PRELIMINARY DESIGN OF A HYDROGEN PEROXIDE THRUSTER FOR REMOTE SENSING SATELLITE
Deif, A., El-Zahaby, A., Makled, A., Khalil, M. (2015). PRELIMINARY DESIGN OF A HYDROGEN PEROXIDE THRUSTER FOR REMOTE SENSING SATELLITE. EKB Journal Management System, 16(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 – May 26 - 28, 2015), 1-12. doi: 10.21608/asat.2015.23014
Ah. Deif; A. El-Zahaby; Ah. El-S. Makled; M. Khalil. "PRELIMINARY DESIGN OF A HYDROGEN PEROXIDE THRUSTER FOR REMOTE SENSING SATELLITE". EKB Journal Management System, 16, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 – May 26 - 28, 2015, 2015, 1-12. doi: 10.21608/asat.2015.23014
Deif, A., El-Zahaby, A., Makled, A., Khalil, M. (2015). 'PRELIMINARY DESIGN OF A HYDROGEN PEROXIDE THRUSTER FOR REMOTE SENSING SATELLITE', EKB Journal Management System, 16(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 – May 26 - 28, 2015), pp. 1-12. doi: 10.21608/asat.2015.23014
Deif, A., El-Zahaby, A., Makled, A., Khalil, M. PRELIMINARY DESIGN OF A HYDROGEN PEROXIDE THRUSTER FOR REMOTE SENSING SATELLITE. EKB Journal Management System, 2015; 16(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 – May 26 - 28, 2015): 1-12. doi: 10.21608/asat.2015.23014

PRELIMINARY DESIGN OF A HYDROGEN PEROXIDE THRUSTER FOR REMOTE SENSING SATELLITE

International Conference on Aerospace Sciences and Aviation Technology
Article 75, Volume 16, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 – May 26 - 28, 2015, May 2015, Page 1-12  XML PDF (848.36 K)
Document Type: Original Article
DOI: 10.21608/asat.2015.23014
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Authors
Ah. Deif1; A. El-Zahaby2; Ah. El-S. Makled1; M. Khalil1
1Egyptian Armed Forces, Egypt.
2Tanta University, Egypt.
Abstract
In recent years, mono-propellant propulsion has attracted widespread attention in space due to excessive benefits of safety, low cost, simplicity, clean exhaust and high reliability. A 5N monopropellant Hydrogen Peroxide (H2O2) thruster is selected to be utilized with remote sensing (RS) satellites for attitude control and orbit correction. In the present paper, comprehensive theoretical analysis and design parameters are investigated. The effects of change in various design parameters are studied, such as operating pressures (7-16 bar), H2O2 concentration (70-95%) and initial temperature (25-70℃). The crucial design performance of thruster has been carried out by using thermo-chemical software package. A conceptual design was conducted to determine the dimensions of the thruster prototype including the injector plate, catalytic bed, retainer and nozzle part. 70℃ H2O2 preheating temperature might be needed for catalytic bed fast response. The results are described in the form of graphs and tables for the quick and easy analysis.
Keywords
Monopropellant; thrusters; space propulsion system; catalytic bed; Hydrogen Peroxide
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