Determination of Heat Fluxes for Fairing Separation of Launch Vehicle

The payload fairing is one of the most important parts of the satellite launch vehicle. It protects the satellite from severe undesired effects. Payload faring is jettisoned when it is no more required. The aerodynamic thermal flux upon fairing jettison is not greater than 1,135 W/m². The value of heat flux can be calculated from different schemes like Direct Simulation Monte Carlo(DSMC), CFD and Navier Stokes Equation. In this paper the heat flux for fairing separation phenomenon is estimated using DSMC technique. A comparison of this estimated value with different techniques is being provided. The effects of analytical and computational heat flux schemes on payload fairing separation phenomena and payload capability of launch vehicle are also analyzed and discussed.