Method for Improving the Natural Lateral-Directional Stability of Flying Wings
Publication: Journal of Aerospace Engineering
Volume 29, Issue 5
Abstract
Poor lateral-directional flight quality is a critical technical problem in flying wing aircraft design. This paper proposes an approach to achieve lateral-directional dynamic stability of flying wing aircraft. This approach is different from general methods such as installing a wingtip vertical stabilizer or depending on a stability augmentation system. Through directly including the judgment of aircraft dynamic stability into the aerodynamic configuration design, sufficient lateral-directional stability can be guaranteed without relying on other systems. A lateral-directional dynamic stability satisfaction judgment function was built based on MIL-F-8785C. The lateral-directional dynamic stability was improved using only the adjustment of the spanwise dihedral layout. To validate the feasibility of this design method, this study selected a flying wing aircraft with a high aspect ratio as the object. Two optimized configurations with different aerodynamic shape but similar stability characters were finally obtained. Each configuration achieved flight quality which surpassed Level 2 requirements of MIL-F-8785C in the entire airspeed range.
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References
Bolsunovsky, A. L., et al. (2011). “Flying wing problems and decisions.” Aircraft Des., 4(4), 193–219.
CATIA [Computer software]. Dassault Systemes Americas Corporation, Waltham, MA.
Clark, L. R., and Gerhold, C. H. (1999). “Inlet noise reduction by shielding for the blended-wing-body airplane.” AIAA, Reston, VA, 99–1937.
Davidson, R. W. (2004). “Flight control design and test of the joint unmanned combat air system (J-UCAS) X-45A.” AIAA, Reston, VA, 2004–6557.
Department of Defense. (1980). “Military specification flying qualities of piloted airplanes.”, Washington, DC.
Dobrenz, T. L., Spadoni, A., and Jorgensen, M. (2010). “Aviation archeology of the Horten 229 v3 aircraft.” AIAA, Reston, VA, 2010–9214.
Fang, Z. P., Chen, W. C., and Zhang, S. G. (2005). Flight dynamics of aerial vehicle, Beihang University Press, Beijing, 324–334 (in Chinese).
Guo, Y. P., Burley, C. L., and Thomas, R. H. (2014). “On noise assessment for blended wing body aircraft.” AIAA, Reston, VA, 2014–0365.
Liebeck, R. H. (2004). “Design of the blendedwing body subsonic transport.” J. Aircraft, 41(1), 10–25.
Mader, C. A., and Martins, J. R. R. A. (2013). “Stability-constrained aerodynamic shape optimization of flying wings.” J. Aircraft, 50(5), 1431–1449.
Melin, T. (2000). “A vortex lattice MATLAB implementation for linear aerodynamic wing applications.” M.S. thesis, Dept. of Aeronautical and Vehicle Engineer, Kungliga Tekniska Högskolan (KTH), Stockholm, Sweden.
Morris, S. J., and Kroo, I. (1990). “Aircraft design optimization with dynamic performance constraints.” J. Aircraft, 27(12), 1060–1067.
Nickel, K., and Wohlfahrt, M. (1996). Tailless aircraft in theory and practice, 2nd Ed., AIAA Education Series, Washington, DC, 110–120.
Richard, G. (2007). “Introducing taranis.” Aerosp. Int., 34(1), 30–31.
Risch, T., Cosentino, G., and Regan, C. D. (2009). “X-48B flight-test progress overview.” AIAA, Reston, VA, 2009–934.
Roskam, J. (1991). “Evolution of airplane stability and control: A designer’s viewpoint.” J. Guidance, 14(3), 481–491.
Snyder, M. P., and Weisshaar, T. A. (2013). “Flutter and directional stability of aircraft with wing-tip fins: Conflicts and compromises.” J. Aircraft, 50(2), 615–625.
Song, L., Yang, H., and Xie, J. F., et al. (2014). “Predicting stability derivatives of flying wing aircraft based on improved vortex lattice method.” J. Nanjing Univ. Aeronaut. Astronaut., 46(3), 457–463 (in Chinese).
Stenfelt, G., and Ringertz, U. (2010). “Yaw control of a tailless aircraft configuration.” J. Aircraft, 47(5), 1807–1811.
Stinton, D. (1996). “Rolling moment with sideslip and directional stability.” Flying qualities and flight testing of the airplane, 1st Ed., AIAA, OH, 486–487.
Taylor, B. R., and Yoo, S. Y. (2011). “Engine yaw augmentation for hybrid-wing-body aircraft via optimal control allocation techniques.” AIAA, Reston, VA, 2011–6253.
Whittenbury, J. R. (2011). “Configuration design development of the navy UCAS-D X-47B.” AIAA, Reston, VA, 2011–7041.
Wise, K. A. (2003). “X-45 program overview and flight test status.” AIAA, Reston, VA, 2003–6645.
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© 2016 American Society of Civil Engineers.
History
Received: Apr 26, 2014
Accepted: Feb 16, 2016
Published online: May 18, 2016
Published in print: Sep 1, 2016
Discussion open until: Oct 18, 2016
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