分离式飞机应急数据记录跟踪系统设计与试验

Design and test of the ejection emergency flight data recording and tracking system

分离式飞机应急数据记录跟踪系统具备智能弹射与分离、拖曳式跟踪拍摄、缓降与应急漂浮和数据传输等功能,针对弹射和缓降等过程进行了系统设计和无人机试验验证。同时,针对伞-囊组合体的特点,分析了气囊尾流区中伞衣阻力系数的变化规律。结果表明:气囊半径和伞衣名义直径是影响伞衣阻力系数的主要因素;伞衣阻力系数随气囊半径增大而下降,随伞衣名义直径增大而上升;在气动力分析和数值模拟的基础上,确定了伞衣阻力系数的计算公式。无人机试验完成各项设计功能,系统整体方案合理可行,为后续工程应用提供了重要参考。

The ejection emergency flight data recording and tracking system consists of the intelligent ejection separation,tow-type image tracking,inflatable soft-landing and data transmitting.In this paper,the key subsystem design and UAV test verification are carried out.According to the characteristics of the parachute-airbag module,the variation of the canopy drag coefficient in the airbag wake region is analyzed.The results show that the radius of the airbag and the nominal diameter of the canopy are the main factors affecting the canopy drag coefficient.The canopy drag coefficient decreases with the increase of the radius of airbag,and increases with the increase of the nominal diameter of the canopy.Based on the aerodynamic analysis and the numerical simulation,the canopy drag coefficient formula is obtained.Meanwhile,the full functions are achieved by UAV test,and it is proved that the system scheme is reasonable and feasible.It provides an important reference for the subsequent engineering application.