Spaceplanes are the future of space travel and launching objects into space. They are fully reusable, and provide a lot of flexibility to a mission. This thesis focuses on the propulsion system and its impact on the stability and control of a spaceplane. The main research question is: "Which parameters and deficiencies in the propulsion system of a winged second-stage spaceplane effect its controllability at single points during the hypersonic ascent phase?" To analyse propulsion effects, a dedicated propulsion model is developed to simulate the rocket engines of the vehicle. These engines are used for thrust vector control (TVC) of the vehicle. An incremental nonlinear dynamic inversion (INDI) controller is designed to study the controllability of the system. It is demonstrated that this INDI controller can effectively control the vehicle, even when subjected to thrust deficiencies, such as engine-out failures, engines getting stuck, thrust fluctuations and inertia shifts.

This report presents the Final design of the Design Synthesis Exercise (DSE) to 'Capture a Small Asteroid and Change its Orbit' at the Faculty of Aerospace Engineering at Delft University of Technology. The bachelor programme 'Aerospace Engineering' comprises several projects enabling students to explore aeronautics and space from different kinds of perspectives. The Design Synthesis Exercise serves as the conclusion to this programme. During this final project students integrate their previously obtained knowledge and skill to examine a specific design problem in groups of ten students for the duration of eleven weeks. This final report is the last in a series of four and documents the detailed design of the concept that was chosen in the mid-term report.