Demonstration of Straight Nozzle Configuration Micro Thruster for Small Satellites


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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


S. Jason, S. Sulinets, A.S.Curiel, M.Sweeting, “Earthquake Forecast Science Research with a Small Satellite”, 16th Annual USU Conference on Small Satellites, SSC02-IX-5, 2002

J.M. Andringa, D.E. Hastings, “A Systems Study on How to Dispose of Fleets of Small Satellites”, J.M. Andringa submitted to the Department of Aeronautics and Astronautics at MIT

S.W.Janson, H.Helvajian, K.Breuer, “MEMS, Microengineering and Aerospace Systems”, AIAA-99-3802

H.Helvajian, S.Janson, and E.Y.Robinson, “Big benefits from Tiny Technologies: Micro-Nanotechnologoy Applications in Future Space Systems”, pp3-34 in Advancement of Photonics for Space, edited by E.W.Taylor, CR66, Critical Reviews of Optical Science and Technology, SPIE Press, Bellingham, WA, 1997

A.M. de Aragon et al., Micro/Nano Technologies for Space, Round Table at ESTEC, European Space Agency Report ESA WPP-091, March 1995.

K.Ramamurthi and G.Madhavan Nair, Evolution and Growth of Spacecraft Propulsion Systems, Journal of Spacecraft Technology, Vol. 8, No.1, Jan 1998.

NASA, Chemical Micro thruster Options (NASA Contract Report 198531,page 6, Oct 1996

C. Senthil Kumar, S. Elangovan, E. Rathakrishnan, Studies on Flow Characteristics in a Slanted Entry Nozzle Run by a Supersonic Stream, (2008) International Review of Aerospace Engineering (IREASE), 1 (3), pp. 277-283.

K. M. Pandey, A. P. Singh, Transient Analysis of Supersonic Combustion with Jet Co-Flow with Finte Rate Chemistry Mode, (2011) International Review of Aerospace Engineering (IREASE), 4 (2), pp. 93-102.

J.M.Bellerby, Hydrazine as a Propellant for Space Systems, Journal of the British Interplanetary Society, Vol.44, PP211-216, 1991.

B.W. Schmitz, Development of Design and Scaling Criteria for Monopropellant Hydrazine Reactors employing Shell 405 spontaneous Catalyst”, RRC-66-R-76, Volume-II.

Donald Platt, A Monopropellant Milli-Newton Thruster system for Attitude control of Nano satellite, 16th annual USU Conference on small satellites [SSC02-VII-4]


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