| The folding wing structure is widely applied in the missile wing for its simple construction, little space occupation, easy to storage, transport, and launch. The main unfolding performance includes unfolding time, unfolding speed, unfolding impact, reliability of the locking mechanism and strength of the wing. These points directly affect the flight performance of the missile, so it’s necessary to analysis its structure design and unfolding performance. In this paper, a full flight simulator unfolding actuator is studied, design method is discussed, mathematic model is established, the dynamics simulation of the 3D model of the whole structure’s unfolding process and is researched, and the unfolding property is tested to verify rationality of the design and offer optimizing suggests for weak points. The main work in this research includes:(1) According to the request from overall technical indicator for the unfolding structure after summarizing the research background and development of the folding mechanism, Stern rudder folding mechanism scheme is put forward, a dynamic unfolding process is analyzed based on Newton’s law and the second Lagrange equation, the design of the structure is completed, and the structure of the driving element parameter is determined.(2) The structure of the 3d model is established. Considering the nonlinear factors in the structures such as gap, friction conditions and flexible body, virtual prototyping technology is used to get the folding mechanism of dynamics simulation performance through ADAMS software. Deployment time, angular velocity and into the impulse and the vane flake stress data is obtained, the influence of nonlinear factors in the structure of the unfolding performance is analyzed by contrast, and reasonable suggestions are put forward.(3) The static tests and unfolding performance tests of stern rudder folding mechanism are conducted to obtain the rudder surface strain, folding mechanisms on performance and the influence of impact load on the weak links, the results show that structural design is reasonable and the simulation model is accurate.(4) The basic content of aero elasticity principle is introduced, for rudder surface such as weak links, the technology of finite element strength is applied and modal is analyzed, flutter analysis is conducted on the basis of the principle of aerodynamics and aerodynamic elasticity. The strength of the vane flake is checked through NASTRAN software, and the structure size is optimized.Design scheme is put forward based on analyzing the performance of the rudder structure and technical indicators, dynamics simulation is applied considering nonlinear factors such as clearance, friction, flexible body, etc. Static tests and performance testing are applied on the structure. The content of the research can provide a reference for folding the rudder structure design and optimization. |
