靶机气囊缓冲着陆过程中的冲击特性  

Impact Characteristics of Drone Aircraft in Airbag Cushion Landing

作　　者：段文琪 蒲克强 方雄 党万腾 龙舒畅 姚小虎[1] DUAN Wenqi;PU Keqiang;FANG Xiong;DANG Wanteng;LONG Shuchang;YAO Xiaohu(School of Civil Engineering and Transportation,South China University of Technology,Guangzhou 510640,Guangdong,China;Technology Center of Chengdu Aircraft Industrial(Group)Co.,Ltd.,Chengdu 610092,Sichuan,China)

机构地区：[1]华南理工大学土木与交通学院,广东广州510640 [2]成都飞机工业(集团)有限责任公司技术中心,四川成都610092

出　　处：《高压物理学报》2021年第6期210-220,共11页Chinese Journal of High Pressure Physics

基　　金：中国博士后科学基金(2020M672614)。

摘　　要：针对缓冲着陆过程中靶机气囊的瞬态动力学响应问题,采用显式动力计算方法和均压气囊模型分析靶机气囊缓冲着陆阶段机身、机翼在冲击作用下的动力学响应,得到靶机回收过程中的姿态与强度特性和气囊变化参数。探讨了气囊缓冲参数(排气口面积、气囊初始内压及排气阈值)和靶机状态等参数对靶机着陆过程中机身的影响。结果表明:标准工况下,经过气囊缓冲后的靶机姿态、强度符合安全着陆要求。通过分析着陆过程中的相关参数发现,气囊排气口面积对缓冲效果影响较大,气囊排气压力阈值和初始内压影响较小,同一气囊对靶机不同着陆初始速度的适应性高,带有俯仰角的靶机后着陆后机身部分区域的局部应力偏大。该方法可以广泛用于飞机气囊缓冲的动力学计算,结合气囊落震试验以获取相应的气囊参数和机身结构响应数据,为靶机设计提供依据。Aiming at the transient dynamic response of drone aircraft cushion landing with airbag,the explicit dynamic calculation method and pressure equalizing airbag model are adopted to analyze the dynamic response of drone aircraft fuselage and wings under impact during cushion landing with airbag,and the attitude and strength characteristics and airbag parameters in the recovery process of drone aircraft are obtained.The effects of airbag cushion parameters(orifice area,initial internal pressure and exhaust threshold)and drone aircraft state on the fuselage of drone aircraft during landing are discussed.The results show that:under the standard conditions,the aircraft’s attitude and strength meet the requirements of safe landing after buffering with airbag.Through the analysis of different landing parameters,it is found that the area of the airbag exhaust vent has a great impact on the cushioning effect,while the threshold of the airbag exhaust pressure and the initial internal pressure have little impact on it.The same airbag has high adaptability to different initial landing speeds of drone aircraft.The local stress of the later landing fuselage of the drone aircraft with pitch angle is too large.This method can be widely used in the dynamic calculation of aircraft airbag cushion.Combined with the airbag drop test,the corresponding airbag parameters and fuselage structure response data can be obtained,which provides a basis for the design of target aircraft.

关 键 词：靶机 气囊 缓冲着陆 动力学响应 缓冲参数 

分 类 号：O347[理学—固体力学] V222[理学—力学]