Two system optimization architectures are proposed for missile system preliminary design, taking into account aerodynamics, weights and sizing, propulsion and trajectory. Approximation methods are investigated in orde...Two system optimization architectures are proposed for missile system preliminary design, taking into account aerodynamics, weights and sizing, propulsion and trajectory. Approximation methods are investigated in order to reduce problem dimensionality and to improve the efficiency of optimization process.展开更多
In modem missile design, the operation of a missile aerodynamics with angles of attack is required to serve a demand on the maneuverability. The key aero-physics is the development of vortices and its interaction to t...In modem missile design, the operation of a missile aerodynamics with angles of attack is required to serve a demand on the maneuverability. The key aero-physics is the development of vortices and its interaction to the control surface such as wing and fins. This paper thus presents the investigation of the missile flow field at 4° and 8° degrees of angles of attack. The Mach numbers for both case were varied from 0.6 to 5.5. Here, the Steady Reynolds-Averaged Navier-Stokes （SRANS） equations with standard κ-ε turbulence model were selected. The numerical results of aerodynamics coefficients （both force and moment） were compared against semi-empirical data computed using Missile DatCOM. The results revealed the development of vortices observed and their interaction with fin at the rear part of the missile.展开更多
基金Supported by National Doctoral Foundation of china (20010487024)
文摘Two system optimization architectures are proposed for missile system preliminary design, taking into account aerodynamics, weights and sizing, propulsion and trajectory. Approximation methods are investigated in order to reduce problem dimensionality and to improve the efficiency of optimization process.
文摘In modem missile design, the operation of a missile aerodynamics with angles of attack is required to serve a demand on the maneuverability. The key aero-physics is the development of vortices and its interaction to the control surface such as wing and fins. This paper thus presents the investigation of the missile flow field at 4° and 8° degrees of angles of attack. The Mach numbers for both case were varied from 0.6 to 5.5. Here, the Steady Reynolds-Averaged Navier-Stokes （SRANS） equations with standard κ-ε turbulence model were selected. The numerical results of aerodynamics coefficients （both force and moment） were compared against semi-empirical data computed using Missile DatCOM. The results revealed the development of vortices observed and their interaction with fin at the rear part of the missile.
