| Design, build and test a Mono-propellant Thruster using 85% Hydrogen Peroxide |
| Paper ID : 1069-ASAT19-FULL |
| Authors: |
|
Ahmed Mohamed DeifAllah * Space Technology Center |
| Abstract: |
| The objective of this research is to design, build, and test about 5N Hydrogen Peroxide(H2O2) monopropellant thruster (MPT). It is utilized in remote sensing satellites for attitude control and orbit maneuvers. The MPT uses high test peroxide (HTP) of 85 % concentration. Firstly, H2O2 ≈ 85% by weight is prepared in laboratory. A distillation unit is built, and 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 feed 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 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 evaluated to be ≈ 93-97s with the decomposition efficiency ≈ 84-87% 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, the Is expected to increase up to ≈111.5s |
| Keywords: |
| Spacecraft propulsion, monopropellant, hydrogen peroxide, catalyst bed, thruster, green propellant |
| Status : Paper Accepted (Oral Presentation) |
