小迎角高超声速非旋转钝锥非线性运动分析

doi:10.7527/S1000-6893.2015.0227

流体力学与飞行力学

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小迎角高超声速非旋转钝锥非线性运动分析

蒋增辉, 宋威, 陈农

中国航天空气动力技术研究院, 北京 100074

收稿日期:2015-07-08 修回日期:2015-08-16 出版日期:2016-05-15 发布日期:2015-09-30
通讯作者: 蒋增辉,Tel.:010-68376792 E-mail:jzhhit@163.com E-mail:jzhhit@163.com
作者简介:蒋增辉,男,博士,高级工程师。主要研究方向:非定常空气动力学、超空泡流体动力学。Tel:010-68376792 E-mail:jzhhit@163.com;宋威,男,硕士,助理工程师。主要研究方向:非定常空气动力学。Tel:010-68376792 E-mail:623426297@qq.com;陈农,男,博士,研究员。主要研究方向:非定常空气动力学。Tel:010-68741250 E-mail:chennong27@126.com
基金资助:
国家自然科学基金(11202200)

Analysis of nonlinear motion for hypersonic non-spinning blunt cones at small angle of attack

JIANG Zenghui, SONG Wei, CHEN Nong

China Academy of Aerospace Aerodynamics, Beijing 100074, China

Received:2015-07-08 Revised:2015-08-16 Online:2016-05-15 Published:2015-09-30
Supported by:
National Natural Science Foundation of China (11202200)

摘要/Abstract

摘要：

采用分段拟合技术对小迎角高超声速(马赫数Ma=6)非旋转钝锥双平面拍摄风洞自由飞试验结果进行了分析,获得了非旋转钝锥在小迎角高超声速下气动导数非线性的具体形式,分析了非旋转钝锥在小迎角下的非线性运动特点。研究发现在小迎角范围内钝锥的动导数系数均呈现明显的非线性,而静导数系数非线性较弱,可近似为线性。各组试验的静、动导数系数的非线性形式表明,除模型Ⅱ外的其余模型均为两方向振幅不同的极限圆锥运动,模型Ⅱ为极限平面运动。每组试验两个平面的静导数系数在小迎角范围内保持基本相等。而无论出现极限圆锥运动的四组试验还是出现极限平面运动的一组试验,模型在俯仰和偏航两个方向的动导数系数均存在较大差异。

关键词: 非线性运动, 气动导数, 小迎角, 高超声速, 极限圆锥运动, 极限平面运动

Abstract:

With over-lapping sectional fitting technique, the data of wind-tunnel free-flight tests with biplanar optical system at Mach number 6 and small angle of attack, are analyzed. The concrete form of nonlinear aerodynamic derivatives of hypersonic non-spinning blunt cones at small angle of attack is acquired and the characteristic of nonlinear motion of non-spinning cones is studied. The obvious nonlinearity of dynamic stability derivative coefficient has been found at small angle of attack, while the nonlinearity of static stability derivative coefficient is so weak that it can be considered as almost linear. The nonlinear form of aerodynamic derivative coefficients indicate that all the test models appear limit coning motion with different amplitudes between the pitch and yaw direction, except that one model appears limit planar motion. The static stability derivative coefficients are nearly equal in pitch and yaw directions at small angle of attack for each test. All the models, appearing both limit coning motion and limit planar motion, present different dynamic stability derivative coefficients between pitch direction and yaw direction.

Key words: nonlinear motion, aerodynamic derivative, small angle of attack, hypersonic, limit coning motion, limit planar motion

中图分类号:

蒋增辉, 宋威, 陈农. 小迎角高超声速非旋转钝锥非线性运动分析[J]. 航空学报, 2016, 37(5): 1454-1461.

JIANG Zenghui, SONG Wei, CHEN Nong. Analysis of nonlinear motion for hypersonic non-spinning blunt cones at small angle of attack[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(5): 1454-1461.

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E-mail：hkxb@buaa.edu.cn

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小迎角高超声速非旋转钝锥非线性运动分析

Analysis of nonlinear motion for hypersonic non-spinning blunt cones at small angle of attack

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