Abstract
The problem of aerodynamic configuration design optimization is a multidisciplinary design optimization (MDO) problem, and recently the MDO method is widely adopted in the field of hypersonic vehicle configuration design. From the aerodynamic point of view, the aerodynamics, aerothermodynamics and trajectory are considered in this paper. Generally speaking, the aerodynamic characteristics, aerodynamic heating and trajectory are determined by the aerodynamic configuration and the design of flight trajectory. The design method considering these three disciplines is proposed. The parametric geometrical configurations are proposed, and the aerodynamic characteristics are predicted by the rapid and effective engineering method. The optimization of aerodynamic configuration considering the integration of aerodynamics, aerothermodynamics and trajectory is investigated based on the parametric geometrical configuration. Maximum lift-to-drag ratio, maximum range of the trajectory and minimum total heat load of the stagnation point are chosen as the three optimal goals. The detailed research indicates that the optimal configurations and trajectories with different weighting factors can be obtained by the optimization, and there are obvious differences between them. The optimal configuration and flight trajectory obtained by the optimization can be used as the feasible schemes in the future work.
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References
Tang W, Gui YW, Wang AL (2009) Proposal of thermal configuration optimization design for a maneuverable vehicle. J Astronaut 30:1803–1807 (in Chinese)
Wang ZG, Chen XQ, Luo WC et al (2006) Research on the theory and application of multidisciplinary design optimization of flight vehicles. National Defense Industry Press, Beijing (in Chinese)
Tang W, Zhang Y, Li WJ et al (2004) Aerodynamic design and optimization for vehicles with conic cross section. J Astronaut 25:429–433 (in Chinese)
Kulfan BM (2007) A universal parametric geometry representation method –“CST”. AIAA-2007-62
Feng Y, Tang W, Ren JX et al (2012) Parametric geometry representation method for hypersonic vehicle configuration. ACTA Aerodyn Sin 30:546–550 (in Chinese)
Chaudhary A, Nguyei V, Iran H et al (2001) Dynamics and stability and control characteristics of the X-37. AIAA-2001-4383
Wang ZG, Luo SB, Wu JJ (2005) Development of reusable launch vehicle technology. National University of Defence Technology Press, Changsha (in Chinese)
Jenkins DR, Landis T, Miller J (2003) American X-Vehicles: an inventory-X-1 to X-50. NASA history series, SP-2003-4531
Huang ZC (1995) Aerodynamics of hypersonic vehicle. National Defense Industry Press, Beijing (in Chinese)
Tang W, Gui YW, Fang F (2008) Aerodynamic configurations selection for lift reentry capsule. J Astronaut 29:84–88 (in Chinese)
Feng Y, Xiao GM, Tang W et al (2013) Aerodynamics configuration conceptual design for X-37 analog transporter. ACTA Aerodyn Sin 31:94–98 (in Chinese)
Feng Y, Tang W, Xiao GM et al (2013) Aerodynamics analysis for X-33 analog lifting body transporter. ACTA Aerodyn Sin 31:473–476 (in Chinese)
Tang W, Feng Y, Ning Y et al (2011) Aerodynamics configuration conceptual design for X-38 analog lifting body transporter. ACTA Aerodyn Sin 29:555–558 (in Chinese)
Tang W, Zeng L, Feng Y et al (2011) Aerodynamic configuration conceptional design for high maneuverable lift body with flaps. ACTA Aerodyn Sin 29:370–373 (in Chinese)
Xiao GM, Feng Y, Tang W et al (2012) Aerodynamics configuration conceptual design for ATLLAS-M6 analog transport aircraft. ACTA Aerodyn Sin 30:592–596 (in Chinese)
DeJarnette FR (1971) Calculation of inviscid surface streamlines and heat transfer on shuttle type configurations. Part 1. Description of basic method. NASA CR-111921
DeJarnette FR, Hamilton HH, Weilmuenster KJ (1985) A review of some approximate methods used in aerodynamic heating analyses. In: AIAA 20th thermophysics conference
Hamilton HH, Weilmuenster KJ (1985) Application of axisymmetric analogue for calculating heating in three-dimensional flows. AIAA-85-0245
Deharnette FR, Hamilton HH, Weilmuenster KJ (2008) New method for computing convective heating in stagnation region of hypersonic vehicles. In: 46th AIAA aerospace sciences meeting and exhibit
Yuan ZH, Qian XF (2001) Control flight mechanics and computer simulation. National Defense Industry Press, Beijing (in Chinese)
Gen M, Cheng RW (1999) Genetic algorithms and engineering optimization. Wiley, New York
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This work was supported by the National Natural Science Foundation of China (91216204).
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Feng, Y., Tang, W. & Gui, Y. Aerodynamic configuration optimization by the integration of aerodynamics, aerothermodynamics and trajectory for hypersonic vehicles. Chin. Sci. Bull. 59, 4608–4615 (2014). https://doi.org/10.1007/s11434-014-0534-9
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DOI: https://doi.org/10.1007/s11434-014-0534-9