This project aims to design a reliable solid propellant micro-rocket thrust sensor capable of detecting small amounts of thrust, less than 5 Newtons. The sensor consists of a wire foil strain gage bonded to an aluminum beam, with the rocket attached to the beam end, nozzle facing up. The strain gage leads are connected to a Wheatstone Bridge, which is fed into an operational amplifier to amplify the analog signal. The amplified signal is sent to a data acquisition system that records real time voltage data from the strain gage while the rocket is firing. Using a mass calibration graph and voltage graph with respect to time, the rocket's thrust, impulse, and specific impulse can be calculated

Rocket mounted to aluminum beam, before ignition

End burning rockets, the one on the right has a core dug out. The solid propellant is AP (ammonium perchlorate) and HTPB (hydroxyl terminated polybutadiene)