit by optimizing
the use of launch vehicle and satellite bus subsystems and reducing non-instrument
mass delivered to orbit. All support functions are provided by the IDMV. This approach
represents a significant improvement over conventional systems, especially with
respect to the orbital launch of payloads less than about 100 kg.
