助推火箭安装偏差对小型无人机发射安全的影响
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摘要
针对火箭助推发射无人机起飞的安全性问题,结合研制的无人机,采用仿真和实际试飞试验结合的方法,建立了发射阶段动力学模型,仿真计算了助推火箭安装偏差对无人机发射安全的影响。仿真结果表明,当助推火箭安装角纵向偏差控制在-0.5°~0°以内,横向偏差控制在-0.5°~0.5°以内时,无人机发射起飞是安全的。此外,在无人机的飞行试验中,采用标定助推火箭挡板的方法,使得助推火箭安装角控制在仿真结果建议的偏差范围内,保障了无人机发射的起飞安全,从而验证了仿真模型的可靠性。
To improve the launch safety of unmanned aerial vehicle( UAV) with rocket assisted take-off,a dynamic model was built by combining simulation and flight test data to study the effect of the booster rocket installation deviation. It was found that when the longitudinal installation deviation is within-0. 5° ~ 0° and the lateral deviation is within-0. 5° ~ 0. 5°,the lunch take-off of the UAV is safe. Furthermore,the simulation results from the dynamic model were validated in the UAV flight test. It was demonstrated that if the installation angle of the booster rocket is controlled by a calibration booster baffle to be within the suggested range from the simulations,the UAV can be launched safely.
To improve the launch safety of unmanned aerial vehicle( UAV) with rocket assisted take-off,a dynamic model was built by combining simulation and flight test data to study the effect of the booster rocket installation deviation. It was found that when the longitudinal installation deviation is within-0. 5° ~ 0° and the lateral deviation is within-0. 5° ~ 0. 5°,the lunch take-off of the UAV is safe. Furthermore,the simulation results from the dynamic model were validated in the UAV flight test. It was demonstrated that if the installation angle of the booster rocket is controlled by a calibration booster baffle to be within the suggested range from the simulations,the UAV can be launched safely.
引文
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[3]石林,马威,杨龙军.基于ADAMS的无人机零长发射动力学仿真及分析[J].弹箭与制导学报,2017,37(2):37-39.SHI Lin,MA Wei,YANG Longjun.Simulation and analysis of UAV zero-length launching dynamics based on ADAMS[J].Journal of projectiles,rockets,missiles and guidance,2017,37(2):37-39.
[4]罗浩.无人机飞行姿态检测及控制研究[J].电子世界,2018(1):175-176.LUO Hao.UAV flight attitude detection and control research[J].Electronic world,2018(1):175-176.
[5]胡明,刘高,梁振刚.小型无人机弹射系统的动力学研究[J].成组技术与生产现代化,2017(3):6-9,13.HU Ming,LIU Gao,LIANG Zhengang.Dynamics research on the spring loaded launch system of small UAV[J].Group technology&production modernization,2017(3):6-9,13.
[6]仲培泳.火箭助推发射飞机模型设计方法研究[J].南京航空航天大学学报,1994,26(5):686-691.ZHONG Peiyong.A Study of design methods of rocket projected model aircraft[J].Journal of Nanjing University of Aeronautics&Astronautics,1994,26(5):686-691.
[7]裴锦华.无人机双发固体火箭助推器同步性研究[J].飞行力学,1999,17(1):21-26.PEI Jinhua.A Study of the synchronism of double solid boosting rockets applied to UAV[J].Flight dynamics,1999,17(1):21-26.
[8]EYMANN T A,MARTEL J D.Numerical investigation of launch dynamics for subscale aerial drone with Rocket Assisted Take-Off(RATO)[C]//2008 US Air Force T&E Days.Los Angeles,California,2008:1622.
[9]MARTEL J D,EYMANN T A.Numerical investigation of rail influence on initial forces and moments for subscale aerial drone with rocket Assisted Take-Off(RATO)[C]//26th AIAA Applied Aerodynamics Conference,Guidance,Navigation,and Control and Co-located Conferences.Honolulu,Hawaii,2008.
[10]许军,张军红,荣海春.小型无人机火箭助推发射动态响应研究[J].机械与电子,2018,36(1):15-17,21.XU Jun,ZHANG Junhong,RONG Haichun.Research on dynamic response of rocket booster launching for small unmanned aerial vehicle[J].Machinery&electronics,2018,36(1):15-17,21.