CanSat descent control system design and implementation

Abstract

The aim of this study is to design a descent control system for a CanSat that simulates a sensor payload travelling through a Martian atmosphere and sampling the atmospheric composition during flight. CanSat is a first step in space studies that gives low cost opportunity to test the space program design. The system is developed under the rules of International CanSat Competition 2016, which aims to simulate the Mars glider project of NASA. A novel descent control system approach was designed and implemented with cadets according to the requirements of the competition.