Free flight static and dynamic aerodynamic characteristics for re-entry capsule at transonic speed
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摘要: 采用运动自由度不受约束的风洞自由飞试验技术，研究大钝头、小升阻比的类"联盟号"返回舱在跨声速区自由飞行时的运动特性与气动特性规律。以单平面光路拍摄返回舱模型在风洞中自由飞动态运动过程图像，经图像自动判读获取其运动轨迹与姿态角，并以参数微分法对模型运动姿态角进行线性与非线性气动参数辨识，得到模型俯仰方向的静、动稳定导数系数。研究结果表明：采用线性与非线性气动参数辨识所获得的静稳定导数系数Cmα均小于零，在数值上差距不大；从非线性气动参数辨识结果看，返回舱静稳定导数系数的数值主要由线性项Cmα0决定，非线性项Cmα2α2所占比例较小；类"联盟号"返回舱静稳定导数系数的非线性较弱，可近似用线性气动模型进行辨识。在试验迎角范围内，返回舱的动稳定导数系数呈现出非线性性质，且在小迎角范围内由线性项
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图 4 返回舱模型俯仰角位移时间历程及相平面图
Figure 4. History of pitch angle and phase-plane diagram of the re-entry capsule
图 6 迎角测量值与辨识回代值对比图
Figure 6. Comparison of measurement and back substitution of angle of attack
图 7 非线性参数辨识的线性项、非线性项及总静稳定导数系数随迎角α变化曲线
Figure 7. The linear, nonlinear term and total static derivative coefficient curves vary with angle of attack α for nonlinear parameter identification
图 8 非线性参数辨识的线性项、非线性项及总动稳定导数系数随迎角α变化曲线
Figure 8. The linear, nonlinear term and total dynamic derivative coefficient curves vary with angle of attack α for nonlinear parameter identification
表 1 返回舱模型的流场参数与质量特性参数
Table 1. Model mass parameters of re-entry capsule
Parameters of flow field Parameters of mass Ma v/(m·s-1) q/Pa m/g I/(g·cm2) xg/mm yg/mm xg/d 0.8 236 32 281.2 139.68 97.266 15.34 1.34 0.385 
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表 2 线性与非线性气动参数辨识结果对比表
Table 2. Comparison of nonlinear and linear aerodynamic parameter identification
Linear model Nonlinear model Static derivatives coefficient Dynamic derivatives coefficient Fitting precision Static derivatives coefficient Dynamic derivatives coefficient Fitting precision Cmα 
SD(α) Cmα0 Cmα2 
SD(α) -0.11463 -3.7269 0.027 -0.09463 -0.10455 -1.2583 -42.4665 0.0018
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