Research on Numerical Simulation of Support Interference for Dynamic Derivatives at Hypersonic Flight Speeds

Abstract:

The research on dynamic derivative under the dynamic unsteady condition is one of the most difficult aspects of the aircraft development process. For the special experiment of dynamic derivatives, no numerical simulation of support interference has yet been systematically studied. The numerical simulation of support interference for identification of dynamic derivatives with 7o blunted cone under the hypersonic condition was done in this paper. The 2-order Roe scheme and the dual-time-step method based on LU-SGS were respectively applied to discrete of the spatial and time derivative of the unsteady flow. A least square method based on the Etkin unsteady aerodynamic model was used for identification of dynamic derivatives. Hypersonic missile module was adopted as a verification example, and the numerical calculation results are consistent with the experimental results. For two different sting support forms with 7o blunted cone, the impact of sting support interference on dynamic derivatives was studied. Results show the moment coefficients of two support forms under static conditions are essentially the same, while there is a big difference in the pitch damping derivatives under dynamic conditions. The support interference of nonlinear aerodynamic loads resulted from the shock wave induced separation and other unsteady flow structures under dynamic conditions is far more complicated than that under static conditions, and the correction law of support interference under static conditions cannot be applied directly to the unsteady dynamic situations.

• Periodical: Advanced Materials Research (Volume 1016)
• Pages: 495-500
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.1016.495
• Online since: August 2014
• Authors: Xu Liu*, Wei Liu, Yun Fei Zhao
• Keywords: CFD, Dynamic Derivative, Hypersonic, Least Square (LS), Support Interference

References

[1] Wei Liu, Hai-Yang Zhao. Investigation of the dynamic stability of a capsule in multidisciplinary methods [J]. Proc IMechE Part G: J Aerospace Engineering, 2013, 227(7): 1161-1172.

[2] Roe P L. Aproximate Rieman Solvers, parameter Vector and Diference Schemes [J]. Journal of Computation Physics, 1981, 43: 357-372.

[3] Jameson A. Time Dependent Calculations Using Multigrid with Application to Unsteady Flows past Airfoils and Wings [R]. AIAA 91-1596, (1991).

DOI: 10.2514/6.1991-1596

[4] Liu X, Zhao Y, Wang D, et al. Investigation of Dynamic Characteristics of Hypersonic Integrative Vehicle with Internal and External Flow [J]. Journal of Ballistics, 2013, 25(3): 38-43.

[5] Uselton BL, Cyran FB. Sting interference effects as determined by measurements of dynamic stability derivatives, surface pressure, and base pressure for Mach numbers 2 through 8 [R] . DTIC Document, (1980).

[6] East R A, Hutt G R. Comparison of Predication and Experimental Dara for Hypersonic Pitching Motion Stability [J]. Spacecraft, Vol. 25, No. 3, May-June, (1988).