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Control Effectiveness of Wing with Elevon of a Typical Reusable Launch Vehicle

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Proceedings of SECON 2020 (SECON 2020)

Part of the book series: Lecture Notes in Civil Engineering ((LNCE,volume 97))

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Abstract

Modern aircraft structures uses more lightweight materials such as composites for their design. This makes the aeroelastic study an extremely important aspect of aircraft design. By having more light weight control surfaces, the control effectiveness study becomes vital in today’s scenario. Control effectiveness is the ability of a control surface such as an aileron or a rudder to produce aerodynamic forces and moments to change the airplane orientation and manoeuvre it along the intended flight path. This paper presents the static aeroelastic analysis of a typical reusable launch vehicle focusing on control effectiveness of elevon. A Reusable Launch Vehicle (RLV) is the space analogy of an aircraft. Ideally it takes off vertically on the back of a dispensable rocket and then glides back down like an aircraft. MSC PATRAN and MSC NASTRAN were the software’s used for Finite Element Modeling and Analysis. The main aim of the analysis is to compute the control effectiveness of launch vehicle along its trajectory to determine whether it is efficient to control the vehicle. The objectives of this work are, to study the control surface effectiveness of elevon by carrying out static aeroelastic analysis using NASTRAN inbuilt aerodynamics, for a typical Reusable Launch Vehicle (RLV).

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Abbreviations

Xcp:

Center of Pressure (m)

Xcg:

Center of Mass (m)

Q:

Dynamic pressure (Pa)

Qdiv:

Divergence dynamic pressure (Pa)

E:

Young’s Modulus (N/m2)

I:

Area moment of inertia (m4)

References

  1. Alley Jr VL, Harper Gerringer A (1967) An analysis of aeroelastic divergence in unguided launch vehicles. NASA Technical Note, NASA TN D–3281

    Google Scholar 

  2. Thompson WT, Dahleh MD (2011) Theory of vibrations with applications. University of California, vol 5

    Google Scholar 

  3. Petyt M (2003) Introduction to finite element vibration analysis. Institute of Sound and Vibration Research, vol 7

    Google Scholar 

  4. Bisplinghoff RL, Ashley H, Halfman RL (1996) Aeroelasticity. Dover Publications

    Google Scholar 

  5. Praveen R, Surendar E, Shyam Kumar K (2018) Design, static structural and modal analysis of aircraft wing NACA 4412 using ANSYS workbench 14.5. Int J Eng Sci Invent (IJESI), 61–71

    Google Scholar 

  6. Katon M, Rahman NA, Manap N (2017) Theoretical and finite element method of static structural analysis at wing segment. ARPN J Eng Appl Sci, 4491–4493

    Google Scholar 

  7. Fung YC (2003) An introduction to the theory of aeroelasticity. University of California, vol. 3

    Google Scholar 

  8. Sruthi K, Lakshmana Kishore T, Komaleswara Rao M (2017) Design and structural analysis of an aircraft wing by using aluminium silicon carbide composite materials. IJEDR 5, 949–959

    Google Scholar 

  9. Lee I, Miura H, Chargin MK (1992) Static aeroelastic analysis for generic configuration. J Aircraft

    Google Scholar 

  10. Xie C, Wang L, Yang C, Li Y (2013) Static aeroelastic analysis of very flexible wings based on non-planar vortex lattice method. Chin J Aeronaut

    Google Scholar 

  11. Lina Q, Zhou Z, Chi Z (2019) Static aeroelastic characteristics of grid structure wing. IEEE Aerosp Conf

    Google Scholar 

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Acknowledgements

The authors would like to acknowledge, the scientists from VSSC, ISRO and ADA who have initially guided us in successfully carrying out the static aeroelastic analysis and divergence analysis for RLV. We would also like to acknowledge MSC NASTRAN technical support people for guiding us in the software side. We would like to express our sincere gratitude to the above without their initial support this paper wouldn’t have seen the light.

Author information

Authors and Affiliations

  1. Department of Civil Engineering, Mar Baselios Institute of Technology and Science, Nellimattom, India

    Nyle Nazar & Manju George

  2. STR, VSSC, ISRO, Thiruvananthapuram, India

    P. Ashok Gandhi & S. Rajendran

Authors
  1. Nyle Nazar
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  2. P. Ashok Gandhi
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  3. S. Rajendran
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  4. Manju George
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Corresponding author

Correspondence to Nyle Nazar .

Editor information

Editors and Affiliations

  1. Department of Civil Engineering, Indian Institute of Technology Guwahati, Guwahati, Assam, India

    Kaustubh Dasgupta

  2. Department of Civil Engineering, Indian Institute of Technology Palakkad, Palakkad, Kerala, India

    T. K. Sudheesh

  3. Department of Civil Engineering, NSS College of Engineering, Akathethara, Kerala, India

    K. I. Praseeda

  4. Department of Civil Engineering, Federal Institute of Science and Technology (FISAT), Angamaly, Kerala, India

    G. Unni Kartha

  5. Department of Civil Engineering, Federal Institute of Science and Technology (FISAT), Angamaly, Kerala, India

    P. E. Kavitha

  6. Department of Civil Engineering, Federal Institute of Science and Technology (FISAT), Angamaly, Kerala, India

    S. Jawahar Saud

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Nazar, N., Gandhi, P.A., Rajendran, S., George, M. (2021). Control Effectiveness of Wing with Elevon of a Typical Reusable Launch Vehicle. In: Dasgupta, K., Sudheesh, T.K., Praseeda, K.I., Unni Kartha, G., Kavitha, P.E., Jawahar Saud, S. (eds) Proceedings of SECON 2020. SECON 2020. Lecture Notes in Civil Engineering, vol 97. Springer, Cham. https://doi.org/10.1007/978-3-030-55115-5_21

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  • DOI: https://doi.org/10.1007/978-3-030-55115-5_21

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  • Publisher Name: Springer, Cham

  • Print ISBN: 978-3-030-55114-8

  • Online ISBN: 978-3-030-55115-5

  • eBook Packages: EngineeringEngineering (R0)

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