Design And Working Reliability Simulation Research On Deployable Mechanism Of Twice Folding Wing

As an important part of missile body, folding wing is folded during storage, transportation and launch phase of a missile. After the missile is launched out of the canister launcher, folding wing will be deployed and locked by deployable mechanism, providing aerodynamic force for missile flight. Now, researches on folding wing deployable mechanism are all about single folding wing, when the wing span is larger, many times folding wing are required to satisfy the constraint requirement of the canister launcher. So, to develop related technology researches on deployable mechanism of twice folding wing will be of great importance.A new kind of deployable mechanism of twice folding wing is proposed in this paper. Configuration synthesis and mechanics property analysis are performed, reliability simulation is studied, test device is designed and experiment by using the prototype is conducted, as follows:1. According to graph theory, configuration synthesis of deployable mechanism of twice folding is analyzed, configuration optimization is carried out based on function demand and actual design requirements, and the final configuration scheme is determined. Rationality of the chosen configuration is verified by configuration transformation.2. Taking the minimal pressure angle, the minimal overall radius dimension and the maximal radius dimension of missile body as optimization objectives, sizing optimization design is performed. Key components of deployable mechanism are chosen and designed to complete the overall structure of twice folding wing. Dynamic theory model including driving force, aerodynamic force, gravity, friction of kinematic pairs and impact force is setup based on the Lagrange’s equations of second kind, changing rules of the motion parameters and the impact force are determined. Dynamics simulation calculation is finished by using Pro/E-Adams co-simulation to verify that the mechanism design can meet the design requirements.3. Based on Adams simulation platform, parameterization of the virtual prototype is finished. Given an overall consideration about random factors including dimension error of moving members, clearance of kinematic pair and the peak value of driving force, reliability simulation experiment is conducted by using Adams/Insight, reliabilities of deployment angle, deployment time and impact force are computed by Matlab, and then the working reliability of twice folding wing deployable mechanism system are obtained.4. Ground test device of twice folding wing deployable mechanism is established, function verification experiment is performed to get the test result. Dynamics simulation of the virtual prototype under the same conditions with the test device is carried out to get the simulation result. Comparing the test result with the simulation one to verify the validity of test device of twice folding wing deployable mechanism.