Abstract
The structural design of a Hybrid Multi-rotor UAV which is aimed to have both conventional take-off and landing (CTOL) and vertical take-off and landing (VTOL) capability is developed. Typical conditions of load are proposed for the static strength analysis of the full aircraft structure. Based on works above, flutter models of wing, wing - boom - tail configuration under CTOL state and VTOL state are constructed using p-k method to investigate the impact of additional vertical lift load of multi-rotor system on aeroelastic characteristics. The analysis demonstrates that the structural design of aircraft is reasonable, and fulfills the requirements of weight and strength. The multi-rotor system reduces the modal frequencies of wing, the critical flutter speed of configuration state declines by 14%. More attention should be paid to this problem when implementing the structural design of Hybrid Multi-rotor UAV.
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