CAJ | 학술논문

采用数值法计算了膜扑翼飞行器的气动力,并与实验结果进行了对比.将惯性力和刚性扑翼产生的气动力作为原始载荷,采用有限元法计算了膜扑翼的变形,分析了此变形引起的气动力的变化.与实验结果的对照表明,该计算结果有较好的可靠性.与刚性扑翼相比,膜扑翼对升力的影响不大,但是大大地增大了推力的正峰值,使得推力有较大的增加,从而改善了扑翼飞行器的气动性能.
채용수치법계산료막복익비행기적기동력,병여실험결과진행료대비.장관성력화강성복익산생적기동력작위원시재하,채용유한원법계산료막복익적변형,분석료차변형인기적기동력적변화.여실험결과적대조표명,해계산결과유교호적가고성.여강성복익상비,막복익대승력적영향불대,단시대대지증대료추력적정봉치,사득추력유교대적증가,종이개선료복익비행기적기동성능.
The numerical method to study aerodynamics of the flapping-wing micro aero vehicles (FMAVs) was adopted, and the result was compared with the experimental data. The finite element method was employed to calculate the deformation caused by the inertial force and aerodynamic force of the rigid flapping-wing, and the change in aerodynamic force caused by the deformation was analyzed. Comparison with the experimental data showed the reliability of the calculation results. Compared with the rigid flapping-wing, the membrane flapping-wing affects the lift little, but increases the thrust because the positive peak value of thrust increases greatly, thus improving the aerodynamic performance of flapping-wing aerial vehicles.