An Evolution of Hybrid Airship Vehicle (HAV) Envelope: Aerodynamics Analysis

Abstract:

HAV has a potential application as the new means to carry Ultra Heavy Payload cargo since it combines the buoyancy capabilities of Lighter-than-Air (LTA), and the aerodynamics of lifting body of Heavier-than-Air (HTA) for speed. Due to its potential, American Institute of Aeronautics and Astronautics (AIAA) has issued a Request for Proposal (RFP) regarding the Hybrid Airship Vehicle (HAV) as cargo transportation with several requirements. AIAA RFP required an envelope that can produce 60% of the lift from buoyancy and 40% of lift from aerodynamic. To satisfy the RFP requirements, this paper analyzed 4 different designs using Computational Fluid Dynamic (CFD) software. Design 4 was chosen as the final design because it meets all the requirements. It was found that at 5° Angle of Attack (AOA), the envelope produce highest aerodynamic lift over drag (L/D) ratio of 3.79. At higher AOA, flow separation occurs at the envelope tail section jeopardizing the aerodynamic characteristic of Design 4 envelope. The lift and drag force graphs were plotted at this AOA and it was found that the HAV envelope is capable of performing the tasks in the RFP.

• Periodical: Applied Mechanics and Materials (Volume 660)
• Pages: 498-502
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.660.498
• Online since: October 2014
• Authors: Muhammad Iyas Mahzan*, Sallehuddin Muhamad
• Keywords: Aerodynamics, Aerodynamics Lift, Altitude, Angle of Attack, Buoyant Lift, Envelope Evolution, Hybrid Airship Vehicle (HAV)

References

[1] Information on http: /www. faculty. fairfield. edu/jmac/sj/scientists/lana. htm.

[2] L. Winter, and G. Degner, Minutes of Epic Flight, first ed., Grosset & Dunlap, New York, 1933, pp.26-27.

[3] A. Werthmüller, The Hindenburg Disaster,  Rüfenacht Switzerland: Swiss Hydrogen Association, February 22, (2006).

[4] William W. Lace, The Hindenburg Disaster of 1937, Infobase Publishing NY, 2008. ISBN: 978-0-7910-9739-7.

[5] A. Akira, Fundamental Formulation of Airship Performance and Flight Dynamics, Institute of Space and Aeronautical Science, University of Tokyo Report No. 536, December (1975).

[6] S.P. Rajkumar, A Methodology for determination of Baseline Specifications of a Non-Rigid Airship, AIAA 2003-6830, AIAA's 3rd Annual Aviation Technology, Integration, and Operations (ATIO) Tech, 17-19 November 2003, Denver Colorado. Pp 1 – 9.

DOI: 10.2514/6.2003-6830

[7] M.I. Mahzan, and S. Muhamad, Cost Analysis of a Hybrid Airship Vehicle for Cargo Delivery, Applied Mechanics and Materials Vols. 465-466 (2014) pp.373-378.

DOI: 10.4028/www.scientific.net/amm.465-466.373

[8] K.S. Zhang, Z.H. Han, B.F. Song, Flight Performance Analysis of Hybrid Airship: Revised Analytical Formulation, Journal of Aircraft Vol. 47, No. 4, July-August (2010).

DOI: 10.2514/1.47294

[9] R.L. Ashford, B.B. Levitt, N.J. Mayer, J.M. Vocar, D.E. Woodward, 1981 LTA Technology Assessment: Past and Present, AIAA Paper 1981 -2348, (1981).

[10] AIAA Foundation Undergraduate Team Aircraft Design Competition RFP, 2010-(2011).

[11] M.I. Mahzan, D. Niccas, E. Ong, D. Scholtz, M. Chan, O. Camarillo, C. P Cervantes, S. Florez, AIAA RFP: Team Garuda Proposal, Aerospace Engineering Department, California State Polytechnic University Pomona, (2011).