Design Of Solar/Hydrogen Hybrid Powered Small-scale UAV And Research On Key Techniques

According to the long-endurance demand of small low-altitude electric UAVs, a configuration design of small low-altitude UAV with hybrid solar and hydrogen energy system is introduced. Considering the coupling relationship between weight and energy in the design process, a conceptual parameters design method which is based on power matching, weight balancing and energy balancing is proposed. In this thesis, the research on solar/hydrogen hybrid powered UAV is made by the following aspects.(1) Conceptual design method of hybrid powered UAVsAccording to the particularity in the design process of hybrid powered UAVs, a preliminary parameter design method which considers the coupling relationship of weight and energy is proposed. After establishing the model of aerodynamic, weight and energy, the equilibrium equation based on power matching, weight balancing and energy balancing is got. Finally the hybrid powered UAV preliminary parameter design is completed by solving the equations using iteration method.(2) Influence degrees of design parametersThrough the preliminary parameter design method for hybrid powered UAVs, influence degrees of design parameters on solar powered, fuel cell powered and hybrid powered UAVs are analyzed, which results in the range of application of solar/hydrogen hybrid powered UAVs. Besides, the influence of energy system on UAV is also analyzed, which offers references for the design process in the subsequent sections.(3) Synthesis design of the hybrid powered UAVOn the foundation of preliminary parameter design method, the conceptual design, preliminary design and detailed design of the hybrid powered UAV are completed in turn. Faced with the problem of relatively low power support of the UAV, measures are taken to improve the aerodynamic efficiency in the detailed design process, such as choosing a better airfoil and refining the wing's planform and twist.(4) Analysis of aerodynamic characteristicsTo verify the feasibility of the configuration of hybrid powered UAV, the stability and turn radius are analyzed, and the simulated test is completed by using the autopilot system. Finally, the UAV's flight performance is tested and verified.