某型新能源飞机航程航时研究及飞行试验  

Research on flight time and flight test of a new energy aircraft

作　　者：周国庆[1] 李英 王锋[1] 陶晶 ZHOU Guo-qing;LI Ying;WANG Feng;LI Ya-dong(Liaoning Key Laboratory of General Aviation,Shenyang Aerospace University,Shenyang 110136,China;不详)

机构地区：[1]沈阳航空航天大学辽宁省通用航空重点实验室,沈阳110136 [2]沈阳航空航天大学材料科学与工程学院,沈阳110136

出　　处：《新能源航空》2023年第4期9-15,共7页

基　　金：辽宁省教育厅项目(JYT19005);辽宁省教育厅项目(LJKMZ20220568)

摘　　要：受限于电池能量密度的不足,为了增加新能源电动飞机的航程航时,在以现有的新能源电动飞机基础上进行了优化、分析,通过增加适当的电池重量以及在最大升阻比的构型状态下进行飞行,达到增加航程航时的目的。根据ASTM F2245适航条款及项目指标要求,基于不同于油动飞机的电动力方程和输出功率、总体参数、气动参数、螺旋桨的效率以及锂电池能量密度等特点,采用辛卜生积分和龙格-库塔求微分方程的计算方法,按照优化的输入条件,对某型新能源电动飞机进行了整个的性能分析。通过仿真计算,并与飞行试验结果对比,结果表明:计算结果与试验结果具有良好的一致性,且航程航时满足指标要求。In order to increase the range time of the new energy electric aircraft,it is optimized and analyzed on the basis of the existing new energy electric aircraft,by increasing the proper weight of the battery and flying under the configuration of the maximum lift-drag ratio,the aim of increasing the range flight time is achieved.According to ASTM F2245 airworthiness terms and project specifications,based on the characteristics of different from oil-powered aircraft such as electric power equation and output power,overall parameters,aerodynamic parameters,propeller efficiency and energy density of lithium battery,the entire performance of a new energy electric aircraft was analyzed under optimized input conditions using the symbiosis integral and the runge-Kuta differential equation method.The simulation results are compared with the flight test results.The results show that the calculated results are in good agreement with the test results,and the range time meets the requirements.

关 键 词：新能源 电动飞机 航程 航时 升阻比 辛卜生积分 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]