| 引用本文: | 李敏娇,Laith K. Abbas,芮筱亭,王国平.柔性火箭弹气动力计算精度预测[J].哈尔滨工业大学学报,2016,48(10):91.DOI:10.11918/j.issn.0367-6234.2016.10.013 |
| LI Minjiao,Laith K. Abbas,RUI Xiaoting,WANG Guoping.The prediction of flexible rocket’s aerodynamic force computational accuracy[J].Journal of Harbin Institute of Technology,2016,48(10):91.DOI:10.11918/j.issn.0367-6234.2016.10.013 |
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| 摘要: |
| 为验证小变形小攻角下基于准定常和线性理论进行柔性火箭弹气动力计算的合理性，采用计算流体力学(CFD)方法预测了某火箭弹的升力及阻力系数，并在此基础上与经验公式相结合，获得该火箭弹沿轴向的单位长度升力和阻力系数导数分布.应用多体系统传递矩阵法计算了该火箭弹的固有频率和振型，在准定常及线性理论的假设条件下,结合已得到的气动力系数导数,计算了基于火箭弹一阶振型的两个弯曲模型在不同攻角下的单位长度气动力系数分布.与CFD计算结果进行对比，发现该火箭弹在实际飞行条件下，该计算方法精度较好，在远超于实际的大变形时、攻角较大的情况下在头部和弹身处仍具有一定精度，但尾部误差较大，总体精度降低.
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| 关键词: 多体系统传递矩阵法 柔性火箭弹 振动特性 CFD 气动力 |
| DOI：10.11918/j.issn.0367-6234.2016.10.013 |
| 分类号:V211 |
| 文献标识码:A |
| 基金项目:国家自然科学基金(5,7)；新世纪优秀人才支持计划(NCET-10-0075)；高校博士点基金(5,7) |
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| The prediction of flexible rocket’s aerodynamic force computational accuracy |
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LI Minjiao, Laith K. Abbas, RUI Xiaoting, WANG Guoping
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（Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing 210094, China）
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| Abstract: |
| To verify the reasonability of calculating the flexible rocket’s aerodynamic forces based on the quasi steady theory and the linear theory when both the deformation and the attack angle are small enough, the computational fluid dynamics (CFD) method is used to calculate the rocket’s lift and drag coefficients. Using this method and the empirical formula, the rocket’s aerodynamic coefficient derivatives distributions are obtained. The transfer matrix method of the linear multibody system dynamics (MSTMM) is applied to get the rocket’s frequencies and mode shapes. Under the assumption of quasi-steady theory and linear theory, using the obtained aerodynamic coefficient derivatives distribution, the aerodynamic forces of two bended rochets’ the deformations of which are based on the first order mode shape are calculated. To judge the reasonability of the linear theory, the CFD method is also used to simulate the two models. Compared with the CFD method, the proposed method has high precision under the practical flight conditions. In addition, when the bending degree is much higher than the possible deformation, the precision of the rocket’s nose is still fine but very low in the tails position for the proposed method.
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| Key words: transverse matrix method of multi-body system flexible rocket vibration characteristic CFD aerodynamic force |
