Planetary Reentry CanSat with Delicate Payload Protection

Designed a planetary entry probe with detachable aero-braking heat shield and dual-stage descent system to protect a delicate payload, using passive control fins for orientation stability. Created deployable aero-brake system in SolidWorks that reduced terminal velocity by 44%. Optimized probe container in Abaqus to reduce mass by 38%, enabling lighter descent and subsystem expansion. Integrated probe subsystems in SolidWorks to produce a functional assembly for PDR and CDR.