|Marcom Aeronautics & Space
was founded in 2002 and has been designing and developing the
CHEETAH-1 CSLV. Capable
of delivering a 1,000 kg payload into Low Earth Orbit.
The company has submitted several proposals to
government in this regard and would like to become involved in a government/private
sector satellite launch initiative.
The CHEETAH-1 is a two-stage design. The vehicle will be powered by two regenerative cooled liquid propellants, gas-generator cycle rocket engines. The first stage would be powered by a single rocket engine with a total sea level thrust of 860 kN, while the second stage would have a single 58-kN engine. The complete rocket would stand 31.7 m tall, including the two stages, the interstage and the nose cone.
It would be able to put a 1,000-kg payload into a 200-km orbit at an inclination of 34 degrees, or a 650-kg payload into a 200-km orbit at a declination of 90 degrees, or a 650-kg payload into a 200-km polar orbit. It would be able to accommodate payloads with a maximum diameter of 1.6 m, and a maximum length of 4.2 m.
CHEETAH 1 CSLV
Two stage, expendable launch vehicle designed to provide launch services to inclined, polar and sun-synchronous low Earth orbits.
200 km, 34 deg 1000 kg
200 km, 90 deg 650 kg
Sun-synchronous Orbit: 800 km, 98.6 deg 439 kg
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.
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.
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
Semi-monocoque Aluminium skin/stringer and carbon fiber matrix composites. Tanks, Aluminum alloy.