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Unformatted text preview: Year 2010 Month 10 Day 10 HYDROGEN PEROXIDE THRUSTER EXPERIMENT Aerospace Engineering Laboratory II Name : Martin Suhartono Student ID : 20106182 Martin Suhartono - 20106182 Page 2 1. Objective To familiarize ourselves with the experimental process of monopropellant thruster as well as to evaluate the performance by analyzing the experimental result 2. Introduction and Background A thruster is generally a propulsive device used in spacecraft which plays an important role in installing a satellite, or any outer space device in that sense, to the desired orbit. Thrusters are generally classified into two categories; chemical and electrical/electronic depending on the source of its energy. The electrical thrusters have high specific impulse but are rarely used due to its low thrust level generated as well as weight constraint. In contrast, the chemical thrusters, like the monopropellant or bipropellant thrusters, are able to provide high level of thrust and are significantly lighter. Hence, the chemical thrusters are more commonly used for launch vehicle control system. Specifically, monopropellant thrusters can generate high level of specific impulse with rarely any failure and thus they are highly recyclable. Compared to bi-propellant thrusters, the monopropellant thrusters are more advantageous due to its lighter mass and smaller volume and hence it’s reduced complexity. Monopropellant thrusters are then extensively used for launch vehicle attitude control. A common example of the propellant (chemical) used in a chemical thruster is hydrogen peroxide, H 2 O 2. Hydrogen peroxide in high concentration of around 90% readily decomposes into steam and oxygen. Hence, unlike other hydrazine compounds, it is not toxic. For thruster application, hydrogen peroxide is pumped into a reaction chamber where a catalyst such as silver or platinum is used to cover the chamber wall. The high temperature steam generated through the decomposition is then expelled through a nozzle where it consequently generates thrust. In this experiment, we will try to evaluate the performance of such hydrogen peroxide thruster. The evaluation of thruster performance is correlated with the degradation rate of the propellant. The following formula indicates the decomposition rate based on characteristic velocity....
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This note was uploaded on 03/19/2012 for the course AEROSPACE MAE309 taught by Professor Kwonsejin&hyunchulshim during the Spring '12 term at Korea Advanced Institute of Science and Technology.
- Spring '12