复合翼垂直起降无人机直驱混合动力系统验证设计与试验建模方法  

Verification Design and Experimental Modeling Method of the Direct-Drive Hybrid Power System on A Vertical Take-Off and Landing Unmanned Aerial Vehicle with Composite Wings

作　　者：郑育行 张勋 安斯奇 唐庆如[1] 张启悦 ZHENG Yuhang;ZHANG Xun;AN Siqi;TANG Qingru;ZHANG Qiyue(College of Aviation Engineering,Civil Aviation Flight University of China,Guanghan 618307,China;Institute of Electronic and Electrical Engineering,Civil Aviation Flight University of China,Guanghan 618307,China)

机构地区：[1]中国民用航空飞行学院航空工程学院,广汉618307 [2]中国民用航空飞行学院航空电子电气学院,广汉618307

出　　处：《内燃机工程》2023年第6期77-89,共13页Chinese Internal Combustion Engine Engineering

基　　金：中国民用航空飞行学院科研基金面上项目(J2020-042);中央高校基本科研业务费专项资金项目——学生科研项目(XSY2022-9)。

摘　　要：针对传统复合翼垂直起降(vertical take-off and landing,VTOL)无人机(unmanned aerial vehicle,UAV)垂直机动时间短的固有缺陷,提出了一种应用油电混动技术的直驱混合动力系统拓扑结构。面向起飞质量约15~20 kg的复合翼垂直起降无人机对直驱混合动力系统的软硬件进行开发与选型,设计出了满足上述起飞质量下功率需求的直驱混合动力系统。为对动力系统的设计方法进行验证并在探究其特性规律的基础上建立简化的直驱混合动力系统数学仿真模型,搭建了能够在地面模拟搭载直驱混合动力的复合翼垂起无人机飞行工况与工作模式的直驱混合动力系统地面一体化验证平台。基于此验证平台,设计了直驱混合动力系统特性一体化探究试验方案,采用试验建模法建立了简化的直驱混合动力系统的稳态与动态数学仿真模型,通过仿真与实物对比试验分析法,验证了试验方案的可行性与模型准确性。直驱混合动力系统配装复合翼垂直起降无人机搭建飞行验证平台并完成垂直机动飞行试验,试验过程中,全系统工作正常,飞行验证平台垂直机动时间超过预期指标。飞行试验结果表明,直驱混合动力系统设计方法是正确且有效的,动力系统具有良好的功率输出表现,能够改善复合翼垂起无人机垂直机动时间短的固有缺陷。Aiming to address the intrinsic flaw of the short vertical maneuver time of traditional vertical take-off and landing(VTOL)unmanned aerial vehicles(UAVs)with composite wings,a direct-drive hybrid power system architecture tailored to such UAVs was presented,which employs gasoline-electric hybrid technology.The software and hardware of the direct-drive hybrid power system were developed and selected for the VTOL UAV with a takeoff weight of 15 kg to 20 kg,and a direct drive hybrid power system prototype was created to fulfill the power requirements at the above takeoff weight.Aiming to verify the power system’s design method and establish a simplified mathematical simulation model of the direct-drive hybrid power system on the basis of exploring its characteristic laws,ground integrated verification platform which can simulate flight working conditions and working modes of the direct-drive hybrid power VTOL UAV with composite wing was built.Based on this platform,an integrated test scheme for studying the properties of the direct-drive hybrid power system was devised,and an experimental modeling approach was used to construct a simplified statistic and dynamic mathematical simulation model of it.The simulation and physical comparison test analysis approach confirmed the feasibility of the test plan and the correctness of the model.The direct-drive hybrid power system was coupled with a VTOL UAV with a composite wing and has completed the vertical maneuver flying test.The power system performed normally during the test,and the vertical time of the VTOL UAV surpassed the predicted goals.The flight test results reveal that the direct-drive hybrid power system design method is valid and effective,and the power system has outstanding output performance and may overcome the intrinsic flaw of short vertical maneuvering time of traditional VTOL UAV with composite wings.

关 键 词：垂直起降 无人机 复合翼垂直起降无人机 直驱混合动力系统拓扑结构 油电混动 动力系统一体化验证平台 试验建模法 飞行验证平台 

分 类 号：V275[航空宇航科学与技术—飞行器设计]