Bachelor/Master-Thesis: LIQUID ROCKET ENGINE PRELIMINARY THERMAL DESIGN CASE STUDY

In this study, a case study will be conducted on the design of cooling ducts for a liquid-fueled rocket engine during the preliminary design phase. Thermal management of rocket engines is crucial to prevent material deformation at high temperatures and to enhance engine efficiency. Therefore, it is recommended that you conduct thorough literature research and consult the necessary books before beginning this study.

Tasks expected from the student are listed below. The engine geometric dimensions will be given previously.

• Calculate the O/F ratio for maximum combustion efficiency.
• Calculate the mass flow rates for fuel and oxidizer separately.
• Calculate the thermopyhsical properties of the burned gas resulting from the fuel and oxidizer mixture using analytical or any software.

After conceptualizing and drawing the rocket profile of the liquid-fueled rocket engine whose design dimensions will be pre-defined, the student should conduct the following steps:

• Calculate the heat flux along the profile as a result of combustion. You can use the thermo- physical properties you calculated in 1-c for this calculation. Explain your assumptions and methods in detail.
• Determine the appropriate channel section dimensions and the number of channels required for this profile. You can make assumptions in the first stage.
• Calculate the total channel pressure losses and temperature distributions with CFD using these values.

The student can perform all your tasks using the software and programs she/he wants.

Further question will be answer as follows:

• What are the boundary conditions (adiabatic, isothermal or a constant heat transfer coefficient?) for the outer surface of the nozzle?
• Will the coolant be the fuel or oxidizing liquid, or a mixture of them?
• What is should be considered for inlet temperature and inlet pressure of the coolant?
• Any value given for the surface roughness of the cooling channels?

This task will be conducted in collaboration with a company working in spacecraft technologies. Therefore, the potential student is asked to

• have good grades in Heat and Mass Transfer, Numerical Methods (at least 3.25 GPA)
• have basics in CFD and CAD
• be interested and motivated in working on thermal analysis issues
• write and present a conference paper

Bachelor/Master-Thesis: RADIATOR AREA OPTIMIZATION STUDY

One of the thermal control methods used to manage the heating and cooling of satellites in space is radiators. Radiators are surfaces generally coated with materials with high emissivity. For example, materials such as white paint, thanks to their high reflectivity and low absorbency properties, reduce heating by reflecting solar heat, while at the same time providing cooling by radiating the internal heat into space through radiation. In this way, temperatures of electronic equipment are kept within safe limits and satellite missions can be completed successfully.

In this study, an electronic equipment connected to an aluminum 6061 plate with 1 x 1 m dimensions and 0.04 m thickness and 0.035 surface emissivity coating. Assuming that the surrounding of the system has adiabatic boundary condition, the plate is thermally conditioned in an environment maintained at 200 K.

[New Space Economy]

The student is expected to accomplish the following work packages:

• Radiator surface material selection
• Selection of thermal interface material between the equipment and the plate
• Analytical calculation of the required radiator area in steady-state
• Selection of the radiator surface coating.
• Determination of time-dependent temperatures of equipment temperatures for cases where the equipment produces a certain heat flow (60 W) with heat rejection over a duration of 10 min
• Evaluation of heat rejection over 50 min at 40 W waste heat

This task will be conducted in collaboration with a company working in spacecraft technologies. Therefore, the potential student is asked to

• have good grades in Heat and Mass Transfer, Numerical Methods (at least 3.25 GPA)
• have basics in CFD and CAD
• be interested and motivated in working on thermal analysis issues
• write and present a conference paper

Start:     immediately

Contact:

Assoc. Prof. Dr. Mete BUD