Impact Characteristics of Drone Aircraft in Airbag Cushion Landing
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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。Abstract: 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.
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Key words:
- drone aircraft /
- airbag /
- cushion landing /
- dynamic response /
- cushion parameter
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图 4 靶机着陆缓冲减速后的小角度侧偏
Figure 4. Small angle cornering of drone aircraftafter landing buffer deceleration
图 5 落震试验与模拟着陆过程中质心处的过载曲线
Figure 5. Overload curves at the center of mass duringlanding process in simulation and drop test
图 6 靶机着陆0.084 s时的Mises应力分布
Figure 6. Mises stress distribution of the drone aircraft landing at 0.084 s
图 7 前机身腹部的应力和应变分布
Figure 7. Stress and strain distribution of front fuselage underpart
图 8 前、后机身上下梁上不同位置的应力
Figure 8. Stress at upper and lower beams of front and rear fuselage
图 9 中机身和机翼梁上不同位置的应力
Figure 9. Stress at upper and lower beams of middle fuselage and wing
图 11 着陆前后气囊压力和法向接触力曲线
Figure 11. Pressure and normal contact force curves of front and rear airbags during landing
图 12 排气口面积不同时靶机着陆过程中重心处速度 (a) 和过载 (b) 的变化曲线
Figure 12. Velocity (a) and overload (b) curves at the mass center of drone aircraft during landing with different exhaust port area
图 13 排气口面积不同时靶机着陆过程中前后气囊的压力峰值与机身的Mises应力对比
Figure 13. Comparison of front and rear airbags’ peak pressure and Mises stress of fuselage during landing with different exhaust port areas
图 14 不同初始着陆速度下靶机重心的速度变化曲线
Figure 14. Velocity curves of drone’s center of gravity at different initial landing velocities
图 16 带有俯仰角的靶机着陆过程中的速度变化曲线
Figure 16. Velocity curves of drone aircraft landing with pitch angle
表 1 靶机材料的相关参数
Table 1. Aircraft material parameters
Material Density/(g·cm−3) Elastic modulus/
GPaPoisson’s ratio Yield stress/
MPaAluminium alloy 2.800 66 0.330 325 Alloy structural steel 7.760 196 0.300 835 Glass fiber composite 2.030 23 0.074 Carbon fiber composite 1.560 58 0.074 
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表 2 不同缓冲工况的相关参数
Table 2. Relevant parameters of different cushion conditions
Case No. Orifice
area/mm2Initial internal
pressure/MPaDischarge pressure
threshold/kPaLanding
speed/（m·s−1）Pitch
angle/（°）1 0 0.101 10.1 6 0 2 1696.4 0.101 10.1 6 0 3 2827.4 0.101 10.1 6 0 4 3958.4 0.101 10.1 6 0 5 2827.4 0.106 10.1 6 0 6 2827.4 0.108 10.1 6 0 7 2827.4 0.110 10.1 6 0 8 2827.4 0.101 30.3 6 0 9 2827.4 0.101 50.5 6 0 10 2827.4 0.101 10.1 4 0 11 2827.4 0.101 10.1 5 0 12 2827.4 0.101 10.1 7 0 13 2827.4 0.101 10.1 6 5 14 2827.4 0.101 10.1 6 −5 15 2827.4 0.101 10.1 6 8 16 2827.4 0.101 10.1 6 −8
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