Modeling And Sensitivity Analysis Of Movement Function Reliability Of Deployable Mechanism Of Folded Wings

As an important component of missiles,deployable mechanism of folding wing is widely used in modern missiles.Its reliability directly determines the success of the whole launching task or not.On the basis of current research situation related to deployable mechanism of folding wing,this paper aims to study its reliability of movement function and the sensitivity analysis model is obtained by doing so.Methods employed are primarily concerned with theoretical solving as well as simulation solving,which are verified each other.The sensitivity values of greater key parameters that affect the reliability of deployable mechanism of folding wing can be acquired by adopting the ways mentioned above.A comprehensive analysis of the key parameters is conducted under the influence of deployable mechanism of folding wing,which provides for guidance value for engineering practice and the design of missile folding-wing deployment mechanism.Firstly,in addition to exploring the research status,methods and development trends,the main types of folding wing deployment mechanism both at home and abroad are reviewed respectively according to the driving force and the folding mode.Based on the analytical results produced,the problems existing in reliability sensitivity solving,such as low accuracy and little deep research on the solution of the "one-shaped" deployable mechanism of folding wing,are summarized,laying the foundation for the study of "one-shaped" deployable mechanism of folding wing.Secondly,This paper deals with the simplification of the "one-shaped" deployable mechanism of folding wing,and the limit state equation and reliability sensitivity are obtained by respectively establishing the model in startup stage,unfolding stage and locking stage of the deployable mechanism of folding wing.Reliability Sensitivity Expression of Key Parameters can be obtained by taking partial derivation of the limit equation.By using the AFSOM method,the reliability of the folding wing deployment mechanism and the sensitivity of the related parameters are solved.The hinge length and rod length parameters are analyzed by the "effective rod length theory".AFSOM is used to solve the reliability and sensitivity of the deployment phase.The lock phase is regarded as a cantilever deformation.Then the reliability and key parameters of sensitivity in the lock phase can be solved by AFSOM method.Thirdly,the paper aims to establish parametric model in ADAMS of the folding-wing unfolded structure and output a response.On the basis of considering the peak of driving force,hinge clearance and dimension error,the reliability of folding wing deployment mechanism and related parameter sensitivity value is achieved by parameter distribution of ADAMS/Insight.Sensitivity data is compared with the theoretical value to verify correctness.GUI is developed in MATLAB and calculation program of reliability of deployable mechanism of folding wing was written.Finally,the key parameters such as wing length,putter length and driving force,which affect the reliability of the deployable mechanism of folding wing,were analyzed separately to get their influence law.By fitting the data in ADAMS/Insight through MATLAB data,we get the comprehensive influence law of stretching angle under two parameters.