| Tilt-rotor aircraft have the advantages of vertical take-off or landing and the high speed in forward flight, but the existing tilt-rotor aircraft adopt the way of rotating the rotor on the wings tip to realize the flight mode transformation from hover state to forward flight state, this kind of layout have poor stability of force and moment, result high technical difficulty of problems and high risk. Linking up the quadrotor aircraft which has excellent stability in the hover state and small speed forward flight state and the fixed wing which has high-speed forward flight performance, design a tilt-quadrotor with new configuration. Analyze the aerodynamic characteristics and get the law of the aerodynamic interference by the numerical calculation method based on CFD.Firstly, design a tilt-quadrotor with new configuration. The aircraft install four rotor in the fuselage and wing tip before and after, and the transition process is step by step, so as to realize the stable transition of flight mode and effectively reduce the tilt rotor aircraft technical difficulties.Complete the three-dimensional geometric model of tilt-quadrotor with new configuration.Secondly, for the aerodynamic characteristics of the aircraft, establish a set of numerical calculation method based on CFD, the rotor stimulation adopt MRF, compared the test value and the numerical value, the value include the tension and the power of isolated rotor in hover state, verified the validity of the numerical calculation method.Then by this method, stimulate and analyze detailedly the aerodynamic characteristics of the tilt-quadrotor. The main content is the aerodynamic interference of rotor/wing/fuselage/tail in vertical flight, in forward flight state and the transition process.Finally get general law of the aerodynamic interference of the rotor fuselage/wings/tail under different state, for the design and application of the tilt-quadrotor aircraft with new configuration laid a theoretical foundation. |
PDF Full Text Request