Lateral-Direction Stability Analysis on Aerodynamic Shape Parameters for a Lifting-Body Configuration
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摘要: 针对高速飞行器存在横侧向耦合易失控问题，建立了基于部件组合思想的CST几何外形参数化建模方法，以升力体外形为例，采用拉丁超立方试验设计方法和高速气动特性快速分析方法，分析了升力体主要布局参数对横侧向耦合稳定性参数开环动态偏离稳定判据（Cnβ，dyn）和闭环横向控制偏离判据（LCDP）的影响规律.升力体外形主导布局参数对横向操纵滚转反逆参数LCDP是二次非线性影响，横侧向稳定性的主导布局参数随着攻角变化有明显变化.文章为耦合稳定性影响规律研究建立了有效的分析方法，研究结论可为高超声速升力体式飞行器总体抗失控设计提供规律建议.Abstract: Aiming at the problem that the hypersonic vehicle is easy to lose control due to lateral coupling, the methods of CST parametric modeling based on part combination were established in this paper. Taking the lifting body as an example, the Latin Hypercube design method and the fast analysis method of hypersonic aerodynamic properties were used. The influence of the lifting-body's main shape parameters on the lateral coupling stability parameters was analyzed, such as dynamic directional stability parameter((Cnβ, dyn) and lateral control departure parameter(LCDP). The dominant shape parameter had a quadratic nonlinear effect on LCDP. The lateral coupling stability parameters changed significantly with the angle of attack. This paper established an effective analysis method for the study of the lateral coupling stability. It can provide regular suggestions for the overall anti-runaway design of hypersonic lifting-body vehicles.
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图 1 部件组合CST参数化建模流程
Figure 1. Process of CST parametric modeling based on part combination
图 2 截面曲线CST参数化建模及几何绝对误差
Figure 2. Parametric modeling of section curve and geometric absolute error
图 4 某升力体数模与参数化建模外形气动力估算误差(Ma=5)
Figure 4. Aerodynamic estimation errors of lifting-body CAD shape and parametric shape(Ma=5)
图 5 某升力体工程估算与CFD计算气动力及力矩系数变化曲线对比(Ma=5)
Figure 5. Comparison between the estimated values and CFD calculation of the lifting-body′s aerodynamic coefficients(Ma=5)
图 6 升力体工程估算与CFD计算耦合稳定性对比
Figure 6. Comparison between the estimated values and CFD calculation of the lifting-body′s coupling stability parameters
图 7 正交与拉丁超立方设计对比(9个样本点)
Figure 7. Comparison between the orthogonal design and Latin hypercube design(9 sample points)
图 9 升力体布局参数对Cnβ, dyn影响的Pareto图
Figure 9. Pareto diagram of the influence of lifting-body′s main shape parameters on Cnβ, dyn
图 10 升力体布局参数对LCDP影响的Pareto图
Figure 10. Pareto diagram of the influence of lifting-body′s main shape parameters on LCDP
表 1 升力体外形参数表
Table 1. Geometry parameter range of a lifting body
parameters parameter declaration lower upper baseline x1 the length of the body′s foreside 0.5 0.7 0.6 x2 the length of the body′s hindside 0.26 0.46 0.36 x3 the height of the body′s bottom 0.1 0.3 0.2 x4 the length of the vertical fin 0.01 0.2 0.08 x5 the length of the vertical fin′s foreside 0.1 0.3 0.2 x6 the length of the vertical fin′s hindside 0.01 0.2 0.1 x7 the length of the body′s side direction cut 0.15 0.35 0.25 x8 the width of the body′s bottom 0.4 0.6 0.5 x9 the location of the flap 0.01 0.1 0.03 x10 the length of the flap 0.01 0.2 0.08 x11 the chord of the flap 0.01 0.2 0.1 
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表 2 气动分析状态
Table 2. State of areodynamic analysis on a lifting body
Ma α/(°) δde/(°) 5, 15 0, 5, 10, 20, 30, 40 0, 10
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表 3 偏航动态稳定性参数Cnβ, dyn系数表线性项
Table 3. Linear terms of coefficient table on dynamic directional stability parameter
Cnβ, dyn α=0° α=40° Ma=5 Ma=15 Ma=5 Ma=15 constant 0.030 08 0.025 04 0.033 82 0.012 12 x1 -0.035 21 -0.028 57 -0.034 65 -0.012 18 x2 0.006 39 0.003 31 -0.010 52 0.010 30 x3 0.203 17 0.195 60 0.020 60 -0.007 62 x4 0.050 06 0.029 07 0.067 13 0.044 02 x5 -0.018 45 -0.017 81 -0.007 43 0.001 38 x6 0.010 80 0.002 34 0.021 02 0.015 25 x7 -0.047 56 -0.044 61 -0.031 26 -0.014 83 x8 -0.078 34 -0.066 46 -0.060 57 -0.019 30 x9 -0.023 39 -0.017 31 -0.013 30 -0.003 06 x10 -0.014 84 -0.012 50 -0.011 14 -0.003 41 x11 0.002 85 0.001 98 -0.000 85 0.001 80
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表 4 横向操纵滚转反逆参数LCDP系数表线性项
Table 4. Linear terms of coefficient table on lateral control departure parameter(LCDP)
LCDP α=0° α=40° Ma=5 Ma=15 Ma=5 Ma=15 constant 0.038 21 0.024 34 0.018 30 0.028 23 x1 -0.045 31 -0.029 91 -0.037 17 -0.049 54 x2 0.003 10 0.006 85 -0.005 82 -0.018 93 x3 0.199 53 0.196 18 0.010 24 -0.020 50 x4 0.051 98 0.031 58 0.047 78 0.033 40 x5 -0.022 39 -0.017 89 -0.003 91 -0.009 59 x6 0.007 48 0.002 52 0.004 48 -0.003 38 x7 -0.052 27 -0.043 32 -0.011 63 -0.012 58 x8 -0.091 07 -0.066 63 -0.029 76 -0.035 70 x9 -0.021 55 -0.013 77 0.074 16 0.070 01 x10 -0.019 93 -0.014 00 0.037 12 0.034 30 x11 0.003 15 0.005 06 0.016 54 0.011 62
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