Elastic Dynamics Analysis And Control Design For Morphing-wing Missiles

Morphing-wing missile can adjust the wing shape to fit different flight environment and different mission,and plays an important role in modern war which has the feature of large velocity envelop,informatization and intelligent.This dissertation choses morphing-wing cruise missile as study object and tries to carry out study on modeling and optimization of aerodynamic and structure,uncertainty analysis,sensitive analysis and morphing control.First,in terms of the requirement of a high lift-to-drag ratio while cruising,the research on wing optimization is carried out,which designs the wing shape with minimum induced drag subject to the required lift ratio.To deduce the wing optimization method,the chord wise circulation distribution is preset,and vortex lattice method and Lagrangian multiplier are applied.The result shows that the wing optimization can reduce the induced drag effectively.Second,considering the aerodynamic load changes because of the wing morphing,the structure design is carried out on wing box which modeled as cantilever beam.Optimality criteria based approach is developed to design the stiffness distribution for achieving minimum wing weight subject to the displacement constraints.The result shows wing structure needs more stiffness in low Mach number with the same lift but different shape.Third,in the condition of given the uncertainties of the inputs such as velocity,temperature and material properties,uncertainty and sensitivity analysis for twist wing are implemented to make the design robust.To solve the problem that generating sample spends too much time,Gaussian process regression is applied to establish emulator.Than uncertainty and sensitivity analysis is carried out with Monte Carlo method and variance decomposition.The result shows the temperature is the most effect element.Finally,based on the aerodynamic and structure optimization,the research on wing morphing control is carried out.To compare wing shapes in different flight environment,the deformation of camber and twist can be obtained.The camber changes by controlling the rudder on leading edge and rear edge,and the rudder instruction generated with linear approximation method.The moveable wing box is adopted,and the rule of twist center and stiffness along with controlling spar changing is analyzed,than a twist control approach is developed.The research of this dissertation has important reference for further engineering design.