Modeling of a Forced-Thrust Spacecraft in Re-Entry Phase with 6-DOF ModelConsideration

Modeling of a Forced-Thrust Spacecraft in Re-Entry Phase with 6-DOF ModelConsideration

The key parameters for re-entry spacecraft are velocity and acceleration in the re-entry phase. The system requirements such as aerothermal, health of man and other factors limit velocity and acceleration in the re-entry phase. In this article, a forced-thrust spacecraft is designed and modeled for achieving of the appropriate parameters. Indeed in this paper, it has been tried to design and model the path of a forced-thrust spacecraft in the re-entry phase. The followings have been done, respectively. With considering a 6-DOF projectile which has a forcedthrust for velocity reduction, the environmental conditions are modeled. After calculating aerodynamic coefficients using MISSILE DATCOM the re-entry model of forced-thrust spacecraft is completed by combination of aerodynamic equations and dynamic equations of rigid body motion with effect of forced-thrust.