Research On Simulation System Of Distributed Driven Morphing Aircraft Control

Morphing aircraft can change the shapes adaptively according to mission and flight environment,in order to make it in the optimal aerodynamic condition all the time to achieve the flightperformances of all-weather and large flight envelope.Nowadays morphing aircraft has become a newsubject of countries, which draws more and more attention. Western developed countries have carriedout relevant researches in this area. Meanwhile, China has embarked on research on morphing aircraftby the National Natural Science Foundation and many other projects for funding.As the research on controlling of morphing aircraft is still in the stage of numerical simulation,building the semi-physical simulation system of morphing aircraft exerts an important significance onthe morphing aircraft field.This paper focuses on the research of the hardware and software ofmorphing aircraft’s simulation system and building the flight control simulation module. Thethorough structure design of simulation system is introduced at first. The hardware module of themorphing wing with20intelligent units which is connected by CAN-bus is built up and has realizedthe shape change of wing chord and span wise. Intelligent unit using ARM microprocessor ascontroller, servo motor as actuator and sensor, CAN-bus as communication system is established.Secondly, thorough design is made for the software of the host computer, and the functions of eachsub-module are being studied and designed in details. The software module of host computer is thecore of the simulation system of morphing aircraft control, including the airfoil selection modulewhich can select the airfoil automatically by integrate the flight environment, the database modulewhich can query the aerodynamic parameters according to flight environment and airfoil, thereal-time airfoil display module which display the three-dimensional airfoil in real-time.The softwarealso connect the host computer with the CAN-bus and the simulation system of flight control. Last butnot least, a six degrees of freedom model of aircraft with varing-parameters is built in MATLAB, anda simple flight control law is designed to realize the stability of the morphing aircraft before morphing,in morphing and after morphing. The results show that the transition control law with dilute part canmaintain the stability of the aircraft during morphing, and the whole simulation system runs well.