基于ADAMS的无人机零长发射动力学仿真及分析

Simulation and Analysis of UAV Zero-length Launching Dynamics Based on ADAMS

针对无人机零长发射系统研制需要,以无人机零长助推火箭发射段为主要研究对象,利用ADAMS建立了无人机发射动力学仿真模型,分别对质心偏心和助推火箭推力偏心工况进行动力学仿真,获取了发射过程中无人机质心位移和角度的变化规律,分析了无人机与发射架的安全距离。结果表明:无人机质心偏心和推力偏心影响其运动姿态,且推力偏心的影响更明显,无人机在发射过程中能够安全离开发射架。

According to the requirement of UAV zero-length launching system development, the launch section of UAV zero-length lauch- ing was taken as the main research object, and Adams was used to establish UAV launching dynamics simulation model. The dynamic sim- ulation of centroid eccentricity and the thrust eccentric condition of booster rocket was carried out, and the centroid displacement and the angle change law of UAV in launching process were obtained. And the safety distance between the UAV and launcher was analyzed. The re- sults showed thai the eentroid eccentricity and thrust eccentricity affected the motion attitude of UAV, and the influence of thrust eccentrici- ty was more obvious. The UAV could safely leave the launcher during launching.