高超声速“准乘波体”构型优化设计方法
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摘要
乘波体构型以其非常高的气动效率,在高超声速飞行器设计中有着广阔的应用前景.基于各种基准流场的乘波体生成方法的发展,使得在飞行器设计过程中可以根据不同需求选择不同类型的乘波体构型.但是,乘波体构型一般难以直接满足容积率、配平、稳定性等基本的飞行器设计工程需求.针对这一情况,本文结合遗传算法和考虑强黏性干扰效应影响的气动力工程算法,提出了一种"准乘波体"构型优化设计方法.所谓"准乘波体",是指在外形生成过程中保留了乘波体的前缘线,然后对于不同的纵向截面,以相同的型线方程从前缘点出发生成下表面.型线方程以一组幂函数为基函数,通过改变基函数系数即可以不同工程需求为约束条件,借助遗传算法优化获得最优构型.分别获得了无约束条件、以容积率为约束和以在设计点自配平且纵向静稳定为约束的最优"准乘波体"构型.通过CFD数值模拟对相应构型的气动力特性进行了评估,结果表明:"准乘波体"构型流场能够保持较好的"乘波"特性且下表面压力分布较为均匀,可以获得比原乘波体更高的升阻比;通过引入不同约束条件获得的最优"准乘波体"构型,可以在一定范围内灵活地改变容积率,并且在优化过程中可以实现在设计点处满足配平和纵向静稳定要求.
The waverider configuration has a wide application prospect in the design of hypersonic vehicles due to its excellent aerodynamic efficiency.Various kinds of waveriders have been developed based on different basic flowfield,which can be chosen according to different design requirements.However,it's generally difficult for the waverider to directly satisfy the engineering requirements of volume efficiency,trim,stability,etc.To overcome these drawbacks,the paper proposes a new design method of hypersonic waverider configuration.In the generation process,the leading edge of the original waverider is kept unchanged.Then at different longitudinal cross section,the profile of the lower surface is determined by the same curve equation,started from the point at the leading edge and cut off at the base plane.The profile function is determined by the sum of a series of power law functions,whose coefficients can be changed according to different design requirements.Different waveriders are obtained according to different constraints.Results show that for this kind of configurations,good shock attachment near the leading edge can be achieved and the pressure distribution on the lower surface is uniform.What's more,the maximum lift-to-drag ratio is even higher than that of the original waverider.Different waveriders with excellent aerodynamic efficiency can also be generated by different constraints of volume efficiency and stability.
The waverider configuration has a wide application prospect in the design of hypersonic vehicles due to its excellent aerodynamic efficiency.Various kinds of waveriders have been developed based on different basic flowfield,which can be chosen according to different design requirements.However,it's generally difficult for the waverider to directly satisfy the engineering requirements of volume efficiency,trim,stability,etc.To overcome these drawbacks,the paper proposes a new design method of hypersonic waverider configuration.In the generation process,the leading edge of the original waverider is kept unchanged.Then at different longitudinal cross section,the profile of the lower surface is determined by the same curve equation,started from the point at the leading edge and cut off at the base plane.The profile function is determined by the sum of a series of power law functions,whose coefficients can be changed according to different design requirements.Different waveriders are obtained according to different constraints.Results show that for this kind of configurations,good shock attachment near the leading edge can be achieved and the pressure distribution on the lower surface is uniform.What's more,the maximum lift-to-drag ratio is even higher than that of the original waverider.Different waveriders with excellent aerodynamic efficiency can also be generated by different constraints of volume efficiency and stability.
引文
1 Kuchemann D.The Aerodynamic Design of Aircraft.Oxford:Pergamon Press,1978.448-510
2 Nonweiler T R F.Aerodynamic problems of manned space vehicles.J R Aeronaut Soc,1959,63:521-528
3 Moore K C.The application of known flow fields to the design of wings with lifting upper surface at high supersonic speeds.R.A.E Technical Report.1965
4 Jones J G,Moore K C,Pike J,et al.A method for designing lifting configurations for high supersonic speeds,using axisymmetric flow fields.Ingenieur-Archiv,1968,37:56-72
5 Mangin B,Benay R,Chanetz B,et al.Optimization of viscous waveriders derived from axisymmetric power-law blunt body flows.J Spacecraft Rockets,2006,43:990-998
6 Rasmussen M L,Jischke M C,Kim B S.Optimization of waverider configurations generated from axisymmetricconical flows.J Spacecraft Rockets,1983,20:461-469
7 Bowcutt K G,Anderson J D,Capriotti D.Viscous optimized hypersonic waveriders.In:AIAA 25th Aerospace Sciences Meeting.Reno,Nevada:AIAA,1987.1-18
8 Corda S,Anderson J D.Viscous optimized hypersonic waveriders designed from axisymmetric flowfields.In:AIAA 26th Aerospace Sciences Meeting.Reno,Nevada:AIAA,1988.1-13
9 Anderson J D,Chang J,Mc Laughlin T A.Hypersonic waveriders:Effects of chemically reacting flow and viscous interaction.In:30th Aerospace Sciences Meeting and Exhibit.Reno,NV:AIAA,1992.1-12
10 Takashima N,Lewis M J.Navier-Stokes computation of a viscous optimized waverider.J Spacecraft Rockets,1994,31:383-391
11 Sobieczky H,Dougherty F C,Jones K.Hypersonic waverider design from given shock waves.In:Proceedings of the First International Hypersonic Waverider Symposium.University of Maryland,1990.1-19
12 Takashima N,Lewis M J.Waverider configurations based on non-axisymmetric flow fields for engine-airframe integration.In:32nd AIAAAerospace Sciences Meeting&Exhibits.Reno,NV:AIAA,1994.1-15
13 Rasmussen M,Duncan B.Hypersonic waveriders generated from power-law shocks.In:AIAA 6th International Aerospace Planes and Hypersonics Technologies Conference.Chattanooga,TN:AIAA,1995.1-9
14 Rodi P E.The osculating flowfield method of waverider geometry generation.In:43rd AIAA Aerospace Sciences Meeting and Exhibit.Reno,Nevada:AIAA,2005.1-8
15 Rodi P E.Vortex lift waverider configurations.In:50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition.Nashville,Tennessee:AIAA,2012
16 Corda S.Star-body waveriders with multiple design Mach numbers.J Spacecraft Rockets,2009,46:1178-1185
17王发民,李立伟,姚文秀,等.乘波体构型方法研究.力学学报,2004,36:513-519
18耿永兵,刘宏,姚文秀,等.锥形流乘波体优化设计研究.航空学报,2006,27:23-28
19耿永兵,刘宏,雷麦芳,等.高升阻比乘波构型优化设计.力学学报,2006,38:540-546
20贺旭照,倪鸿礼.密切内锥乘波体设计方法和性能分析.力学学报,2011,43:803-808
21贺旭照,倪鸿礼.密切曲面锥乘波体--设计方法与性能分析.力学学报,2011,43:1077-1082
22刘传振,白鹏,陈冰雁.双后掠乘波体设计及性能优势分析.空气动力学学报,2017,38:120808
23陈冰雁,刘传振,纪楚群.基于激波装配法的乘波体设计与分析.空气动力学学报,2017,35:421-428
24 Ding F,Liu J,Shen C,et al.An overview of research on waverider design methodology.Acta Astronaut,2017,140:190-205
25 Anderson J D.Hypersonic and High-Temperature Gas Dynamics.2nd ed.New York:Mc Graw-Hill Book Co.,2006.301-305
26 Liu W,Zhang C A,Wang F M.Modification of hypersonic waveriders by vorticity-based boundary layer displacement thickness determination method.Aerospace Sci Tech,2018,75:200-214
27 Liu W,Zhang C A,Han H Q,et al.Local piston theory with viscous correction and its application.AIAA J,2017,55:942-954
28叶友达.近空间高速飞行器气动特性研究与布局设计优化.力学进展,2009,39:683-694
29 Cruz C I,Sova G J.Improved tangent-cone method for the aerodynamic preliminary analysis system version of the hypersonic arbitrary-body program.NASA Technical Note.1990
30 Bertram M H.Hypersonic laminar viscous interaction effects on the aerodynamics of two-dimensional wedge and triangular planform wings.NASA Technical Note.1966
31李维东,韩汉桥,陈文龙,等.考虑高空黏性干扰效应的乘波体气动性能工程预测方法研究.宇航学报,2011,32:1217-1223
32 Debrestian D J,Anderson Jr.J D.Reference temperature method and Reynolds analogy for chemically reacting nonequilibrium flowfields.JThermophys Heat Transfer,1994,8:190-192
33瞿章华.高超声速空气动力学.长沙:国防科技大学出版社,2000
34 White F M.Viscous Fluid Flow.3rd ed.New York:Mc Graw-Hill Book Co.,2006.517
35朱自强,付鸿雁,吁日新,等.翼型和机翼的多目标优化设计研究.中国科学:技术科学,2003,33:999-1006
36 Zhang Q,Ye K,Ye Z,et al.Aerodynamic optimization for hypersonic wing design based on local piston theory.J Aircraft,2016,53:1065-1072
37贾子安,张陈安,王柯穆,等.乘波布局高超声速飞行器纵向静稳定特性分析.中国科学:技术科学,2014,44:1114-1122
2 Nonweiler T R F.Aerodynamic problems of manned space vehicles.J R Aeronaut Soc,1959,63:521-528
3 Moore K C.The application of known flow fields to the design of wings with lifting upper surface at high supersonic speeds.R.A.E Technical Report.1965
4 Jones J G,Moore K C,Pike J,et al.A method for designing lifting configurations for high supersonic speeds,using axisymmetric flow fields.Ingenieur-Archiv,1968,37:56-72
5 Mangin B,Benay R,Chanetz B,et al.Optimization of viscous waveriders derived from axisymmetric power-law blunt body flows.J Spacecraft Rockets,2006,43:990-998
6 Rasmussen M L,Jischke M C,Kim B S.Optimization of waverider configurations generated from axisymmetricconical flows.J Spacecraft Rockets,1983,20:461-469
7 Bowcutt K G,Anderson J D,Capriotti D.Viscous optimized hypersonic waveriders.In:AIAA 25th Aerospace Sciences Meeting.Reno,Nevada:AIAA,1987.1-18
8 Corda S,Anderson J D.Viscous optimized hypersonic waveriders designed from axisymmetric flowfields.In:AIAA 26th Aerospace Sciences Meeting.Reno,Nevada:AIAA,1988.1-13
9 Anderson J D,Chang J,Mc Laughlin T A.Hypersonic waveriders:Effects of chemically reacting flow and viscous interaction.In:30th Aerospace Sciences Meeting and Exhibit.Reno,NV:AIAA,1992.1-12
10 Takashima N,Lewis M J.Navier-Stokes computation of a viscous optimized waverider.J Spacecraft Rockets,1994,31:383-391
11 Sobieczky H,Dougherty F C,Jones K.Hypersonic waverider design from given shock waves.In:Proceedings of the First International Hypersonic Waverider Symposium.University of Maryland,1990.1-19
12 Takashima N,Lewis M J.Waverider configurations based on non-axisymmetric flow fields for engine-airframe integration.In:32nd AIAAAerospace Sciences Meeting&Exhibits.Reno,NV:AIAA,1994.1-15
13 Rasmussen M,Duncan B.Hypersonic waveriders generated from power-law shocks.In:AIAA 6th International Aerospace Planes and Hypersonics Technologies Conference.Chattanooga,TN:AIAA,1995.1-9
14 Rodi P E.The osculating flowfield method of waverider geometry generation.In:43rd AIAA Aerospace Sciences Meeting and Exhibit.Reno,Nevada:AIAA,2005.1-8
15 Rodi P E.Vortex lift waverider configurations.In:50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition.Nashville,Tennessee:AIAA,2012
16 Corda S.Star-body waveriders with multiple design Mach numbers.J Spacecraft Rockets,2009,46:1178-1185
17王发民,李立伟,姚文秀,等.乘波体构型方法研究.力学学报,2004,36:513-519
18耿永兵,刘宏,姚文秀,等.锥形流乘波体优化设计研究.航空学报,2006,27:23-28
19耿永兵,刘宏,雷麦芳,等.高升阻比乘波构型优化设计.力学学报,2006,38:540-546
20贺旭照,倪鸿礼.密切内锥乘波体设计方法和性能分析.力学学报,2011,43:803-808
21贺旭照,倪鸿礼.密切曲面锥乘波体--设计方法与性能分析.力学学报,2011,43:1077-1082
22刘传振,白鹏,陈冰雁.双后掠乘波体设计及性能优势分析.空气动力学学报,2017,38:120808
23陈冰雁,刘传振,纪楚群.基于激波装配法的乘波体设计与分析.空气动力学学报,2017,35:421-428
24 Ding F,Liu J,Shen C,et al.An overview of research on waverider design methodology.Acta Astronaut,2017,140:190-205
25 Anderson J D.Hypersonic and High-Temperature Gas Dynamics.2nd ed.New York:Mc Graw-Hill Book Co.,2006.301-305
26 Liu W,Zhang C A,Wang F M.Modification of hypersonic waveriders by vorticity-based boundary layer displacement thickness determination method.Aerospace Sci Tech,2018,75:200-214
27 Liu W,Zhang C A,Han H Q,et al.Local piston theory with viscous correction and its application.AIAA J,2017,55:942-954
28叶友达.近空间高速飞行器气动特性研究与布局设计优化.力学进展,2009,39:683-694
29 Cruz C I,Sova G J.Improved tangent-cone method for the aerodynamic preliminary analysis system version of the hypersonic arbitrary-body program.NASA Technical Note.1990
30 Bertram M H.Hypersonic laminar viscous interaction effects on the aerodynamics of two-dimensional wedge and triangular planform wings.NASA Technical Note.1966
31李维东,韩汉桥,陈文龙,等.考虑高空黏性干扰效应的乘波体气动性能工程预测方法研究.宇航学报,2011,32:1217-1223
32 Debrestian D J,Anderson Jr.J D.Reference temperature method and Reynolds analogy for chemically reacting nonequilibrium flowfields.JThermophys Heat Transfer,1994,8:190-192
33瞿章华.高超声速空气动力学.长沙:国防科技大学出版社,2000
34 White F M.Viscous Fluid Flow.3rd ed.New York:Mc Graw-Hill Book Co.,2006.517
35朱自强,付鸿雁,吁日新,等.翼型和机翼的多目标优化设计研究.中国科学:技术科学,2003,33:999-1006
36 Zhang Q,Ye K,Ye Z,et al.Aerodynamic optimization for hypersonic wing design based on local piston theory.J Aircraft,2016,53:1065-1072
37贾子安,张陈安,王柯穆,等.乘波布局高超声速飞行器纵向静稳定特性分析.中国科学:技术科学,2014,44:1114-1122