The Cyclone-4 LV is intended for timely and high-accurate injection of a single spacecraft (SC) or group of various SCs into circular, geostationary and sun-synchronous orbits
It is the newest and the most powerful version of the Cyclone launchers family. These launchers are in operation from 1969 and have recommended themselves as the most reliable in the world. Design of the Cyclone-4 LV meets current requirements for the means of SCs launching.
The Cyclone-4 LV is the three stage rocket of tandem arrangement created on the basis of existing Cyclone-3 LV:

• under use of the Cyclone-3 LV first and second stages with minimum improvements and maximum retention of production technology;
• with allowance for implementation of novel technical solutions.

• elaboration of the new third stage with increased propellant stock and the main engine on the basis of RD861K LRE with restart capability;
• novel up-to-date control, safety and measurement systems;
• new payload fairing;
• separate payload assembly with provision of cleanliness level under the fairing required for the SC zone;
• propellant filling at the launch pad, from the first stage end face, for all the stages;
• possibility to conduct thermostatting of the payload cavity with high-pressure air in the case of launch cancellation.

The complex is able to ensure 6 or more launches per year. At present the National Space Agency of Ukraine has signed an Agreement with the Brazil Space Agency about creation of the Space Rocket Complex Cyclone-4. The launches will be performed from the Alcantara Space Center, and the first one is planned for February of 2012.

Cyclone-4LV performance (SC mass, orbit altitude and inclination) at SC launching into circular and elliptic orbits.

Cyclone-4LV performance at SC launching into circular and elliptic orbits of 90 deg inclination.

Cyclone-4LV performance at SC launching into sun-synchronous orbits

Payload envelope

Technical characteristics Lift-off mass (without PL mass), kg - first stage - second stage - third stage 127400 51700 13380 Propellants for all stages: - oxidizer - fuel АТ NDMA Propellant mass, kg: - first stage - second stage - third stage 121000 49000 9120 Vacuum thrust, tf - first stage - second stage - third stage 297,4 99,5 0,764