Print Email Facebook Twitter Thermal Modelling and Thermal Control Optimisation of the mN-μHEMPT Title Thermal Modelling and Thermal Control Optimisation of the mN-μHEMPT Author Granero Moneva, Nacho (TU Delft Aerospace Engineering; TU Delft Space Engineering) Contributor Cervone, A. (mentor) Hey, Franz Georg (mentor) Zandbergen, B.T.C. (graduation committee) de Croon, G.C.H.E. (graduation committee) Degree granting institution Delft University of Technology Programme Aerospace Engineering | Space Systems Engineering Date 2017-08-29 Abstract Airbus Friedrichshafen is working on the development of a milliNewton HEMPT (High EfficiencyMultistage Plasma Thruster): an electrostatic thruster concept suitable for small satellitepropulsion. An engineering model, the mN-μHEMPT, has been built and tested in vacuum,generating thrust levels in the range of 1 to 5 mN. Although the working principle is understood,there is still uncertainty in the loss process, in particular the heat transfer in the plasma-wallinteraction. An efficient heat management is crucial for the operation of the thruster, as theperformance of the magnets is severely hindered after reaching 250ºC. With this in mind, thepresent thesis aims to produce the first thermal model of the mN-μHEMPT, with which a detailedthermal analysis can be carried out. The model validation strategy, based on correlationto testing results, makes it possible to overcome the uncertainty regarding the thermal losses.By simulating the operation of the thruster in extreme load cases in a Low Earth Orbit, itsthermal performance is assessed, resulting in a detailed understanding of the temperatureevolution and heat propagation through the different components. This information is thenused to improve the performance by implementing design modifications. The result of thethesis is a thermal model validated to within 1.65ºC as mean deviation, predicting a maximumtemperature of 180ºC at the magnet stack during operation. The application of a boron nitridecoating to the radiator and the decoupling of the heat losses at the magnet stack and at theanode thanks to a second radiator, results in a maximum temperature of the magnet stackof 85ºC. In conclusion, the thermal performance of the mN-μHEMPT is analysed for the firsttime, and the design modifications proposed become a successful improvement. Subject HEMPTelectric propulsionthrusterspacethermalmodellingthermal analysisSystema To reference this document use: http://resolver.tudelft.nl/uuid:0333e720-8105-4429-abcd-430c0d04f031 Bibliographical note Thesis developed at Airbus Friedrichshafen. Part of collection Student theses Document type master thesis Rights © 2017 Nacho Granero Moneva Files PDF Thermal_Modelling_and_The ... oHEMPT.pdf 6.24 MB Close viewer /islandora/object/uuid:0333e720-8105-4429-abcd-430c0d04f031/datastream/OBJ/view