The Structure Design And Weight Optimization Of Folding Wing In Rocket Projectile

As a flying weapon, the rocket projectiles are often designed with tail wings to ensure their flight stability. In order to reduce the radial size of the rockets and improve payload ability of the weapon system, lots of missiles and rocket projectiles with folding tail are loaded in and launcher from launching container. Meanwhile, the requirements of versatility of weapon system is improved. There are many advantages by using folding wing, such as reducing the radial size of weapon, facilitating the storage, transportation and launch. In addition, more rocket projectiles could be loaded in less vehicles and ships. As a result, the combat effectiveness of weapon system is improved.Firstly, the design experience of folding wings is summarized. In this thesis, the methods of function implemention in the specific structure design are analyzed, which are used in deployable mechanism, locking mechanism and selection of power source. At the same time, reference about folding wing designing is provided to meet specific needs.Secondly, the selection of the geometric parameters is discussed when designing folding tail. The results of discussion is used in the latter design. Besides, the optimization theory and experience of the rocket’s tail are introduced.Then, for the actual project needs, the specific design of the folded tail is conducted. By analyzing the design requirements, suitable design of folding structure is achieved as well as the deployable structure and locking structure. The design scheme is proved feasible to the rocket after the analysis of opening time of foldable tail.Finally, in view of the mass of the folding wing, the thesis carried on the discussion of structure optimization. After the optimization, the mass of folding wing became less. In the optimization model, the optimization aim is smaller weight of the folding tail, while the unfolding time and the maximun deflection of folding wing are constraints. The optimization variables are root thickness, thickness variation coefficient, sweep and wingspan of movable part. The analysis of time constraint is achieved by developing the dynamical model of folding wing. Besides, the result of the approximate solution of maximum deflection is obtained by the Kantorovich methods. After the analysis, the optimization solution of the structure parameters is obtained in the feasible region.