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Description
This work presents the design and feasibility analysis of a 24U CubeSat equipped with a hybrid rocket engine (HRE) for insertion into Mars orbit. The study evaluates the mission architecture, propulsion system and structural requirements for a successful planetary insertion. The hybrid propulsion system is selected to balance efficiency, safety, and compactness within the constraints of a CubeSat spacecraft. A successful demonstration of a CubeSat-based Mars insertion could pave the way for future cost-effective planetary missions as this kind of mission is expected to increase significantly in next few years. The propellants of choice are paraffin-based fuels that may include additives or HTPB at different percentages for performance tuning, and nitrous oxide, a self-pressurizing oxidizer commonly used in hybrid propulsion. The oxidizer over fuel by weight ratio (OF) and related performance parameters are studied using the Chemical Equilibrium with Applications (CEA) software and applied to the design of the thruster system, based on mission requirements in terms of desired delta-V and structural considerations. The system designed has four thrusters and fit the lower level of the CubeSat (2U x 2U x 3U). The geometry of the grain is studied, and initial and final port radius are calculated. An injection system is dimensioned to operate without catalytic decomposition of N2O to simplify the system and reduce weights. The upper level of the CubeSat is used to store the oxidizer with two tanks. A first design, operating at an OF ratio of 2 is proposed. The system meets the mission and structural requirements but has room for optimization. By redesigning the system with an OF ratio of 4, a more efficient HRE can be achieved. This adjustment enhances propulsion while adhering to mass and volume constraints, ensuring remaining propellant for future CubeSat maneuvers.