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The system was validated during a static test of the T-300 solid
rocket engine using cold-pressed KNSU propellant.
Peak thrust: ~240 N
Peak chamber pressure: ~16 bar
Outer temperature: ~50 °C
Strong correlation between thrust and pressure confirmed
system reliability.
The GUI displayed real-time measurements, ensuring safe, remote
control of ignition and data acquisition.
The system integrates sensors and microcontrollers through
modular subsystems:
DAQ-Tx Module (Arduino Mega): acquires data from sensors
(load cell, thermocouples, pressure transducer).
DAQ-Rx Module (Arduino Uno): receives and sends data to a
Python GUI via USB.
PPS Module: powers electronics and ignition system.
Each sensor was calibrated to ensure reliable measurements.
The load cell was calibrated using a spring-based method, relating
controlled spring deformations to the sensor output, allowing
accurate conversion of readings into thrust values.
INTRODUCTION
COBEM 2025
9th - 14th November 2025
CURITIBA | PR | BRAZIL
28th International Congress of Mechanical
Engineering
Solid rocket motor characterization requires accurate
measurement of thrust, pressure, and temperature to validate
performance and safety.
To address the lack of low-cost, reliable systems for academic
rocketry, a wireless data acquisition and transmission system was
developed at UFSM’s Propulsion and Performance Studies Group
(GEPROP).
The system enables real-time monitoring of tests from a safe
distance, ensuring both data integrity and operator safety.
Carlos Roberto Bearzi¹, Andrew Santos Machado,Cesar Addis Valverde Salvador, Marcelo Serrano Zanetti, Miguel Daehn Ribeiro, Ilzy Lima
Vieira, Luana Dalla Vecchia de Lima, Thiago Chagas
¹Federal University of Santa Maria (UFSM), Santa Maria, RS, Brazil, carlos.bearzi@acad.ufsm.br
Development of a Data Acquisition and Transmission System for
Characterizing a University Rocket Engine
METHODOLOGY
RESULTS AND DISCUSSION
CONCLUSIONS
The low-cost, modular system proved to be efficient and robust for
real-time monitoring of rocket engine tests, with the collected data
showing strong correlation with theoretical expectations. Its design
offers a safe and scalable platform for academic propulsion
experiments, supporting ongoing research on cold-pressed solid
propellants at UFSM and contributing to the advancement of
experimental rocketry within the university.
REFERENCES
1.Nakka, R. (2003). Amateur Experimental Solid Propellants.
2.Santivanez et al. (2021). Design of low-cost solid propellant
engine test bench. ICECCME.
3.USINAINFO (2024). Electronic components supplier.
Figure 1. Diagram showing how the system works.
 
Figure 2. DAQ-Tx
Module.
 
Figure 3. DAQ-Rx
Module.
 
Figure 4. PPS Module.
 
Figure 5. Measured Thrust.
 
Figure 6. Measured Pressure.
 
Figure 7. Measured Temperature.