Abstract: When considering the practical engineering application of a waverider, the on-design and off-design aerodynamic characteristics of the design conditions, especially the lift-to-drag ratio and the stability, deserve attention. According to recently studies, the planform and rear sight shape of a waverider are closely related to the above aerodynamic performance. Thus, the planform leading-edge profile curve used to design the planform shape of a vehicle is applied to designing an osculating cone waverider. Two key parameters concerned in planform and rear sight shape, namely the plan view sweep angle of the leading edge and the dihedral angle of the underside are introduced to the waverider design process. Each parameter is inserted in the control curve equation. Especially, a parameterization scheme is put forward for the free adjustment of the sweep angle along the leading edge. Finally, three examples are generated for verification and investigation. After the verification process based on the inviscid flow field of one case, the influences of the sweep and dihedral angles on the lift-to-drag ratio and the lateral static stability are evaluated, and meaningful results are obtained. Based on these results, we can conclude that, considering the maximum lift-to-drag ratio, the sweep angle plays a role on the lift-to-drag ratio only at subsonic and trans/supersonic speed as a negligible effect is observed at hypersonic speeds, whereas the dihedral angle is seem to produce a relevant difference at hypersonic speeds. Considering the lateral static stability, the dihedral angles have more influence on the waverider than the sweep angles.

后掠角及反角可控的吻切锥乘波体设计方法

[1]Adamczak DW, Bolender MA, 2015. The flight dynamics of the HIFiRE Flight 6 research vehicle. Proceedings of AIAA Atmospheric Flight Mechanics Conference.

[2]Ding F, Shen CB, Liu J, et al., 2015a. Influence of surface pressure distribution of basic flow field on shape and performance of waverider. Acta Astronautica, 108:62-78.

[3]Ding F, Liu J, Shen CB, et al., 2015b. Novel approach for design of a waverider vehicle generated from axisymmetric supersonic flows past a pointed von Karman ogive. Aerospace Science and Technology, 42:297-308.

[4]Ding F, Liu J, Shen CB, et al., 2015c. Novel inlet-airframe integration methodology for hypersonic waverider vehicles. Acta Astronautica, 111:178-197.

[5]Ding F, Liu J, Shen CB, et al., 2015d. Simplified osculating cone method for design of a waverider. Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition.

[6]Ding F, Liu J, Shen CB, et al., 2017. An overview of research on waverider design methodology. Acta Astronautica, 140:190-205.

[7]Ding F, Jun L, Shen CB, et al., 2018. An overview of waverider design concept in airframe/inlet integration methodology for air-breathing hypersonic vehicles. Acta Astronautica, 152:639-656.

[8]Etkin B, Reid LD, 1996. Dynamics of Flight: Performance, Stability and Control, 3rd Edition. John Wiley & Sons, New York, the USA, p.81-86.

[9]Favaloro N, Rispoli A, Vecchione L, et al., 2015. Design analysis of the high-speed experimental flight test vehicle HEXAFLY-international. Proceedings of the 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.

[10]He X, Rasmussen ML, Cox RA, 1993. Waveriders with finlets. Proceedings of the 11th Applied Aerodynamics Conference.

[11]He XZ, Le JL, Wu YC, 2009. Design of a curved cone derived waverider forebody. Proceedings of the 16th AIAA/ DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference.

[12]Hirschel EH, Weiland C, 2009. Selected Aerothermodynamic Design Problems of Hypersonic Flight Vehicles. Springer, Berlin Heidelberg, Germany, p.103.

[13]Jones JG, Moore KC, Pike J, et al., 1968. A method for designing lifting configurations for high supersonic speeds, using axisymmetric flow fields. Ingenieur-Archiv, 37(1):56-72.

[14]Kontogiannis K, Sóbester A, Taylor N, 2015a. On the conceptual design of waverider forebody geometries. Proceedings of the 53rd AIAA Aerospace Sciences Meeting.

[15]Kontogiannis K, Cerminara A, Taylor NJ, et al., 2015b. Parametric geometry models for hypersonic aircraft components: blunt leading edges. Proceedings of the 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.

[16]Kontogiannis K, Sóbester A, Taylor N, 2017. Efficient parameterization of waverider geometries. Journal of Aircraft, 54(3):890-901.

[17]Kuchemann D, 1978. The Aerodynamic Design of Aircraft. Pergamon Press, Oxford, the UK, p.448-451.

[18]Liao L, Yan L, Huang W, et al., 2018. Mode transition process in a typical strut-based scramjet combustor based on a parametric study. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 19(6):431-451.

[19]Liu CZ, Duan YH, Cai JS, et al., 2014. Applications of multi-block CST method for quasi-waverider design. Proceedings of the 52nd Aerospace Sciences Meeting.

[20]Liu CZ, Duan YH, Cai JS, et al., 2016. Application of the 3D multi-block CST method to hypersonic aircraft optimization. Aerospace Science and Technology, 50:295-303.

[21]Liu CZ, Bai P, Chen BY, 2017. Design and property advantages analysis of double swept waverider. Acta Aeronautica et Astronautica Sinica, 38(6):120808 (in Chinese).

[22]Liu Z, Liu J, Ding F, et al., 2017a. Effect of thermochemical non-equilibrium on the aerodynamics of an osculating-cone waverider under different angles of attack. Acta Astronautica, 139:288-295.

[23]Liu Z, Liu J, Ding F, et al., 2017b. Novel methodology for wide-ranged multistage morphing waverider based on conical theory. Acta Astronautica, 140:362-369.

[24]Meng YS, Yan L, Huang W, et al., 2019. Structural design and analysis of a composite wing with high aspect ratio. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 20(10):781-793.

[25]Nonweiler TRF, 1959. Aerodynamic problems of manned space vehicles. The Aeronautical Journal, 63(585):521-528.

[26]Pezzella G, Marini M, Cicala M, et al., 2014. Aerodynamic characterization of HEXAFLY scramjet propelled hypersonic vehicle. Proceedings of the 32nd AIAA Applied Aerodynamics Conference.

[27]Rasmussen ML, 1997. Effects of anhedral and finlets on lateral stability of hypersonic waveriders. Proceedings of the 35th Aerospace Sciences Meeting and Exhibit.

[28]Rodi PE, 2011. Geometrical relationships for osculating cones and osculating flowfield waveriders. Proceedings of the 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.

[29]Rodi PE, 2015. Integration of optimized leading edge geometries onto waverider configurations. Proceedings of the 53rd AIAA Aerospace Sciences Meeting.

[30]Rodriguez DL, 2004. Multidisciplinary optimization of a supersonic inlet using a Cartesian CFD method. Proceedings of the 10th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference.

[31]Sobieczky H, Dougherty FC, Jones K, 1990. Hypersonic waverider design from given shock waves. Proceedings of the 1st International Waverider Symposium.

[32]Strohmeyer D, 1998. Lateral stability derivatives for osculating cones waveriders in sub- and transonic flow. Proceedings of the 8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.

[33]Strohmeyer D, Eggers T, Heinze W, et al., 1996. Planform effects on the aerodynamics of waveriders for TSTO missions. Proceedings of Space Plane and Hypersonic Systems and Technology Conference.

[34]Tian C, Li N, Gong GH, et al., 2013. A parameterized geometry design method for inward turning inlet compatible waverider. Chinese Journal of Aeronautics, 26(5):1135-1146.

[35]Viviani A, Pezzella G, 2015. Aerodynamic and Aerothermodynamic Analysis of Space Mission Vehicles. Springer, Switzerland, p.87-91.

[36]Walker SH, Sherk J, Shell D, et al., 2008. The DARPA/AF falcon program: the hypersonic technology vehicle #2 (HTV-2) flight demonstration phase. Proceedings of the 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.

[37]Wang P, Shen CB, 2019. Characteristics of mixing enhancement achieved using a pulsed plasma synthetic jet in a supersonic flow. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 20(9):701-713.

[38]Wen X, Liu J, Li J, et al., 2019. Design and numerical simulation of a clamshell-shaped inlet cover for air-breathing hypersonic vehicles. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 20(5):347-357.

[39]Wood RM, Bauer SXS, 2001. Flying wings/flying fuselages. Proceedings of the 39th Aerospace Sciences Meeting and Exhibit.

[40]Zhang TT, Wang ZG, Huang W, et al., 2019. The overall layout of rocket-based combined-cycle engines: a review. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 20(3):163-183.

[41]Zhang WH, Liu J, Ding F, et al., 2019. Novel integration methodology for an inward turning waverider forebody/ inlet. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 20(12):918-926.