Demonstration of Straight Nozzle Configuration Micro Thruster for Small Satellites

CH. Sreenivasa Rao(1*), K. Shambayya(2), H. S. Venkatesh(3), B. K. Venkataramu(4)

(1) Scientist, Indian Space Research Organisation, Department of Space, Bangalore, India
(2) Scientist, Indian Space Research Organisation, Department of Space, Bangalore, India
(3) Scientist, Indian Space Research Organisation, Department of Space, Bangalore, India
(4) Scientist, Indian Space Research Organisation, Department of Space, Bangalore, India
(*) Corresponding author


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Abstract


This paper provides the details on assembly and process involved in realization of Straight Nozzle Configuration Micro (SNCM) Thruster. SNCM Thruster finds suitable application with low level of thrust in the range of 0.5 - 1.0N for initial attitude acquisition, attitude control and station keeping of spacecraft. Catalyst bed heater is provided on chamber to heat to around 100°C, by which Catalytic decomposition of propellant produces hot exhaust gases . These exhaust gasses are passed through convergent divergent nozzle to produce the desired thrust. High Altitude Firing Test was carried by simulating space environment on SNCM thruster with varying injection pressures. SNCM Thruster is capable to delivered thrust range from 0.5 to1.0N for the given injection pressure 1.0 to 2.4MPa respectively. The specific impulse of the SCNM thruster with hydrazine is propellant is around 200 seconds.
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Keywords


Decomposition; Heater; Nozzle; Propellant; Propulsion; Spacecraft; Thrust

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References


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