Description:
Two stage, expendable launch vehicle designed to provide launch services to inclined, polar and sun-synchronous low Earth orbits.
Performance Summary:
200 km (108 nmi), 34 deg 1000 kg (2205 lbm)
200 km (108 nmi), 90 deg 650 kg (1433 lbm)
Space Station Orbit: 407 km (220 nmi), 51.6 deg 810 kg (1786 lbm)
Sun-synchronous Orbit: 800 km (432 nmi), 98.6 deg 439 kg (968 lbm)
Propulsion:
Two stages, each incorporating a regeneratively cooled, turbo-pump driven liquid rocket engine operating on a gas generator thermodynamic cycle. Burning a mixture of liquid Oxygen and refined Kerosene, the first stage booster is designed to produce 86 tons of sea-level thrust incorporating hydraulic thrust vector control for pitch, yaw and roll control. The second stage is designed to produce 5.8 tons of vacuum thrust steered similarly via electromechanical actuators.
Avionics:
Triple redundant flight control computers, receiving navigation data from triple redundant strap-down inertial navigation systems provide vehicle ascent control. Real time telemetry data, flight termination and ground tracking systems provide for reliability and safety of the system during ascent.
Payload Accommodations:
Usable Diameter 1.6 m
Usable Cylindrical Length 2.4 m
Usable Conical Length 1.8 m
Maximum Axial Acceleration 6.5 g
Maximum Lateral Acceleration 2.0 g
Fuselage
Semi-monocoque Aluminium skin/stringer and carbon fiber matrix composites. Tanks, Aluminum alloy.
