Print Email Facebook Twitter An exploration into the potential of microturbine based propulsion systems for civil Unmanned Aerial Vehicles Title An exploration into the potential of microturbine based propulsion systems for civil Unmanned Aerial Vehicles Author Marcellan, A. Contributor Visser, W.P.J. (mentor) Faculty Aerospace Engineering Department Flight Performance and Propulsion Date 2015-05-13 Abstract A Master Thesis Research has been undertaken with the goal of investigating the potential of micro gas turbines as propulsion system of choice for small Unmanned Aerial Vehicle (UAV) used in civil applications. The UAV market is likely to develop great economic and technological importance on a near future because of the wide variety of applications and the added value related to the unmanned vehicles. In this regard, research focused on improving UAV capabilities is strictly related to UAV propulsion systems; as a matter of fact, aircraft performance is dependent on the mass of the power-plant and its specific fuel consumption since these can have a very significant effect on the reduction in size or increase in range of the UAV. An Exploration Study is performed both in the fields of UAV technology and of Micro Gas Turbine technology. These two areas are covered in order to understand the possible advantages and limitations of micro gas turbine engines compared to alternative propulsion concepts (e.g. electric and reciprocating engines) when used for a specific application. After the identification of a significant Case Study, a conceptual design of a high-potential UAV micro gas turbine based propulsion system is performed. Prediction of scale effects is important within the framework of turbine conceptual design where the power output is varied in order to optimize the mission performance in which the turbine is integrated. To this end, engine cycle optimization using Gas turbine Simulation Program (GSP) is carried out. Furthermore, an "Aircraft Study" is performed in a correlated Master Thesis Project in which the aerodynamic and flight performance model of a baseline UAV is developed. After the model validation, results from the micro gas turbine model are integrated and the performance of the new UAV configuration is investigated. The final engine configuration is a 77 kW dual shaft turboprop which is further implemented into the UAV platform redesigned accordingly to the reduced weight and improved performance. The mission model estimates for this configuration an endurance of 28.7 hours, with a range of 4419 km and a payload weight of 250 kg, with a significant fuel reduction of 12.5% compared to the original UAV configuration. The effect of power setting at cruise and the engine weight reduction allows the turboprop to arguably showcase overall better mission performance. As a result of the work carried out in this Master Thesis Project, a valuable tool for understanding the contribution of micro gas turbine integration into civil UAV has been developed. Subject microturbineUAVcivil Applications To reference this document use: http://resolver.tudelft.nl/uuid:db9e8daf-dede-4915-9425-df4bc9706c12 Part of collection Student theses Document type master thesis Rights (c) 2015 Marcellan, A. Files PDF Thesis_Anna_Marcellan.pdf 3.36 MB Close viewer /islandora/object/uuid:db9e8daf-dede-4915-9425-df4bc9706c12/datastream/OBJ/view