| The future battlefield environment is so bad that it is difficult to meet the war requirements for single guided bomb's the limited amount of information. Precision guided bombs will inevitably face serious challenges. Single-mode dual-mode guidance technology is moving to the direction of multi-mode guidance. Aircraft aerodynamics computation is a key method to the aircraft design, and the operation stability characteristics of aircraft can be quickly obtained in preliminary aircraft design stage. With the high speed development of computer technology and computational fluid dynamics (CFD), and continuous improvement of simulation accuracy; aerodynamic characteristics of aircraft will be quickly and easily realized the aerodynamics parameters are obtained to modify design and replenish wind tunnel tests. Using numerical simulation of complex flow field can reduce cost, long cycle and high-risk defects of wind tunnel test and flight experiment and effectively a "digital wind tunnel" effect.In this thesis, the flow mathematical and physical model for two guided bomb are founded based on three-dimensional Navier-Stokes equation. Finite volume method is used to discrete the flow equations. Numerical calculation method are performed to simulate bomb's flow field, and the wind tunnel test data are compared with the numerical results to verify the validity and reliability of numerical methods. Numerical simulation for this dual-mode guided bomb's flow field in different angles of attack (α=-4°,-2°,0°,2°,4°,6°,8°,10°,12°,14°) and the variable flow speeds (Ma=0.6,0.8,0.9) and different rotation rudder angles (δ=0°,-5°,-10°,-15°). The main aerodynamic parameters are obtained and lift and drag characteristics and static stability of guided bomb are analyzed in detail. It will provide some technical support for the next stage of engineering design. |
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