助推火箭安装偏差对小型无人机发射安全的影响

Effects of a booster rocket installation deviation on the launch safety of a small unmanned aerial vehicle

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.