Flight testing of Indian Cryogenic Upper Stage
- Paper number
IAC-14,C4,1,6,x25201
- Author
Dr. Vanniyaperumal Narayanan, Indian Space Research Organization (ISRO), India
- Coauthor
Mr. Dathan M C, Indian Space Research Organization (ISRO), India
- Coauthor
Mr. SURESH MS, LPSC, ISRO, India
- Coauthor
Dr. K. Sivan, Indian Space Research Organization (ISRO), India
- Coauthor
Mr. VISHNU KARTHA NR, LPSC, ISRO, India
- Coauthor
Mr. KARTHIKESAN D, LPSC, ISRO, India
- Coauthor
Mr. Jose paul Jose paul, LPSC, ISRO, India
- Year
2014
- Abstract
Indigenous Cryogenic Upper Stage (CUS) developed by Indian Space Research Organization (ISRO) is successfully flight tested in GSLV-D5 mission on 5th January 2014. This stage is powered by a cryogenic engine operating in staged combustion cycle using liquid oxygen and liquid hydrogen. The CUS has a total propellant loading of 12,808 kg. The engine unit has a fixed main engine and two vernier steering engines with a total nominal thrust of 73.55 kN and uprated thrust capability of 109.5%. The CUS operates for duration of 715s with a specific impulse of 452s. The propellants are stored in two separate tanks made of aluminium alloy and insulated with special foam based insulation. The tanks are connected by an inter tank structure of titanium alloy construction. The stage has number of fluid circuits to facilitate propellant chilling, filling, thermal conditioning and tank pressure management. The major subsystems of the engine are main Engine, steering engines, booster turbo pumps, main turbopump, pre-burner, control components, ignitors, pyro devices and closed loop thrust and mixture ratio control systems. Pitch, yaw and roll control is accomplished by gimballing the steering engines. The main turbine is driven by the hot gas generated by the pre-burner which is regeneratively cooled. Pyrogen igniters are used for the main engine, steering engines and pre burner to initiate combustion. As part of development, the CUS main engine has undergone 39 hot tests and the steering engine has undergone 77 hot firings in engine and stage configurations. The flight articles after acceptance tests have been assembled with the stage system after carrying out health checks. In GSLV-D5 flight, all the pre-flight activities went off smoothly and the required lift off conditions were achieved. The on-board propellant chilling was normal and the required conditions at the time of engine start were achieved. The engine start and the ignition were as expected. After smooth build up in the transient phase, the engine attained the nominal thrust, operated in the 109.5% thrust level for 400s and continued in the nominal thrust level till shut down. During the steady state operation, the engine parameters were matching closely with the pre-flight prediction. The start and shut down impulses were matching closely with the pre-flight nominal prediction which ensured a precise orbit for the satellite. The majestic performance of the Indian cryogenic stage in GSLV-D5 flight has demonstrated ISRO’s capability in developing cryogenic stage for launch vehicles.
- Abstract document
- Manuscript document
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