Analysis and design of a fixed wing unmanned aerial vehicle gas launching system

Abstract

In order to meet the development requirements of unmanned aerial vehicle (UAV) boosters, a detachable launch booster for fixed wing UAVs was designed, which is driven by high-pressure carbon dioxide gas. A mathematical model for gas launch was established based on the internal ballistic equation of the gas cannon. Through theoretical calculations and the use of dynamic simulation software ADAMS to simulate the designed 3D model, the variation laws of initial velocity, overload, displacement, etc. during the launch of unmanned aerial vehicles of different masses were obtained. The results show that the initial velocity, displacement, and overload variation curves obtained through simulation when the drone leaves the launch pad are highly consistent with the theoretical calculation results, verifying the correctness of the calculation and simulation. The research results indicate that the fixed wing unmanned aerial vehicle (UAV) booster launcher can successfully launch UAVs weighing 14 kg or less and achieve initial takeoff speed without exceeding maximum overload. The simulation results have an error of no more than 3% compared to theoretical calculations. The research results can further provide theoretical guidance for gas emission.

Keywords

• uav|launch frame|gas emission|structural design|dynamics simulation