Abstract
Monopropellant propulsion systems are widely used especially for low cost attitude control or orbit correction (orbit maintenance). To optimize the total propulsion system, subsystems should be optimized. Chemical decomposition, aerothermodynamics, and structure disciplines demand different optimum condition such as tank pressure, catalyst bed length and diameter, catalyst bed pressure, and nozzle geometry. Subsystem conflicts can be solved by multidisciplinary design optimization (MDO) technique with simultaneous optimization of all subsystems with respect to any criteria and limitations. In this paper, monopropellant propulsion system design algorithm is presented and the results of the proposed algorithm are validated. Then, multidisciplinary design optimization of hydrazine propulsion system is proposed. The goal of optimization can be selected as minimizing the total mass (including propellant), minimizing the propellant mass (maximizing the Isp), or minimizing the dry mass. Minimum total mass, minimum propellant mass, and minimum dry mass are derived using MDO technique. It is shown that minimum total mass, minimum dry mass, and minimum propellant mass take place in different conditions. The optimum parameters include bed-loading, inlet pressure, mass flow, nozzle geometry, catalyst bed length and diameter, propellant tank mass, specific impulse (Isp), and feeding mass which are derived using genetic algorithm (GA).
Highlights
A single propellant is used to produce thrust forces in monopropellant propulsion systems
Because hydrazine exothermic reaction starts immediately after contacting with the catalysts, hydrazine monopropellant thrusters have an advantage in quick response, which is adequate for attitude control system [2, 5]
Catalyst bed length and diameter depend on thruster pressure and mass flow, but it should be noted that pressure drop in catalyst bed is related to bed-loading factor
Summary
A single propellant is used to produce thrust forces in monopropellant propulsion systems. Isp level is generally considered as the performance of the propulsion system [1,2,3]. In this regard, hydrazine has a performance of about 20% higher than hydrogen peroxide as a monopropellant. Monopropellant propulsion systems usually use blowdown feeding system which demands lower equipment. The decrease in feeding pressure decreases the thrust level and Isp level. The hydrazine monopropellant propulsion system breaks down into three more important subsystems including thruster subsystem, propellant tank subsystem, International Journal of Aerospace Engineering and pressurized feeding subsystem. Optimization algorithm (GA) is used to derive the optimum solution for every required total impulse and thrust level
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