Traditional rocket engines use liquid propellants and have stayed conservative for some time. However, new hybrid rocket engines have been making more advancements, considering they have more advantages than liquid rocket engines. With the ability to mix between liquid, solid, and gas propellants, they can achieve higher thrust and efficiency. Getting inspiration from Stanford’s Advanced Rocket Propulsion class, our team set goals to build a hybrid rocket engine that can achieve higher thrust for a longer duration.

Purpose:
To design and build a hybrid rocket engine, using a mix of solid with liquid or gas propellant.
Objective:
To achieve 1000 lbs of thrust for a burn time of 20 seconds.
To choose types of propellant.
Research on the correct mixing ratio that will deliver the required thrust.
Design combustion chamber with nozzle to withstand forces to a safety factor of 2.5 with the available budget.
Design stand that can house the rocket engine and the propellant tanks.
Design thrust measuring system.
Run thermal and flow simulations to accurately get temperature values.