Instrumentation of Hybrid Rocket Motor Test Bed
Although propulsion is a mature subject, one technique has recently sparked a lot of research and development since it provides a safer and less expensive way of propulsion. It's known as rocket technology, and it's revolutionized the space business during the previous two decades. This study looks
2025-06-28 16:27:50 - Adil Khan
Instrumentation of Hybrid Rocket Motor Test Bed
Project Area of Specialization Software EngineeringProject SummaryAlthough propulsion is a mature subject, one technique has recently sparked a lot of research and development since it provides a safer and less expensive way of propulsion. It's known as rocket technology, and it's revolutionized the space business during the previous two decades. This study looks at the rocket engine's potential as a feasible mode of propulsion for both spacecraft and missiles. The main objective of this project is to digitize the rocket motor test bed by using different types of sensors to get their data on the screen at every time instant so we can calculate the thrust that is dependent on these very parameters, very precisely on every instant. The parameters will be calculated by installing sensors, then these sensors will be connected to the data acquisition system to compile the values of temperature, pressure, and mass flow rate and then this DAQ will be connected to the LabVIEW software to get the results of thrust on screen. Then we will perform this experiment by using different types of nozzles and propellants (having different shapes) and at last we will install an auto ignition system to ignite the rocket by single command.
Project ObjectivesThe objective of this project comprises of the following milestones:
a) To design an acquisition and data storage system to get the readings of the pressure, temperature and mass flow rate on the screen simultaneously.
b) Digitalize the analog data picked by the different sensors.
c)Then calculate the value of thrust of rocket which is in accordance with the theoretical data.
Project Implementation MethodMethodolgy;
literature review of the rocket motor test bed fabrication(first phase of this project) and the thrust produced by this rocket.
Estimating the values of the parameters by literature review and by anlytical calculations.
Selecting appropriate sensors to find value of combustion temperature and combustion pressure.
Callibrate these sensors.
Integrate these installed sensors with myDAQ.
make vi diagram on labview to get data from myDAQ.
Analyse the results. Compare these results with theoretical results.
Change dimension of nozzle to get supersonic flow at exit of nozzle.
Use different shapes of fuel to observe the difference in value of thrust obtained.
Benefits of the ProjectWe will be able to get the thrust of hybrid rocket motor on the screen of computer at every instant as the regression rate changes.
we wil be able to compare the result obtained by software with theretical results.
Technical Details of Final Deliverable- Design software of temperature, mass flow rate and pressure of combustion chamber.
- Store the values in database using lab view.
- Use data acquisition system to fire the rocket and get the exact values of sensors on the screen of pc with help of lab view software.
- Refine the dimensions of the CD nozzle to get supersonic flow.
- Use different type of fuel shapes and change nozzle types and observe the results.
| Item Name | Type | No. of Units | Per Unit Cost (in Rs) | Total (in Rs) |
|---|---|---|---|---|
| Total in (Rs) | 70000 | |||
| hyundai pressure sensor | Equipment | 1 | 40000 | 70000 |
| 20 gage iron-constantan type j thermocouple | Equipment | 1 | 30000 | 0 |