Multidisciplinary Design Optimization of Hydrogen Peroxide Monopropellant Propulsion System using GA and SQP

Abstract

An intense simplification in production, storage and handling of hydrogen peroxide develop a renewed interest in hydrogen peroxide thrusters especially for low cost attitude control or orbit correction (orbit maintenance). Chemical decomposition, aerothermodynamics flow and structure demand different optimum conditions such as tank pressure, catalyst bed pressure, concentration of H 2 O 2 and geometry. These parameters play important role in propulsion system's mass and performance. Discipline conflicts are solved by Multidisciplinary Design Optimization (MDO) techniques with synchronized optimization for all subsystems respect to any criteria and limitations. In this paper, monopropellant propulsion system design optimization algorithm is presented and result of the design algorithm is validated. Results of the design algorithm have been compared with data of two different operational thrusters. According to the results, the proposed model can suitably predict total mass and performance with errors below than 10%. Then, MDO framework is proposed for the monopropellant propulsion system. Optimum propellant mass, thrust level, mass flow rate, nozzle geometry, catalyst bed length and diameter, propellant tank mass, feeding subsystem mass and total mass are derived using hybrid optimization (GA+SQP) for two space missions.

A kriging based multi objective gray wolf optimization for hydrazine catalyst bed

“…These thrusters use catalytic decomposition to change the propellants chemical energy to thermal energy (Larson et al 1995;Sutton & Biblarz, 2010). Although Hydrazine (Adami et al, 2015a;Jung et al, 2013;Rath et al, 1996;Schmuland et al, 2011), hydrogen peroxide (Adami et al, 2015b;Amrousse et al, 2011;Rhee et al, 2000;Pasini et al, 2011;Whitehead, 1998), Hydroxyl Ammonium Nitrate (HAN) (Chen et al, 2016), De-Methyl Amino Ethyl Aside, hydrazinium nitro formate (HNF) and Nitro oxide (Lohner et al , 2008) are proposed as liquid monopropellant; hydrazine has received a great deal of attention for many years for space applications that require very high reliability (Hwang et al, 2012).…”

Multidisciplinary Design Optimization and Analysis of Hydrazine Monopropellant Propulsion System

“…The feeding subsystems consist of feed lines (tubes and ducting), regulator, valves, tank, and pressurizer gas. Some of these components can be ignored in the conceptual phase because of having the same effect in various concepts [1]. Most parts of the feeding subsystem mass (changing by concepts) are connected to the gas tank mass and pressurizer gas mass [1,2].…”

“…Some of these components can be ignored in the conceptual phase because of having the same effect in various concepts [1]. Most parts of the feeding subsystem mass (changing by concepts) are connected to the gas tank mass and pressurizer gas mass [1,2]. The volume of propellant tank and feeding pressure specify the feeding subsystem geometry and mass.…”

“…Hydrazine (N 2 H 4 ) is known as the most commonly used monopropellant. 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.…”

Optimization of 10 N Monopropellant High Test Peroxide Thruster for Space Applications

“…The MPT system uses a single propellant that reacts or decomposes by specific catalyst bed to produce thrust forces. The specific impulse (I sp ) is mostly considered as the performance of the propulsion system [1,2]. The MPT system has medium performance at low cost where the I sp is range between 130 and 280s, being developed for landing and altitude control of the spacecraft, positioning and for the Reaction Control System (RCS) of satellites that is used since 1940s to provide operations of orbit maintenance, orbit transfer and orbit correction [3][4][5][6].…”