Co-simulation method of pneumatic UAV launching device based on Adams-Hypneu

Abstract

The purpose of this paper is to use the co-simulation method to predict the velocity of the dummy during the launching process. Taking the PL-40 launching device of ELI Company as the research target, Adams is used to establish the mechanism model, and Hypneu establishes the pneumatic model. At the launching conditions of the 10 kg dummy and 10 bar tank pressure, the preliminary co-simulation result is compared with the launching test, and the velocity error is −3.7%. The frictional force is not a constant and depends strongly on the shuttle’s pull force during the launching process. The results are coincident with the shuttle’s kinetics equations and co-simulation results. The frictional forces between wheels and rail significantly affect the dummy’s velocity of launch devices (LDs). The effect of drag force on dummy velocity is 0.4% for the LD during launching. While the co-simulation results are compared with the reference of all conditions, and the maximum launching velocity error is −3.8%.