Study and implementation of the stability and control system of a mini-launcher
Document typeMaster thesis
Rights accessOpen Access
ProvenanceIn this Master Thesis Work (TFM), the proposal is to study some aspects of the stability, like flutter effects, over a small space launcher (less than 100 kg including propellant and payload). This mini-launcher is called Wiki-Launcher and it is part of a space mission done by the Wikisat team. This team is participating in the N-Prize competition that consists of designing a femto-satellite (Less than 20 grams) and injecting it into orbit by a home-made launcher that costs less than 1,000 Pounds Sterline before September, 2012. Flutter is a kind of self-excited aeroelastic unstable phenomenon where the safety of the flight vehicles may be threatened. Flutter can be catastrophic once it occurs and must be avoided. Thus it is mandatory to verify the flutter boundary of the flight launcher by performing wind-tunnel and flight tests, which always consume plenty of time and money. Efficient and effective flutter prediction methods are in demand so as to accelerate the process of tests, as well as ensuring the safety during the tests. The flutter boundary of a mini-launcher is predicted using the data-based parametervarying model. The core algorithms are the well-developed linear fraction transform (LFT) and μ-analysis. Compared with the former model-based μ method, this approach requires less model information and is easier to handle. In this thesis, we try to check if this method is able to be implemented in a low cost way for the Wiki-Launcher that could be extended to other larger launchers.