طراحی سامانة پیشرانش تک‌مؤلفه‌ای به کمک روش بهینه‌سازی طراحی چندموضوعی و روش طراحی ترتیبی و مقایسة نتایج

نویسندگان

1 دانشگاه صنعتی مالک اشتر

2 مجتمع دانشگاهی هوافضا،دانشگاه صنعتی مالک اشتر،تهران،ایران

3 مدیر مرکز ماهواره و فضاپیما، مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر

چکیده

سامانة پیشرانش هیدرازینی از پرکاربردترین سامانه­های پیشرانش تک‌مؤلفه­ای است. این سامانه هزینة پایین و جرم کمی دارد و به دلیل ضربة مخصوص بالا و واکنش­پذیری سریعی که از خود نشان می­دهد در کنترل ماهواره­ها و ماهواره­برها استفاده ­می­شود. در پژوهش حاضر به طراحی بهینة یک سامانة پیشرانش تک‌مؤلفه‌ای هیدرازینی با اهداف به حداقل رساندن جرم و حداکثر کردن ضربه کل در چارچوب روش بهینه‌سازی­ طراحی چندموضوعی و روش ترتیبی پرداخته شده است. ضمن اینکه اصول روش­ طراحی چندموضوعی و ترتیبی در این مقاله بیان شده است؛ سعی شده تا تأثیر المان‌های مختلف را روی اهداف طراحی بررسی کرده و مقدار بهینه به‌دست آمده در هر کدام از ساختارهای طراحی را از جوانب مختلف مقایسه کنیم. شایان ذکر است روند طراحی به دو صورت تک هدفی و دو هدفی صورت گرفته است؛ که از این زاویه نیز روش طراحی بهینه چند موضوعی با روش طراحی ترتیبی برای سامانة پیشرانش تک­‌مؤلفه­ای هیدرازینی مقایسه می‌شود.

کلیدواژه‌ها


عنوان مقاله [English]

Monopropellant Propulsion System Design using Multidisciplinary Design Optimization, Sequential Design Method, and Comparing Results

نویسندگان [English]

  • Hojat Taei 1
  • Mansour Hozuri 2
  • Amirhossain Adami 3
1 MUT
2 Department of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran.
3 Satellite & LV center, Aerospace Department, Malek Ashtar University of Technology
چکیده [English]

The hydrazine propulsion system is one of the most widely used monopropellant
propulsion systems. This low-cost and low mass system is used for the attitude control of
satellites due to its high specificity and rapid response.For this purpose, in the present
study, an optimal design of a hydrazine monopropellant propulsion system with the aim of
minimization of total mass and maximization of total impulse in the framework of
multidisciplinary design optimization and sequential design method is considered. In
addition, the principles of multidisciplinary and sequential design are described in this
paper. It has been tried to examine the impact of different elements on design goals and
compare the optimal value obtained in each of the design structures from different
aspects. It should be noted that the design process is accomplished in two ways, i.e.
single-objective and multi-objective, and the optimal multidisciplinary design method is
compared with the sequential design method for the hydrazine monopropellant propulsion
system.

کلیدواژه‌ها [English]

  • Hydrazine monopropellant propulsion system
  • Multidisciplinary design optimization
  • Sequential design

[1]   Ronald. W. H., Larson, W. J. and  Gary, N. H., eds. Space Propulsion Analysis and Design, 1rd Edition, McGraw-Hill, 1995.

[2]   Sutton, G.P. and Biblarz, O., Rocket Propulsion Elements, 7rd Edition, John Wiley & Sons, 2017.

[3]   Huzel, D.K., Huang, D.H. and Arbit, H., Modern Engineering for Design of Liquid-Propellant Rocket Engines, 1rd Edition, American Institute of Aeronautics and Astronautics, 1992.

[4]   Steve, H., “Launch Vehicle and Spacecraft System Design Using the Pistonless Pump,” Space 2004Conference andExhibit, American Institute ofAeronautics and Astronautics, Vol. 7004,  2004.

[5]   Erichsen, P., “A Quick-Look Analysis Tool for the Impulse Performance of Spacecraft Propulsion Systems,” Presented at the 2nd European Conference for Aerospace Sciences (EUCASS), Brussels, Belgium, 2007.

[6]   Juergen, M., “Thruster Options for Microspacecraft - A

[7]   Review and Evaluation of Existing Hardware and Emerging Technologies,” Presented at the 33rd Joint Propulsion Conference and Exhibit, Seattle, WA, 1997.

[8]   Wiley, S., Dommer, K. and Mosher, L. “Design and Development of the Messenger Propulsion System,” American Institute of Aeronautics and Astronautics/ Society of Automotive Engineers/ American Society of Mechanical Engineers Joint Propulsion Conference, Huntsville, 2003.

[9]   Adami, A.H., Mortazavi, M. and Mehran Nosratollahi. “Multidisciplinary design optimization of hydrogen peroxide monopropellant propulsion system using GA and SQP.’’ International Journal of Computer Applications, Vol.113, No. 9, 2015, pp. 14-21.

[10]  Fazeley, H. R., Taei, H., Naseh, H., & Mirshams, M. “A multi-objective, multidisciplinary design optimization methodology for the conceptual design of a spacecraft bi-propellant propulsion system.’’ Structural and Multidisciplinary Optimization, Vol.53, No. 1, 2016, pp.145-160.

[11]  Fazeley, H. R, Naseh, H., Mirshams, M. Novinzade, A. “Comprehensive pattern design of a spacecraft bi-propellant propulsion low fuel.’’ Journal of Space science and technology, Vol.7, No. 3, 2014, pp.9-21. (in Persian).

[12]  Brown, Nichols F., and John R. Olds. “Evaluation of multidisciplinary optimization techniques applied to a reusable launch vehicle.” Journal of Spacecraft and Rockets, Vol.43, No. 6, 2006, pp.1289-1300.

[13] Jamali, Sajjad, Seyedhosein Poortakdoost, and Seyed javad Mousavi. "Multidisciplinary and multuobjective  optimization of a flying projective using evolutionary algorithm (NSGA-II).”  Journal of Aviation,  Vol.16, No. 1, 2014, pp.17-32. (in Persian).

[14] Balesdent, Mathieu, Bérend, N., Dépincé, P. and Chriette, A., “A survey of multidisciplinary design optimization methods in launch vehicle design.” Structural and Multidisciplinary Optimization, Vol.45, No. 5, 2012, pp.619-642.

[15]  Adami, Amirhossein, Mortazavi, M., Nosratollahi, M., Taheri, M. and Sajadi, J., “Multidisciplinary Design Optimization and Analysis of Hydrazine Monopropellant Propulsion System.” International Journal of Aerospace Engineering , Vol.88, No. 6, 2015, pp.45-51.

[16] McRight, Patrick, Popp, C., Pierce, C., Turpin, A., Urbanchock, W. and Wilson, M. , “Confidence Testing of Shell-405 and S-405 Catalysts in a Monopropellant Hydrazine Thruster.” AIAA paper 3952, 2005.

[17]  Nosratollahi, Mehran, Amirhossein Adami, “Conceptual multidisciplinary design optimization of monopropellant propulsion system for a Small Satellite.’’ Journal of Space science and technology, Vol.3, No. 4, 2010, pp.11-23. (in Persian).

[18] Treybal, E. R., Mass Transfer Operations, 3rd edition, McGraw- Hill, 1981.

[19]  Qhanbaripakdehi, Shahram, Mahdi Mozaffari, Ali Hashemi, “Modeling of catalytic propulsion system in incomplete combustion mode.’’ Journal  of Fuel and Combustion, Vol.2, No. 2, 2009, pp.56-67. (in Persian).

[20]  Schmidt, Michael W., and Mark S. Gordon. "The decomposition of hydrazine in the gas phase and over an iridium catalyst." Zeitschrift für Physikalische Chemie, Vol. 227, No.9-11, 2013, pp.1301-1336.