Group 24 Magnetically Coupled Pump System for Cryogenic Propellant Tank Destratification

       Since start of this project, there were a number of issues that had to be resolved. The first challenge consists of the size constraints of the inlet port of the currently used cryostats. Difficulties with the computational analysis of the pump curve that led to more time being spent on this part of the project, however the calculations were completed and the required power from the motor was found to be 0.5 hp and a required speed of 2500 RPM. The final change to the design that was made is related to the pump system. The design of this system has slightly changed; the inducer that was provided by NASA Marshall Space Flight Center will be used rather than constructing our own. Using this inducer and a self-constructed pump housing, it is possible to achieve the pumping capabilities.

Procurement:
       All of the components of the system (magnets and motor) have been ordered and arrived over the winter break. The raw materials needed to fabricate the components of the design are being supplied by the NASA Marshall Space Flight Center. These materials are in the progress of being collected and sent from. Bill of material can be found Here

Development:
       The fabrication and prototyping of this project will begin soon. We are currently in the process of setting up the electric components of the connecting the purchased driver to the selected motor. An experiment to test the coupling strength relative to the rotational displacement of the magnets using spring gauges is also being devised with the help of our faculty advisor. Upon the delivery of the raw materials, the design components will be sent to the machine shop to begin fabrication.

      Below are CAD drawings of the team's selected design. The design should be compact and easily installed into an existing cryogenic tank. It should also not introduce any additional heat into the cryogenic system. The cryogenic tank will be vacuum-sealed and there must be minimal heat leak from the environment. The cryogenic propellants will be stored at a low pressure of 15 to 25 psia. In order to prevent the pressure from rising, the pump must make the temperature homogenous to prevent the cryogen from boiling. The heat will also be limited through the use of 0.5 in of insulation foam and 20- 30 layers of MLI (Multi-Layer Insulation) where necessary. The pump will have a variable volumetric flow rate of no less than 3gpm and up to 15 gpm in order to satisfy the requirements. The mixer should also facilitate a pressure rise of up to 5 psid in the cryogenic fluid. Additionally, the device will be able to successfully perform destratification of the cryogenic fluids with ease. The motor-pump unit must make use of magnetic coupling technology and an electronic motor. The unit must be tested with water and liquid nitrogen