Research Progress and Prospects for Vehicle Dynamic Stability Parameters

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Dynamic stability parameters (dynamic derivatives) are important indicators for the control system design, orbit design and longitudinal and horizontal dynamic stability analysis of aircrafts. Methods that evaluate the quality and dynamics of an aircraft typically include flight experiment, wind tunnel testing and theoretical calculation, with one of the most important part of them being the obtainment of dynamic derivatives. Project estimation method derivative action is not considered suitable for boundary layer transition, flow separation and re-attached and the complex situation leeward area vortex small angle of attack linear range. Frequency domain is a dynamic non-scheduled periodic invariant system to get moving derivative calculation method, but the accuracy of the unsteady flow is much lower than the time-domain calculations. Currently, unsteady CFD approach represents a time-domain nonlinear aerodynamic characteristics predicted the most advanced level. Derivative prediction efficiency and adaptability under conditions of high angle of attack of the development trend of nonlinear dynamic derivatives were analyzed. As a global trend, obtaining dynamic parameters through numerical calculation is becoming a prevailing approach to dynamic parameter research.

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95-100

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January 2015

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© 2015 Trans Tech Publications Ltd. All Rights Reserved

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[1] YANG Xiaoliang, LIU Wei, WU Tianzuo, et al. Coupling mechanism analysis of a slender delta wing in combined free-roll and free-sideslip motion [J]. Acta Aerodynamica Sinica, 2014, 32 (1): 1-7. (in China).

Google Scholar

[2] Boyd T. ONE HUNDRED YEARS OF GH BRYAN'S STABILITY IN AVIATION [J]. Journal of Aeronautical History Paper No, 2011, 4.

Google Scholar

[3] NIELSEN J. Missile aerodynamics [J]. (1988).

Google Scholar

[4] Thbodohsbn T. General theory of aerodynamic instability and the mechanism of flutter [J]. (1935).

Google Scholar

[5] Albano E, Rodden WP. A doublet-lattice method for calculating lift distributions on oscillating surfaces in subsonic flows [J]. AIAA journal, 1969, 7 (2): 279-85.

DOI: 10.2514/3.5086

Google Scholar

[6] Yang Yongnian, Zhao Lingcheng. Unsteady aerodynamic and flutter [M]. Xi'An: Northwestern polytechnical university press. 1982. (in China).

Google Scholar

[7] Robinson BA, Yang HT, Batina JT. Aeroelastic analysis of wings using the Euler equations with a deforming mesh [J]. Journal of Aircraft, 1991, 28 (11): 781-8.

DOI: 10.2514/3.46096

Google Scholar

[8] Melville RB, Morton SA, Rizzetta DP. Implementation of a fully-implicit, aeroelastic Navier-Stokes solver [J]. AIAA Paper-97-2039, (1997).

DOI: 10.2514/6.1997-2039

Google Scholar

[9] Zhang Xijin. Plane Design Manual: aerodynamic design [M]. Aviation Industry Press, 2002. (in China).

Google Scholar

[10] Xiong Haiquan, Liu Chao, Zheng Benwu. Aircraft flight dynamics [M]. BeiJing: Aviation industry press, 1990. (in China).

Google Scholar

[11] Hu Zhaofeng. Flight dynamics: Stability and maneuverability of plane [M]. National Defence Industry Press, 1985. (in China).

Google Scholar

[12] Roskam J. Airplane design part VI: preliminary calculation of aerodynamic, thrust and power characteristics [J]. Roskam Aviation and Engineering Corporation, Kansas, (1990).

Google Scholar

[13] Hemsch MJ, Hong Jinsen, Yang Qide. Tactical missile aerodynamics [M]. BeiJing: Aerospace press. (1999).

Google Scholar

[14] TONG BG, Hui W. Unsteady embedded Newton-Busemann flow theory [J]. Journal of Spacecraft and Rockets, 1986, 23 129-35.

DOI: 10.2514/3.25798

Google Scholar

[15] Vukelich S, Williams J: AFFDL-TR-79-3032. April, (1979).

Google Scholar

[16] Roskam J. Airplane design [M]. DARcorporation, (1985).

Google Scholar

[17] Schummer J. A Conceptual Approach [J]. HYLE-International Journal for Philosophy of Chemistry, 1998, 4 (2): 129-62.

Google Scholar

[18] East RA, Hutt GR. Comparison of predictions and experimental data for hypersonic pitching motion stability [J]. Journal of Spacecraft and Rockets, 1988, 25 (3): 225-33.

DOI: 10.2514/3.25975

Google Scholar

[19] Clark WS, Hall KC. A time-linearized Navier-Stokes analysis of stall flutter [J]. Journal of Turbomachinery, 2000, 122 (3): 467-76.

DOI: 10.1115/1.1303073

Google Scholar

[20] Van Der Weide E, Gopinath A, Jameson A. Turbomachinery applications with the time spectral method [J]. AIAA Paper, 2005, 4905 (2005).

DOI: 10.2514/6.2005-4905

Google Scholar

[21] Dufour G, Sicot F, Puigt G, et al. Contrasting the harmonic balance and linearized methods for oscillating-flap simulations [J]. AIAA journal, 2010, 48 (4): 788-97.

DOI: 10.2514/1.43401

Google Scholar

[22] Blanc F, Roux F-X, Jouhaud J-C. Harmonic-Balance-Based Code-Coupling Algorithm for Aeroelastic Systems Subjected to Forced Excitation [J]. AIAA journal, 2010, 48 (11): 2472-81.

DOI: 10.2514/1.45444

Google Scholar

[23] Pechloff AN, Laschka B. Small disturbance Navier-Stokes method: Efficient tool for predicting unsteady air loads [J]. Journal of aircraft, 2006, 43 (1): 17-29.

DOI: 10.2514/1.14350

Google Scholar

[24] Hall KC, Thomas JP, Clark WS. Computation of unsteady nonlinear flows in cascades using a harmonic balance technique [J]. AIAA journal, 2002, 40 (5): 879-86.

DOI: 10.2514/3.15137

Google Scholar

[25] Thomas JP, Dowell EH, Hall KC. Nonlinear inviscid aerodynamic effects on transonic divergence, flutter, and limit-cycle oscillations [J]. AIAA journal, 2002, 40 (4): 638-46.

DOI: 10.2514/3.15109

Google Scholar

[26] Da Ronch A. On the calculation of dynamic derivatives using computational fluid dynamics [D]; University of Liverpool, (2012).

Google Scholar