MATLAB/SIMULINK Based Modeling, Simulation and Experimental Validation of High-Pressure Pneumatic Launcher for Fixed Wing UAVs

Fixed-wing Unmanned Aerial Vehicles (UAVs) have diverse applications across the industry. However, deployment of these UAVs, at remote locations & marine environment, is especially challenging due to requirement of paved runways. Pneumatic-based launchers provide an efficient and scalable assistive launch or deployment method in such conditions. Pneumatic launcher is a multi-domain dynamic physical system, involving: rigid dynamics, solid mechanics, pneumatics, and thermodynamic processes. Therefore, effective design and devel-opment of pneumatic launchers necessitate thorough modelling of these multi-domain processes. In this paper, MATLAB/ Simulink based model of a high-pressure pneumatic launcher for small to medium weight UAVs, is presented. The model is developed with prime considerations for scalability of design, practicality of implementation and adaptability to suit a wide range of UAVs with varying sizes, weight & take-off or launch speeds. Multiple simulations are carried out assess the influence of various design parameters. Moreover, the model is validated through multiple experimental tests on a dedicated test bench. Based on experiments, a correction factor is applied to the model to enhance its accuracy and compatibility with the experimental results. The model provides a reference for future engineering design, development, optimization, and subsequent improvement of Pneumatic launchers for UAVs.