Numerical Simulation And Study On Large Fineness Ratio Rockets’ Flexible Deformation And Aerodynamic Characteristics

In order to meet the requirements of high speed, high maneuverability, high accuracy and long-range strike of the modern warfare, the fineness ratio of the rockets is becoming larger and larger. However, with the increase of the rockets’fineness ratio, the variation of the flow field of the rockets’surface and the rockets’aerodynamic configuration have been redistributed, which lead to the rockets’flexure strength and the natural frequency of lateral bending vibration reduced. The lateral bending vibration will be happened in the process of rockets’launch and flight, which is mean flexible deformation happened, that changes the rockets’flight attitude, affects its maneuverability and reduces the accuracy of its remote attack.In order to study rockets’aerodynamic characteristics and flexible deformation, we must combine with the rockets’aerodynamic characteristics and flexible deformation which can study the large fineness ratio guided rockets better.Firstly, in this paper, numerical method has been used to calculate the rockets, set up the different fineness ratio rocket models to study the variation of the different fineness ratio rockets’aerodynamic characteristics which under different attack angle and different Mach numbers, and verify the correctness of the results by the wind tunnel.Then the rocket models when occur the flexible deformation during the different vibration models has been set up to study the influence of rockets’aerodynamic characteristics when the flexible deformation occurred, get the variation of deformed rockets’ lift coefficient, drag coefficient and pitch moment coefficient under different attack angle and Mach numbers. Contrast and analyze the rockets’static stability between the different vibration models and rigid models, get the relationship of rockets’flight stability and flexible deformation.Finally, the numerical method of Fluid-Structure interaction (FSI) has been used to analysis the rockets that during the free flight with the different Mach number and different attack angle, get the large fineness ratio rockets’variation of flexible deformation, size of the deformation and stress distribution during the free flight.The calculation result show that the numerical calculation result of the variation of large fineness ratio rockets’aerodynamic characteristics accord with the variation of convention rockets’aerodynamic characteristics, the numerical calculation result with FSI of rockets’ flexible deformation and stress distribution also accord with the rockets’first-order vibration mode. The work done in this thesis can provide the related references to the design and research of the large fineness ratio rockets.