Structure Design Of Tailstock Vertical Takeoff And Landing UAV

The tail-seat vertical takeoff and landing UAV has the characteristics of both multi-rotor and fixed wing,which can not only take off and land vertically,but also fly horizontally in fixed wing mode.Due to its unique take-off and landing and cruise performance,the tail-seat vertical take-off and landing UAVs are used in military activities such as military reconnaissance,positioning and calibration,communication relays,and civil fields such as power inspection,express transportation,aerial surveying and mapping Great application prospects,so it is of great significance to study this type of UAV.However,due to the lack of detailed and systematic data support,the structural design is more difficult.At the same time,the drone is susceptible to interference from ground effects during the vertical take-off and landing process,making its take-off stability poor.Aiming at the above problems and based on the structure of the flying wing aircraft,this paper has designed a tail-seat dual-engine flying wing vertical take-off and landing UAV solution with excellent aerodynamic performance,and carried out detailed and systematic design.First of all,according to the design requirements of the tail seat twin-engine flying wing vertical take-off and landing UAV,the overall plan and main parameters of the UAV were determined.Eight kinds of flying wing layouts with different torsion angles and sweep angles were designed according to the UAV flying wing layout,and the aerodynamic characteristics were analyzed by CFD method.The height-drag ratio of the flying wing layout is high and the stall performance is good.Its maximum lift-drag ratio and lift coefficient are 13.6 and 1.35,respectively.Then the vertical mode of the propeller slip flow theory is used to calculate the indefinite constant value.The results show that in the vertical mode,the force X from the lower wing surface to the upper wing surface increases with the increase of the propeller speed and vertical flight speed,but the value is small,where the ground state X is 0.64-1.43 N,In the hovering state,X is 0.65 N,that is,the vertical mode stability of the flying wing layout is good.Then based on the structural design requirements and criteria,the detailed structural design of the flying wing layout is mainly included,including the wings,lifting ailerons,fuselage,motor support and landing gear and other components.Secondly,ACP was used to design the composite material of the wing skin,and then ANSYS Workbench was used to check the strength of the wing structure,and the structure was optimized.Design scheme,the weight of this scheme is 28% lighter than the original wing structure.Finally,a technical verification machine was developed.The maximum flight speed was 130 km / h and the endurance time was 35 min.The flight test results show that the unmanned aerial vehicle structure designed in this paper can complete various flight tasks of the tail-seat UAV,and has good aerodynamic performance,thus verifying the rationality of the structure.The research results provide technical reserves and important reference significance for the further research of the tailstock vertical takeoff and landing UAV.