Co-simulation Analysis Of Stage Separation Of Missile Based On FLUENT And ADAMS

Missile is an attractor in the guided weapons, it reflects development level ofcontemporary science and technology, represents the progress of space flight andaviation industry, and also embodies the national comprehensive national power. It is abig problem to improve accuracy for missile attacking target, and it costs quite muchto prove the accuracy by experiment, so we must carry on the reform of traditionalmethod. The paper takes missile separation technology as research object, separationdynamics and aerodynamic characteristics for the separating of missile are analyzedtheoretically, this article uses virtual technology and computational fluid dynamics tothe joint simulation of missile separation, fully taken into account the couplinginfluence of the space motion and the aerodynamic drag.Firstly, we have a brief introduction on the research background of this paper, andalso make a conclusion on domestic and international development of the missileseparation technology, computational fluid dynamics and virtual technology.Secondly, we have a theoretical analysis on dynamics and aerodynamiccharacteristics of missile in the separation process. The article makes use of Lagrangeequation to establish the dynamic model of missile separation, and related formulas areintroduced. We utilize the basic governing equations and dynamic grid control equationwith computational fluid dynamics to establish the aerodynamic analysis model ofmissile separation, and also make theoretical analysis on discretization algorithm,SIMPLE algorithm, turbulence model and the moving mesh parameter settings in theaerodynamic analysis process.Then, the main module, simulation process and integration of ADAMS aredescribed. According to has established dynamic model, dynamic simulation of missileseparation using ADAMS is presented. Kinetic simulation results show that missileseparation time is short; In the effect of engine thrust, warhead accelerate flight with aconstant acceleration; Due to the function of the engine wake, booster do slow down aflight.Finally, make a brief introduction to software structure, process of numericalsimulation and application rang of FLUENT. Taking the coupling effect of space motionand aerodynamic drag into consideration, make a co-simulation study on missileseparation with FLUENT and ADAMS. Flow field simulation results show that shockwave is formed in the front of warhead and booster; Flow field pressure and temperatureare highest around the front of two-body, backward along the axial direction,temperature and pressure decreased; Wake flow is forming in the back of missile body,vortex exists in the region, fluid velocity and pressure are small, temperature is high. Kinetic simulation results show that the speed of war and booster is reduced in the roleof the aerodynamic, booster is greater than warhead in the loss of speed. However, theimpact of the separation process is less than the experimental error requirements.