The Integration and Test of a 5-N Hydrazine Propulsion System

Propellant Grade Hydrazine in Mono/Bi-propellant Thrusters: Preparation and Performance Evaluation

“…The reduced activity of the catalyst results in a drop in chamber pressure and degradation of the thruster performance due to incomplete decomposition of hydrazine. The decomposition of hydrazine on Shell 405 can be described by the reaction 6,[10][11] . Controlling of the degree of dissociation of NH 3 generated from N 2 H 4 decomposition to achieve better characteristic velocities of the thruster, became the basic criterion in the design of injector and catalytic reactor 12 .…”

“…Hydrazine thrusters have been widely used in missile and satellite attitude control, velocity correction of spacecraft, and gas generation to provide auxiliary power in aviation because of simplicity and reliability (monopropellant); lowest cost propulsion system (other than cold gas); space storable for long periods (> 12 years demonstrated); low thrust capability and moderate thrust levels available (≤ 400 N) [1][2][3][4] . In the design of the hydrazine thruster assembly, the collective effects of the injector type, the amount of catalyst packed, and the shape of the catalytic reactor, were the primary concerns [5][6] . These thrusters have limited life because of voids which ultimately occur due to catalyst loss.…”

“…The performance evaluation of propellant grade hydrazine was tested using self-designed 5 N and 22 N hydrazine propulsion systems at high altitude 6,[17][18] . Low cost catalysts were tested in 1 N, 35 N, and 400 N hydrazine thrusters 19 .…”