Prototype Development of Alumina Based Microthruster using High Temperature Co-fired Ceramics (HTCC) Technology : Design, Manufacturing, and Verification

With the advent of nanosatellites the need of developing various micropropulsion systems which can provide the thrusts in range of micro-Newton (μN) to mili-Newton (mN) has gained significantimportance. A liquid monopropellant thruster depends on few components such as propellant tank,injector, heating and catalytic chamber and nozzle. This makes it possible to be adapted to microscalewith suitable changes in design.This master thesis reports on the design, manufacturing and characterization of a ceramic- based liquid monopropellant microthruster which can be a potential alternative to the silicon based micropropulsion systems to provide the thrusts in range of micro-Newton (μN). Few observationsmade for future designs have also been included. The microthruster has been fabricated using the high temperature co-fired ceramic (HTCC) technology and consists of five components: microheater, two temperature sensors enabling four-point measurements, catalytic bed, and a converging divergingmicro nozzle, all integrated in a chip with dimension of 25×25× 0.6 mm3 before sintering.Maximum operating temperature reached with propellant being pumped in catalytic chamber, was307°C with a heating power of 5.62 W. Hydrogen peroxide (30%) was used as propellant for the tests.Complete vaporisation of the propellant was successfully demonstrated.The work has been done at the Ångström Space Technology Centre (ÅSTC), Uppsala University,Uppsala, Sweden. ÅSTC is a research group currently dedicated to the development of microelectromechanical systems (MEMS) systems for space and other harsh environments.Validerat; 20151215 (global_studentproject_submitter