摘要
降落伞强度空投试验模型的气动-动力学特性仿真研究对空投试验方案设计和降落伞减速系统性能的考核至关重要。文章运用数值模拟手段分析了空投试验模型的气动特性和气动稳定性,探讨了降落伞开伞前空投试验模型的弹道轨迹和运动姿态的变化,并针对不同飞行攻角下空速管动压测试值与实际开伞动压存在相对偏差所造成的影响进行了分析。结果表明:空投试验模型的轴向力系数在攻角大于4°时有所下降。法向力系数和俯仰力矩系数随着飞行攻角增加以近似线性的方式增大,压心位置后移,气动稳定性良好。在模型投放后至降落伞开伞前的过程中,随着高度下降空投试验模型的速度以近似线性的形式增大,且俯仰角和攻角均存在周期摆动现象。由于飞行攻角的影响,空速管测得的动压值与开伞实际动压存在相对偏差,但相对偏差范围不会超过14%。研究结果可以为降落伞强度空投试验的方案设计提供参考。
Aerodynamic and dynamic numerical research of parachute airdrop model is a main concern for airdrop test design and parachute deceleration system performance evaluation. In this paper, aerodynamic characteristics and stability of the airdrop test model are investigated, trajectory and motion posture are also discussed. Furthermore, the influence induced by dynamic pressure relative deviation between the measurement value of airspeed head and real value when parachute opening in different angles of attack are also analyzed in this paper. The result shows axial force coefficient decreases when angle of attack is above 4°. Normal force coefficient and pitching moment coefficient have a linear increment with angle of attack increases. The aero- dynamic stability is high enough and the airdrop test center of pressure location moves back with the angle of attack increases. After airdrop test model extraction and before parachute opening, the velocity of airdrop test model has a linear increment with altitude declines, and there is a periodic oscillation in angle of pitch and an- gle of attack. Since the influence of angle of attack, there is dynamic pressure relative deviation between the measurement value of airspeed head and real value when parachute opening. However, the relative deviation range is not more than 14%. The research result can be applied in parachute airdrop test design.
作者
张章
王立武
王文强
王奇
吕智慧
李健
ZHANG Zhang1,2,3 WANG Liwu1 WANG Wenqiang1 WANG Qi1 LYU Zhihui1 LI Jian1(1 Beijing Institute of Space Mechanics ＆ Electricity, Beijing 100094, China） （2 Key Laboratory for Nondestructive Spacecraft Landing Technology of CAST, Beijing 100094, China） （3 Beijing Engineering Technology Research Center of Aerial Intelligent Remote Sensing Equipments, Beijing 100094, China)
出处
《航天返回与遥感》
CSCD
2018年第1期1-10,共10页
Spacecraft Recovery & Remote Sensing
基金
国家自然科学基金(11602018)
关键词
降落伞空投试验
气动性能
动力学特性
动压偏差
数值模拟
航天返回
parachute airdrop test
aerodynamic performance
dynamic charanteristics
dynamic pressure deviation
numerical simulation
space recovery
作者简介
张章，男，1986年生，2014年获北京航空航天大学流体机械及工程专业博士学位，高级工程师。主要研究方向为航天器返回与着陆技术及空气动力学。E—mail：xiaodanni198649@sina．com。
