The GSAT-4 Electrical Propulsion Subsystem based on the KM-45 HET

Paper number

IAC-07-C4.4.01

Author

Dr. Oleg A. Gorshkov, Keldysh Research Center, Russia

Coauthor

Mr. M. Belikov, Keldysh Research Center, Russia

Coauthor

Mr. Viatcheslav Muravlev, Keldysh Research Center, Russia

Coauthor

Dr. A. Shagayda, Keldysh Research Center, Russia

Coauthor

Mr. Krishna Mohan Shanbhogue, Indian Space Research Organisation (ISRO), India

Coauthor

Mr. Premkumar Somanathan, Indian Space Research Organisation (ISRO), India

Coauthor

Mr. Jayaraman Maruthia, LPSC, ISRO, India

Coauthor

Mr. Vijayan Nandalan, Indian Space Research Organisation (ISRO), India

Year

2007

Abstract

This paper describes results of development and qualification tests of electric propulsion system (EPS) for GSAT-4 spacecraft. This EPS includes low power Hall effect thrusters KM-45, power processing and control system (PPCS), propellant storage and feed system (PSFS).

The KM-45 thruster was developed in Keldysh Research Center. This thruster can operates at power range between 200 W and 400 W with nominal value 330 W. In the nominal mode it provides 18 mN thrust and 1450 s specific impulse. The thruster has passed qualification tests including vibro-tests, shock tests, transportation tests, thermo-cyclic tests. The predicted value of lifetime is 3500 hours it is based on the results of 1000-hour life tests.

The ‘G4-PPCS’ power processing and control system was developed in LPSC, ISRO. This unit comprises of Anode supply, Heater supply, Keeper supply, Magnet supply modules. ‘G4-PPCS’ can operate from a 28 to 42 VDC unregulated power bus of the GSAT-4 spacecraft consuming about 420Watts. The ‘G4-PPCS’ has passed the thermo-vacuum tests, EMI/EMC tests, transportation tests, and the integrated performance mapping test with the KM-45 thruster.

The ‘G4-XFS’ propellant storage and feed system was developed in LPSC, ISRO. The ‘G4-XFS’ can operate for a storage pressure range of 150 to 5 bar and regulate the pressure by an Electronic Pressure Regulator (EPR) and a redundant conventional Xenon Mechanical Pressure Regulator (XMPR) to 0.7 bar. The flow can be throttled using the EPR from 80

EPS elements for flight test have been manufactured and its integration to the GSAT-4 spacecraft is in progress. Flight tests will take place onboard spacecraft GSAT-4. It’s launch planned in 2008. The EPS will be used for north-south station keeping.

Abstract document

IAC-07-C4.4.01.pdf

Manuscript document

IAC-07-C4.4.01.pdf (🔒 authorized access only).

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