Abstract
Traditional tilt rotor aircraft rely on turning the whole engine nacelle, to accomplish the transformation between vertical take-off and landing as well as flying. This scheme has a large rotational inertia and requires a heavy and complex tilting mechanism. the engine jet flow in the process of vertical take-off and landing directly spray down, and this flow could blow up the sand and stone, let engine suck it in or hurt people. So this paper designed a new rotated way based on variable shaft Angle gear transmission. The carrier aircraft design scheme referenced the data come from following software and website. The data of airfoils come from the software profili and the website Airfoil Investigation Database. The pressure distribution as well as air flow simulation and calculation is based on XFLR5. The mechanical, appearance and overall design is based on CATIA. The gear contour design is based on CAXA CAD and the full-aircraft aerodynamic simulation is based on ANSYS/FLUENT. The engine with this design is fixed, so it only needs rotate the tilting rotor shaft, and the mechanical structure is relatively simple, which make this aircraft can play an important role in the future logistics and transportation system.
Highlights
With the progress of electronic technology and aviation theory, Industrial UAVs began to show a blowout development, the function of UAVs from folk entertainment and military spy to integrated with aerial photography, aerial surveying, short-distance delivery, reconnaissance and strike, it's becoming mature
2.1 The design of wing, aileron and wing flap. Because of this UAV's design concept is low speed, branch line, normal configuration propeller cargo transport plane, the aerofoil selected from NACA's digit Number aerofoil, CLARK and GA-2 aerofoil(family of aerofoil), we analyzed various data of CLARK X, CLARK V, CLARK Z, CLARK-Y 11.7 %smoothed, CLARK W, CLARK K, CLARK Y, NACA 4415, NACA 6412, NACA 4418, NACA 4421, NACA CYH, CLARK YM-15 and NASA/LANGLEY LS(1)-0413 (GA(W)-2)[2]
In consider of machining difficulty, wing lift-drag ratio[3] and structural safety, preliminary define the wing taper ratio of main wing is 1, The ratio of exposed wing's wingspan and wing chord is 6 and the wing planform is straight wing or forward-swept wing, In order to determine which wing planform suit the tilting rotor cargo UAV batter, we did some aerodynamic analysis based on XFLR5, used vortex lattice method to analyzed the aerodynamic characteristic of this two wing planform, first, The dynamic viscosity of air μ is calculated by using satland's formula: μ μ0
Summary
With the progress of electronic technology and aviation theory, Industrial UAVs began to show a blowout development, the function of UAVs from folk entertainment and military spy to integrated with aerial photography, aerial surveying, short-distance delivery, reconnaissance and strike, it's becoming mature. Manned cargo planes and trucks are still the main force in the field of medium-distance express transportation. the technology of flight control and UAV remote control is becoming more and more mature, and the technology of tilt rotor is becoming more and more perfect,This makes it possible to design the tilting rotor cargo UAV. It could use smaller venues like parking lot or small squares to land and take off like a helicopter, due to it's fixed-wing flying mode,it could load more weight and fly longer distance than a helicopter. The aviation community expects the tilt-rotor aircraft to be the main aircraft for the 20 years[1]
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