Design And Analysis Of Ejection Mechanism Of Missile Wing With High Dynamic Pressure And High Stiffness

To improve the boom load of the missile launch platform and emission efficiency,will usually wing designed to fold,in the form of existing can curl wing generally USES the rotation of the form,the radius is big,wing surface aerodynamic instability,the process wing unfolds locking sti ffness is low,compared with the rotary wing,straight acting out in wing wing wing surface in the process of aerodynamic force is stable,When not deployed,the missile wing is completely stored in the interior of the missile body.After being deployed,th e missile wing is pushed out in a straight line with a large storage ratio.Based on the type of moving of the performance advantage on wing,the paper developed a wing launch institutions,large dynamic pressure high stiffness after the quick launch wing t o wing for reliable locking,and launch various institutions internal implant anti-backlash eliminate wing kinematic pair clearance,increase the support stiffness and stability of the wing,and developing principle prototype test of its performance.Of winged missile of thorough investigation and summarizing the research status at home and abroad,put forward the feasible design scheme,the performance characteristics of each scheme comparison,select the best design scheme of each part of wing launch mechanism components for design and structure,and completed the wing launch key structure parameters.The dynamic parameters of the ejector mechanism were solved to verify its functional indexes,and the stress analysis of the ejector mechanism under static load was carried out to analyze the internal and external force relations among its components.The impact characteristics and anti-backlash characteristics of the ejector mechanism are studied.The instantaneous impact force and its influence on the structure are analyzed.The impact force at the hinge clearance and its influence on the motion state of the ejector wing are analyzed.The static stiffness of the ejector mechanism under clearance condition is analyzed and its deformation is analyzed.Based on fractal geometry knowledge and contact stress theory,dynamic stiffness modeling and analysis were carried out on the ejection mechanism of the missile wing under the condition of anti-backlash,the relationship between locking force and support stiffness was studied,the function of anti-backlash component was verified,and the driving performance of shape memory alloy was calculated.The dynamic simulation of the pull-out mechanism was carried out to obtain the motion response of the pull-out mechanism during the action process,and the functional characteristics of the pull-out mechanism were analyzed by comparing with the theoretical analysis results.Static simulation analysis was carried out to obtain the force and deformation of the pushout mechanism unde r static load.The air flow field of the wing is simulated and the relationship between the aerodynamic load on the wing surface and the flight Angle of attack is obtained.Modal analysis,harmonic response analysis and random vibration analysis were carried out to verify the stiffness characteristics of the pushout mechanism.The prototype of the ejector mechanism was completed.According to the input load characteristics,the tooling system to simulate the resistance load was designed,and the ejector mechan ism’s ejector function was tested.Through the basic frequency test,the dynamic stiffness of the mechanism after the launch of the missile wing is tested,and the function of the anti-backlash component is verified.