[1]李民民.先进布局飞机自由滚转试验现象的仿真[J].大众科技,2021,23(7):40-42.
　Simulation of Free-to-Roll Test Phenomenon for an Advanced Layout Aircraft[J].Popular Science & Technology,2021,23(7):40-42.
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先进布局飞机自由滚转试验现象的仿真()
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《大众科技》[ISSN:1008-1151/CN:45-1235/N]

卷:
23
期数:
2021年7
页码:
40-42
栏目:
电力与机械
出版日期:
2021-07-20

文章信息/Info

Title:
Simulation of Free-to-Roll Test Phenomenon for an Advanced Layout Aircraft
作者:
李民民
（南京航空航天大学，江苏 南京 210016）
关键词:
自由滚转试验; 非定常气动力; 极限环振荡; 气动力建模; 飞行仿真
Keywords:
free-to-roll test unsteady aerodynamics limit-cycle oscillation aerodynamic modeling flight simulation
文献标志码:
A
摘要:
当迎角较大时，小展弦比飞翼布局飞机产生了滚转方向的极限环振荡。为仿真该试验现象，文章通过建立相应的非线性气动力模型，准确描述了非定常气动力，进而以刚体运动方程模拟了风洞自由滚转试验过程。相较于传统线性化气动导数模型，该气动力模型表现出更高的建模精度，成功复现了该机的滚转自激振荡现象，展现出在大迎角非定常气动力建模方面的独特效果。最终仿真结果表明，滚转自激振荡是正负阻尼与静稳定性共同作用的结果。
Abstract:
At high angle of attack, limit-cycle roll oscillations are usually observed on the low aspect ratio flying wing. In order to simulate this test phenomenon, a special nonlinear aerodynamic model was applied to describe the unsteady aerodynamic loads accurately, and then the free-to-roll test process was simulated by kinematics equation of rigid body. Compared with the linear model of aerodynamic derivatives, this nonlinear model is more accurate in unsteady aerodynamic modeling at high angle of attack, which makes the recurrence of self-excited oscillation, and show the unique effect of unsteady aerodynamic modeling at high angle of attack. Finally, the simulation results illustrate that self-excited roll oscillation is the result of damping, negative damping and static stability.

参考文献/References:

【参考文献】 [1]　刘伟，杨小亮，张涵信，等. 大攻角运动时的机翼摇滚问题研究综述[J]. 力学进展，2008，38(2): 214-228. [2] Ericsson L, King H. Rapid prediction of high alpha unsteady aerodynamics of slender-wing aircraft[J]. Journal of Aircraft, 1992, 29(1): 85-92. [3] 陈永亮，沈宏良，刘昶. 机翼摇晃预测与抑制[J]. 航空学报，2005，26(3): 276-280. [4] Ohshima R, Miyaji K. Numerical simulations of free-to- roll wing rock phenomena by the time spectral CFD[C]. AIAA Scitech 2020 Forum, 2020. [5] Wang B, Deng X, Ma B, et al. Modeling of wing rock using frequency spectrum analysis to free-to-roll time history[J]. Journal of Aircraft, 2011, 48(3): 805-811. [6] Shen L, Huang D, Wu G. Effects of yaw-roll coupling ratio on the lateral-directional departure prediction and restraint[J]. Chinese Journal of Aeronautics, 2019, 32(10): 2239-2253.

相似文献/References:

[1]沈 霖 黄 达 杨 勐.基于非定常气动力模型的尾旋仿真研究[J].大众科技,2013,15(11):87.

备注/Memo

备注/Memo:
【收稿日期】2021-05-05 【基金项目】国家自然科学基金（11872209）。 【作者简介】李民民（1995－），男，南京航空航天大学在读硕士研究生，研究方向为非定常空气动力学。
更新日期/Last Update: 2021-10-22