Research On Aerodynamic Characteristics Of High Speed Rocket

In order to meet the needs of modern war,rocket weapons tend to develop with high speed.Taking a high-speed rocket with large fineness ratio as the research object.Fluent is used to simulate the flow field of the rocket without rotation and rotation,and the aerodynamic parameters and rolling aerodynamic parameters are obtained.Then the twoway coupling method is used to simulate the aero-elasticity of the wing,and the change of wing deformation with time and the influence on aerodynamic parameters after deformation are obtained.The specific work is as follows:Numerical simulation of four piece tail model projectile,and the obtained aerodynamic parameters are compared with the test results and simulation results in the literature.The results show that the error between the simulation results and the test results is within the allowable range,which verifies the feasibility of the numerical method.The same numerical method is used to calculate the external flow field of the large aspect ratio rocket without rotation.The aerodynamic parameters of the rockets with different Mach numbers,different angles of attack and different angles of inclination of the wing are obtained.The results show that the lift coefficient of the rocket increases first and then decreases with the increase of Ma,and increases with the increase of the angle of attack.The change of the angle of the wing has no obvious influence on the lift coefficient.In order to study the rolling aerodynamic characteristics of the rocket,the multireference system model is used to simulate the steady rotation of the rocket.The effects of the incoming Mach number,the incoming angle of attack and the angle of inclination of the wing on the equilibrium speed of the rocket and the derivative of the rolling damping torque are analyzed.The results show that the equilibrium speed of the rocket increases with the increase of Ma,the angle of attack and the angle of inclination of the wing.The absolute value of the derivative of the rolling damping torque increases with Ma.The increase first increases and then decreases,and increases with the increase of the angle of attack and the angle of inclination of the wing.Based on the ANSYS Workbench platform,the two-way coupling and spring smoothing method are used to simulate the aero-elasticity of the wings under different Ma,different angle of attack and different angle of inclination of the wings.The results show that the deformation form of the wing mainly shows bending deformation,the deformation changes periodically and gradually converges,and the maximum deformation occurs at the wing tip;the larger the Mach number and the angle of attack,the larger the deformation of the wing;the deformation of the wings on both sides is opposite to the angle of inclination of the wings.The stress generated when the wing is deformed is mainly concentrated on the mounting feet;the maximum stress generated by the deformation of the wing increases with the increase of the Mach number,the angle of attack and the oblique angle.The greater the deformation of the wing,the greater the stress generated at the corners of the wing.The lift provided by the deformation of the wings is somewhat reduced.