ABSTRACT
The mission detailed in this chapter intends to perform a soft landing on the object, collecting some sample material, and safely return it back to Earth for further scientific studies. This chapter highlights the dynamics of reentry module using 3-degree-of-freedom code and structure analysis using Abaqus 6.13, which is a commercial finite element method-based software. The major loads acting in the reentry module are the inertia loads due to acceleration, drag during reentry, and internal pressure in propellant tanks. The maximum longitudinal (axial) deceleration expected is 13 g and the maximum drag expected is 40 kN. Therefore, we have constraints on maximum “g” level, which is governed by initial flight path angle and entry velocity of the module. An optimal flight path angle has to be chosen for obtaining the “g” level within the limits. Loads obtained from the trajectory of reentry module give input to perform structural analysis. The major constraint in this aspect is maximum allowable stress, thickness 82of the shell, and thickness of thin sheet used for partition of propellant tanks. Therefore, an optimal solution has to be carried out for meeting all constraints.
