Skip to main content

Advertisement

SpringerLink
Log in

A multi-objective, multidisciplinary design optimization methodology for the conceptual design of a spacecraft bi-propellant propulsion system

  • INDUSTRIAL APPLICATION
  • Published:
Structural and Multidisciplinary Optimization Aims and scope Submit manuscript

Abstract

Space propulsion systems play an increasingly important role in planning of space missions. The traditional method for design of space propulsion systems includes numerous design loops, which does not guarantee to reach the best optimal solution. Multidisciplinary Design Optimization (MDO) is an approach for the design of complex systems that considers a design environment with multiple disciplines. The aims of this study are to implement and compare Multidisciplinary Feasible and Collaborative Optimization architectures for the multi-Objective optimization of a bi-propellant space propulsion system design. Several disciplines such as thrust chamber, cooling, and structure were exploited in a proper combination. The main optimization objectives in the MDO frameworks were to minimize the total wet mass and maximize the total impulse by considering several constraints. Furthermore, Genetic Algorithm and Sequential Quadratic Programming are employed as the system-level and local-level optimizers. The presented design methodology provides an interesting decision making approach to select the best system parameters of space propulsion systems under conflicting goals.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5
Fig. 6
Fig. 7
Fig. 8
Fig. 9
Fig. 10
Fig. 11
Fig. 12
Fig. 13
Fig. 14

Similar content being viewed by others

References

  • Alexandrov NM, Hussaini MY (1997) Multidisciplinary Design Optimization: State of the Art. In, 1997. Proceedings in Applied Mathematics Series. Soc Ind Appl Math, p 388

  • Alexandrov NM, Lewis RM (2002) Analytical and computational aspects of collaborative optimization for multidisciplinary design. AIAA J 40:301–309. doi:10.2514/2.1646

    Article  Google Scholar 

  • Arias-Montano A, Coello Coello C, Mezura-Montes E (2012) Multi-objective evolutionary algorithms in aeronautical and aerospace engineering evolutionary computation. IEEE Trans on 16:662–694

    Google Scholar 

  • Balesdent M, Bérend N, Dépincé P, Chriette A (2012) A survey of multidisciplinary design optimization methods in launch vehicle design. Struct Multidiscip Optim 45:619–642. doi:10.1007/s00158-011-0701-4

    Article  MathSciNet  MATH  Google Scholar 

  • Chen H, Wen C-Y, Yang C-K (2012) Numerical simulation of air-he shock tube flow with equilibrium air model. AIAA J 50:1817–1825. doi:10.2514/1.J051129

    Article  Google Scholar 

  • Coats DE (2004) Assessment of thrust chamber performance. In: Liquid Rocket Thrust Chambers. Progress in Astronautics and Aeronautics. Am Inst Aeronaut Astronaut, pp 601–620. doi:10.2514/5.9781600866760.0601.0620

  • Grujicic M, Arakere G, Sellappan V, Ziegert JC, Kocer FY, Schmueser D (2009) Multi-Disciplinary Design Optimization of a Composite Car Door for Structural Performance, NVH, Crashworthiness, Durability and Manufacturability Multidiscipline Modeling in Materials and Structures 5:1–28 doi:citeulike-article-id:3904582

  • Hart T (1959) Design criteria and analyses for thinwalled pressurized vessels and interstage structures. Lockheed Missiles and Space Company

  • Hart C, Vlahopoulos N (2010) An integrated multidisciplinary particle swarm optimization approach to conceptual ship design. Struct Multidiscip Optim 41:481–494. doi:10.1007/s00158-009-0414-0

    Article  Google Scholar 

  • Hearn HC (1988) Thruster requirements and concerns for bipropellant blowdown systems. J Propuls Power 4:47–52. doi:10.2514/3.23030

    Article  Google Scholar 

  • Howell JC, Oberstone J, Stechman RC (1969) Design criteria for film cooling for small liquid-propellant rocket engines. J Spacecr Rocket 6:97–102. doi:10.2514/3.29545

    Article  Google Scholar 

  • Humble R, Henry GN, Larson WJ, United States. Department of Defense., United States. National Aeronautics and Space Administration. (1995) Space propulsion analysis and design. Space technology series, 1st edn. McGraw-Hill, New York

  • Huzel DK, Huang DH, Arbit H (1992) Modern engineering for design of liquid-propellant rocket engines. Progress in astronautics and aeronautics,, vol 147, Rev., updated, and enl. / edn. American Institute of Aeronautics and Astronautics, Washington, DC

  • Johnson L, Meyer M, Palaszewski B, Coote D, Goebel D, White H (2013) Development priorities for in-space propulsion technologies. Acta Astronaut 82:148–152. doi:10.1016/j.actaastro.2012.05.006

    Article  Google Scholar 

  • Konak A, Coit DW, Smith AE (2006) Multi-objective optimization using genetic algorithms: a tutorial. Reliab Eng Syst Saf 91:992–1007

    Article  Google Scholar 

  • Kroo I, Altus S, Braun R, Gage P, Sobieski I (1994) Multidisciplinary optimization methods for aircraft preliminary design. In: 5th Symposium on Multidisciplinary Analysis and Optimization. Multidisciplinary Analysis Optimization Conferences. American Institute of Aeronautics and Astronautics. doi:10.2514/6.1994-4325

  • Macdonald M, Badescu V (2014) The international handbook of space technology. Springer, Berlin

    Book  Google Scholar 

  • McBride BJ, Gordon S (1996) Computer program for calculation of complex chemical equilibrium compositions and applications II. User’s Manual and Program Description. National Aeronautics and Space Administration

  • Mirshams M, Naseh H, Fazeley HR (2014) Multi-objective multidisciplinary design of space launch system using holistic concurrent design. Aerosp Sci Technol 33:40–54. doi:10.1016/j.ast.2013.12.015

    Article  Google Scholar 

  • Orlando J, Meyers JF, Bruhn EF (1967) Analysis and design of missile structures. Tri-state Offset Company

  • Shine SR, Sunil Kumar S, Suresh BN (2012) A new generalised model for liquid film cooling in rocket combustion chambers. Int J Heat Mass Transf 55:5065–5075. doi:10.1016/j.ijheatmasstransfer.2012.05.006

    Article  Google Scholar 

  • Sobieszczanski-Sobieski J, Haftka RT (1997) Multidisciplinary aerospace design optimization: survey of recent developments. Struct Optim 14:1–23. doi:10.1007/BF01197554

    Article  Google Scholar 

  • Sutton GP (2006) Technology and Hardware. In: History of Liquid Propellant Rocket Engines. Library of Flight. American Institute of Aeronautics and Astronautics, pp 33–240. doi: 10.2514/5.9781600868870.0033.0240

  • Sutton GP, Biblarz O (2010) Rocket propulsion elements, 8th edn. Wiley, Hoboken

    Google Scholar 

  • Turner MJL (2009) Rocket and spacecraft propulsion : principles, practice and new developments. Springer-Praxis books in astronautical engineering, 3rd edn. Springer published in association with Praxis Publishing, Berlin; Chichester

  • United States. National Aeronautics and Space Administration (1976) Pressurization systems for liquid rockets. Nasa Sp-8112. NASA, Washington, Springfield, Va

  • Wagner WA, United States. National Aeronautics and Space Administration. (1974) Liquid rocket metal tanks and tank components. Nasa Sp-8088. National Aeronautics and Space Administration, Washington

Download references

Author information

Authors and Affiliations

  1. Space Research Lab, K.N. Toosi University of Technology, P.O. Box 16765-3381, Tehran, Islamic Republic of Iran

    H. R. Fazeley

  2. Faculty of Aerospace Engineering, Malek Ashtar University of Technology, P.O. Box 15875-1774, Tehran, Islamic Republic of Iran

    H. Taei

  3. Ministry of Science, Research and Technology, Aerospace Research Institute, P.O. Box 14665-834, Tehran, Islamic Republic of Iran

    H. Naseh

  4. Faculty of Aerospace Engineering, K.N. Toosi University of Technology, P.O. Box 16765-3381, Tehran, Islamic Republic of Iran

    M. Mirshams

Authors
  1. H. R. Fazeley
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. H. Taei
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. H. Naseh
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. M. Mirshams
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to H. R. Fazeley.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Fazeley, H.R., Taei, H., Naseh, H. et al. A multi-objective, multidisciplinary design optimization methodology for the conceptual design of a spacecraft bi-propellant propulsion system. Struct Multidisc Optim 53, 145–160 (2016). https://doi.org/10.1007/s00158-015-1304-2

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s00158-015-1304-2

Keywords

Search

Navigation