Design, test and build of a monopropellant thruster using 85% hydrogen peroxide
Deif, A., Makled, A., Khalil, M., Elshaar, Y. (2021). Design, test and build of a monopropellant thruster using 85% hydrogen peroxide. EKB Journal Management System, 19(19), 1-13. doi: 10.1088/1757-899X/1172/1/012043
A Deif; A El-S Makled; M K Khalil; Y Elshaar. "Design, test and build of a monopropellant thruster using 85% hydrogen peroxide". EKB Journal Management System, 19, 19, 2021, 1-13. doi: 10.1088/1757-899X/1172/1/012043
Deif, A., Makled, A., Khalil, M., Elshaar, Y. (2021). 'Design, test and build of a monopropellant thruster using 85% hydrogen peroxide', EKB Journal Management System, 19(19), pp. 1-13. doi: 10.1088/1757-899X/1172/1/012043
Deif, A., Makled, A., Khalil, M., Elshaar, Y. Design, test and build of a monopropellant thruster using 85% hydrogen peroxide. EKB Journal Management System, 2021; 19(19): 1-13. doi: 10.1088/1757-899X/1172/1/012043

Design, test and build of a monopropellant thruster using 85% hydrogen peroxide

International Conference on Aerospace Sciences and Aviation Technology
Article 45, Volume 19, Issue 19, April 2021, Page 1-13  XML PDF (1.03 MB)
Document Type: Original Article
DOI: 10.1088/1757-899X/1172/1/012043
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Authors
A Deif1; A El-S Makled2; M K Khalil3; Y Elshaar3
1Space Technology Centre, Cairo, Egypt.
2Faculty of Engineering, Zagazig University, Zagazig, Egypt.
3Military Technical College, Cairo, Egypt.
Abstract
The objective of this research is to design, build, and test about a 5N Hydrogen Peroxide(H2O2) monopropellant thruster (MPT). It is utilized in remote sensing satellites for attitude control and orbit manoeuvres. The MPT uses high test peroxide (HTP) of 85 % concentration. Firstly, H2O2 ≈85% concertation by weight is prepared in the laboratory. A distillation and filtration units are built. The distillation and filtration processes are performed. Next, the design of the monopropellant thruster is done based on the developed mathematical model using NASA CEA rocket performance code. The test facility is developed which consists of the thruster, the feeding system, static test stand and data acquisition system with measuring sensors. An experimental test stand is designed and fabricated with Pendulum thrust mechanism for measurements of thrust. Finally, the silver catalyst is prepared and packed inside the MPT chamber where silver screens of high purity 99.96 % are used. The 10-firing tests are conducted under atmospheric conditions. The firings performed without heating are not completely successful. The analysis of the results shows that the thruster has a thrust range from 3.8-4.2 N. The performance of thruster starts to decay after consuming 6 kg of stabilized H2O2. The specific impulse (Is) is evaluated to be ≈ 93-97s at decomposition pressure of ≈10 bars and mass flow rate ≈4.18 g/s. The performance evaluation is judged to be successful. However, using the whole potential of the 85 % concentrated H2O2, is expected to increase (Is) up to ≈111.5s.
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