Cyclone-2K LV is a new version of Cyclone-2 LV, created by Yuzhnoye State Design Office and manufactured by Yuzhny Mashinostroitelny Zavod PA. It is a space transport system designed on the basis of components with proven high reliability and the best flight and service characteristics traditionally belonged to the launch vehicles of Cyclone family.

• Improved performance;
• High accuracy of spacecrafts (SC) injection into specified orbits;
• Safety of the handling personnel owing to automatization of prelaunch processing and launch;
• Short time of prelaunch preparation and performance of the launch (from 5 to 24 hours);
• Minimum amount of the handling personnel.

Cyclone-2K LV provides possibility of various SC launches from the Baikonur Space Center in Kazakhstan. Preparation of the SC and its mating with the LV are performed by experienced staff in buildings with all required equipment, including zones of integration and testing certified under cleanliness class of 100 000 (FED-STD-209E). The Cyclone-2K LV is able to launch from the Baikonur Space Center:

• SC of 2000kg mass into the circular orbit of 1000 km altitude and 65° inclination;
• SC of 2000kg mass into the sun-synchronous orbit of 700 km altitude.

Power characteristics of the Cyclone-2K LV at the
third stage flight limited by the time of 1400 sec.

i=65° Нcirc, km SC mass, kg 500 2460 750 2235 1000 1980 1100 1840 1250 1570 1380 1200 1570 550 1670 0

SSO Нcirc, km SC mass, kg 500 1790 800 1460 1000 1290 1500 810 2000 180 2110 0

The main components of the Cyclone-2K LV are: the first stage (4); the second stage with adapter (3); upper stage ADU-600 (2) and nose fairing (1).
The nominal length is 39.952 m and traditional for the Cyclone family diameter of the two first stages is 3.0 m.

	Characteristics	First stage	Second stage	Upper stage
	Mass, kg:
	- dry	6150	2620
	- filled	127424	51675
	Total propellant mass, kg	121124	49075	600
	Dimensions, m:
	- length	18,87	8,884
	- diameter	3,0	3,0
	Main engine vacuum thrust, kN	2797,2	955,2
	Steering engine vacuum thrust, kN	334,5	55,0
	Specific impulse, s	300,33 SL	313,8
	Main engine propellant flowrate, kg/s	1009,46	321,91
	Steering engine propellant flowrate, kg/s	114,56	19,71

The payload unit consists of the nose fairing, SC and SC adapter with isolating membrane. The payload unit represents a separate technological assembly and is intended to locate a payload (SC) under provision of all required environment conditions during all service phases of the payload and LV. It is designed with allowance for cleanliness requirements and is intended for operation in an environment corresponding to the class М 6.5 (100000) under FED-STD-209E.The payload (SC) envelope under the nose fairing is determined preliminary on the basis of data for payload location on the Cyclone-3 LV; its volume is about 22.5 m3.

The short time of prelaunch preparation (15 months or less) ensures timely launch service for the customers. High flight characteristics, wide experience and high flight reliability in combination with acceptable cost are recognized properties of the Cyclone-2K LV. This unique combination may provide all advantages for the customers for implementation of launches under flexible price politics at exceptionally low risk level. The launch vehicles of Cyclone family have impressive statistic of successful launches - 98% - confirming their exceptionally high reliability at launches of various spacecrafts. Launch statistics Cyclone-2