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Jeremy Agte, O. Weck, J. Sobieszczanski-Sobieski, P. Arendsen, A. Morris, M. Spieck (2009)
MDO: assessment and direction for advancement—an opinion of one international groupStructural and Multidisciplinary Optimization, 40
N. Othman, S. Krishnan, W. Ali, M. Jaafar (2011)
Design and testing of a 50N hydrogen peroxide monopropellant rocket thruster, 33
H. Schoeyer, P. Korting, W. Veltmans, J. Louwers, A. Heijden, H. Keizers, R. Berg (2000)
An overview of the development of HNF and HNF-based propellants
S. Defoort, M. Balesdent, P. Klotz, P. Schmollgruber, J. Morio, J. Hermetz, C. Blondeau (2012)
Multidisciplinary Aerospace System Design: Principles, Issues and Onera Experience
Donald Platt (2002)
A Monopropellant Milli-Newton Thruster System for Attitude Control of Nanosatellites
Hai Huang, Haichao An, Wenrui Wu, Lingyan Zhang, Beibei Wu, Weipeng Li (2014)
Multidisciplinary design modeling and optimizationfor satellite with maneuver capabilityStructural and Multidisciplinary Optimization, 50
A. Prince, R. Carpenter, T. Boardman, T. Abel, S. Claflin (2000)
Design and testing of an upper stage hybrid propulsion system using hydrogen peroxide oxidizer
Y. Chan, H. Hsu, Y. Chao (2011)
Development of a HTP Mono-propellant Thruster by Using Composite Silver Catalyst
A. Sorge, M. Turco, G. Pilone, G. Bagnasco (2004)
Decomposition of Hydrogen Peroxide on MnO2/TiO2 CatalystsJournal of Propulsion and Power, 20
Yongjun Moon, Chul Park, S. Jo, Sejin Kwon (2014)
Design specifications of H2O2/kerosene bipropellant rocket system for space missionsAerospace Science and Technology, 33
A. Adami, M. Mortazavi, M. Nosratollahi (2015)
Multidisciplinary Design Optimization of a Deorbit Maneuver Considering Propulsion, TPS, and TrajectoryInternational Journal of Computer Applications, 116
Sungyong An, Hayoung Lim, Sejin Kwon (2007)
Hydrogen peroxide thruster module for microsatellites with platinum supported by alumina as catalyst, 5
Koopmansand Shrimpton, G. Roberts (2011)
Validation and Design Optimization for a Hydrogen Peroxide Thruster
M. Balesdent, N. Bérend, P. Dépincé, A. Chriette (2012)
A survey of multidisciplinary design optimization methods in launch vehicle designStructural and Multidisciplinary Optimization, 45
L. Pirault‐Roy, C. Kappenstein, M. Guerin, R. Eloirdi, N. Pillet (2002)
Hydrogen Peroxide Decomposition on Various Supported Catalysts Effect of StabilizersJournal of Propulsion and Power, 18
Nobuo Tsujikado, Masatoshi Koshimae, R. Ishikawa, Kazuki Kitahara, A. Ishihara (2002)
AN APPLICATION OF COMMERCIAL GRADE HYDROGEN PEROXIDE FOR HYBRID/LIQUID ROCKET ENGINE (II)
A. Adami, M. Mortazavi, M. Nosratollahi (2015)
Multidisciplinary Design Optimization of Hydrogen Peroxide Monopropellant Propulsion System using GA and SQPInternational Journal of Computer Applications, 113
Y. Chan, H. Liu, K. Tseng, T. Kuo (2013)
Preliminary Development of a Hydrogen Peroxide ThrusterWorld Academy of Science, Engineering and Technology, International Journal of Mechanical, Aerospace, Industrial, Mechatronic and Manufacturing Engineering, 7
E. Wernimont (2006)
Monopropellant Hydrogen Peroxide Rocket Systems: Optimum for Small Scale
Purpose – For complex engineering problems, multidisciplinary design optimization (MDO) techniques use some disciplines that need to be run several times in different modules. In addition, mathematical modeling of a discipline can be improved for each module. The purpose of this paper is to show that multi-modular design optimization (MMO) improves the design performances in comparison with MDO technique for complex systems. Design/methodology/approach – MDO framework and MMO framework are developed to optimum design of a complex system. The nonlinear equality and inequality constrains are considered. The system optimizers included Genetic Algorithm and Sequential Quadratic Programming. Findings – As shown, fewer design variables (optimization variables) are needed at the system level for MMO. Unshared variables are optimized in the related module when shared variables are optimized at the system level. The results of this research show that MMO has lower elapsed times (14 percent) with lower F -count (16 percent). Practical implications – The monopropellant propulsion upper-stage is selected as a case study. In this paper, the efficient model of the monopropellant propulsion system is proposed. According to the results, the proposed model has acceptable accuracy in mass model (error < 2 percent), performance estimation (error < 6 percent) and geometry estimation (error < 10 percent). Originality/value – The monopropellant propulsion system is broken down into the three important modules including propellant tank (tank and propellant), pressurized feeding (tank and gas) and thruster (catalyst, nozzle and catalysts bed) when chemical decomposition, aerothermodynamics, mass and configuration, catalyst and structure have been considered as the disciplines. The both MMO and MDO frameworks are developed for the monopropellant propulsion system.
International Journal of Intelligent Unmanned Systems – Emerald Publishing
Published: May 11, 2015
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