Lognitudinal Aerodynamic Configure And Control System Optimize Design Research For UAV

As compared to manned aircraft , unmanned aerial vehicle has some unique advantages, from the beginning of this century, the development of UAVs has been greatly accelerated. UAV flying qualities can reflect the degree of difficulty to complete the missions, with good flying qualities is a base to ensure the UAV flight safety and complete the mission successfully. However, flying qualities standards and criteria are currently deficient for UAVs and rely heavily on manned air vehicle standards and guidance, which can not meet the need of the current development of UAV. UAV specific missions, tasking, and payload requirements warrant development of new standards and criteria.Dynamic model and aerodynamic parameters are the basis for UAV flying qualities analysising, CFD simulation is a important means to calculate the aerodynamic characteristics of airfoil, wing and so on. The research of UAV requires a method with short cycle and lower costs, but the traditional overall optimize way needs a large number of money and time,it's not suitable for UAV.In this paper,along with the theme of control system and aerodynamic layout optimize design in longitudinal channel,carried out the work as follows:(1) Departure from Newtonian mechanics, established a dynamic model of six degrees of freedom for UAV. Through the small perturbation linearization and decoupling, the vertical equation of motion is derived.(2) By CFD numerical simulation,got the aerodynamic characteristics and aerodynamic derivatives of the wing and the horizontal stabilizer about a UAV.(3) Elaborated the concept of stability, researched the method to evaluate flying qualities of UAV, studied the method of analysising long-period, short-period modal in the longitudinal plane of UAV, designed a control law for pitch channel.(4) Under some reasonable assumptions, advanced a method for control and aerodynamic layout optimization based on the constraint of flying quality . Adanced a multi-objective optimization method to make the drag and structure mass minimum of horizontal tail based the precondition of meeting the first level flying qualities. Finally, a UAV was optimized, proveing that the method was able to optimize the results.