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. Developed nichrome wire stage separation mechanism in SolidWorks for heat shield deployment and release. Designed impact-dampening landing system that reduced landing force by 68%, ensuring delicate payload integrity. Created deployable aero-brake system in SolidWorks that reduced terminal velocity by 44%. Optimized probe container in Abaqus to reduce mass by 38%, freeing mass for other subsystems and improving descent performance.