Téma:Development of a water rocket
Vedoucí:Jan Roháč
Vypsáno jako:Práce v týmu a její organizace
Popis:Water rocket simulation model
1. Assemble the simulation model in Matlab Simulink for a vertical flight of a water rocket, which will take into account - a) the dynamics of motion of a rigid body with variable mass including the effect of gravitational forces and the influence of aerodynamic drag, b) dynamics of a water column flowing out from the rocket through an outlet nozzle with respect to the rocket shape and dissipation losses, c) thermodynamics of pressurized air above the water level with respect to heat transfer, d) the dynamics of the flowing air through outlet nozzle (after emptying the water) with respect to the influence of the compressibility and the speed of sound. The output of the simulation model will be especially time progressions of altitude, speed and acceleration of water rocket, thrust and a specific impulse of propulsion system, flow velocity in the output nozzle, water level in the rocket, pressure and temperature of the air in the rocket, etc. The simulation model will be validated by measurements in the test bed.
2. Perform the optimization of initial parameters of the simulation model (e.g. volume of water, the nozzle diameter, air pressure, etc.) to achieve the maximum flight altitude for a given mass of the payload.
3. Perform the draft of size and position of aerodynamic surfaces for ensuring longitudinal stability during a vertical flight. Determine the conditions of static stability and assemble the simulation model for dynamic stability during the flight (CG position varies greatly). Required dependences of aerodynamic coefficients for different angles of attack will be determined by modeling of the flow around the rocket in the CFD program (e.g. Open Foam, Fluent).

Test bed for experimental verification of a water rocket simulation model
1. Design and develop a test bed dedicated for static experimental verification of the thrust of a rocket propulsion system. The thrust measurement will be based on the construction with strain gauges implemented to measure its time progression according to a rocket holder deformation.
2. The test bed will be also dedicated for experimental verification of parameters of the water rocket simulation model (e.g. dissipation losses, heat transfer etc.). For this purpose design and develop a measuring system for evaluation of pressure and temperature inside the rocket, and the level of the water in the rocket. The emphasis should be paid to the character of changes of those quantities. It has to be taken into account that those changes are rapid, i.e. in about 1.5 second the water is emptied and there might be a pressure drop from 10 bar to the atmospheric pressure, in the case of the temperature it might be a drop of -70 °C.

Trajectory measuring system for a water rocket motion tracking
1. Design and develop a measuring system dedicated for tracking a water rocket motion. The system should enable estimation of the position, speed, and attitude of the rocket primary based on MEMS based inertial sensors, e.g. accelerometers and gyroscopes, aided by magnetometers and/or GPS receiver. It has to be taken into account that the flight has four stages: a) the launch, b) a powered ascent – the acceleration is about 11 g and coasting flight, c) the descent, and d) the falling with ground reaching and recovery. The whole ascent can take about 5-7 seconds according to the size of the rocket and its inner initial pressure. The estimated data as well as raw data should be stored in a SD card for post-flight evaluation.
2. Design and develop a parachute deployment system for rocket safe and slow descent and landing. The parachute should be deployed when the rocket reaches its highest altitude.
3. Design a SW for the rocket motion trajectory evaluation.
4. Verify developed systems experimentally.

Parachute launching system
1. Design and develop a parachute launching system to be activated before the descent the stage of a water rocket flight takes place.
2. Verify its reliability.

Pokyny:Communication within the team will be held in English. Two team members will arrive from Spain. The project will be co-coordinated by Petr Kočárník, PhD. (Department of Electric Drives and Traction) who will be responsible for the rocket design.

The PTO assignments can be extended for diploma theses. The topic provides broad possibilities for student mobility within PEGASUS Network (

Realizace:Letu schopný HW
Vypsáno dne:04.02.2015
Max. počet studentů:5
Přihlášení studenti:David Blanco Abejón, Jaime Cabrera Valor, Jakub Štol, Jan Frank

Upozornění: toto je závazné přihlášení. Zrušit ho může pouze vedoucí práce