Tailless Morphing Wing Aircraft Mechanism Design And Aerodynamic Analysis

Aircraft layout and design methods can’t meet the diverse needs of the performance of theaircraft followed with the advances in aircraft design. To improve the flight performance and increasethe flight’s envelope the aircraft designers have proposed morphing technology. Multiple variantsproject is proposed by researchers since the Second World War, and different mechanism wasproposed.The traditional control surface has low efficientl. Inorder to increase the controlling efficient ofairplane a morphing wing technology used to take the place of traditional flaps is developed accordingto the summarize of the morphing technology. The profit and feasibility is proved by analysis, themechanism can deform as respect is explored.Bernstein polynomial is used to describe the airfoil shape, XFOIL software is used to calculatethe aerodynamic characteristics of different airfoils, the genetic algorithm is the optimizationalgorithm, multidisciplinary optimization software Isight is used to transmit data between thesemodules. The shape of airfoil NACA0012is optimized based on minimum drag coefficient atdifferent lift coefficient when the Re is300000and Mach number is0.045. A set of airfoil shape,which have minimum drag coefficient at different lift coefficient, is obtained. Control efficiency of therudder is simplified as the size of the additional resistance of the rudder surface when producing thesame lift or side force. The efficient of morphing wing and the traditional flaps is compared, it isproved the drag force of morphing wing is much smaller than the traditional flaps when provide thesame lift.A variant mechanism used joint location controller and elastic deformation skin is designed. Thismechanism can control the flight attitude with a minimum drag force, and take the place of wing flapto improve the take off performance. CATIA is used to do three-dimensional modeling of thisinstitution and a variant wing single rib section of the model is created and tested; the deformation testproved that this morphing institution can meet the deformation requirements. The ultrasonic motordrive and the elastic skin are used to design a simple mechanism, which can only meet therequirement of the wing flap only. This mechanism is simple, has less actuator, structure and easy toimplement. CATIA is used to do three-dimensional modeling of this institutionAn MAV use the morphing wing to control the flight attitude is progressed. the lift and dragcharacteristics, pitching moment, rolling moment and the yaw moment of aircraft at different angle of attack, sideslip angle is analyzed. The flight is trim calculated at different speed when the aircraft inlevel flight. It is proved that the morphing wing aircraft can used taking place of rudder to controlflight attitude.The traditional flaps and slats of MAV have a complex structure and low efficiency. The MAVhave a low flight speed, small size, so the drive power requirements of morphing mechanism is smalland it is easy to achieve. It is proposed that use morphing wing technology take the place oftraditional flaps and slats in the MAV. An airfoil shape that can provide a larger lift is obtained by theoptimization algorithm; then take off flight path of different take-off method is compared between themorphing wing and the traditional wing. It is proved that the morphing wing can develop the take offperformance.It is found that morphing wing can not only reduce drag at the same lift but also have a bigaerodynamic center which can improve the static stability of pitch which is the challenge of blendedwing body when comparing aerodynamic characteristics of the traditional rudder and morphing wing.The static stability of morphing wing and traditional wing is compared, and it is proved that themorphing wing have a big benefit.