Generic model for missile ight dynamics simulation
Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Simulations are run during early design conception phase in order to have a global overview of the performances and abilities of a given product. Building the aerodynamics and control of a flying device such as a missile requires time and resources. This study focuses on the development of a simplified but accurate enough model of a controlled airframe. The purpose of such a model is to get a good estimation of the behaviour of a given missile. The model has a generic structure which allows it to be adapted to any kind of missile. Given the commanded acceleration in missile frame of reference the simplified model gives the position and the attitude of the missile. A back-to-back validation with a pre-existing model of controlled airframe is performed in order to get the most accurate one. Such a study raises several challenges when it comes to modelling the autopilot or the aerodynamics of the missile. The aerodynamics of this controlled airframe is built such asto require as few aerodynamic parameters as possible. The performances of the simplified controlled airframe meet the expectations of its designers but users have to be aware that this simplified model is limited by its structure: a first-order linear and invariant model cannot describe accurately a whole flight. Further studies on the speed and acceleration ofthe platform when ˝ring and on the controlled but non-guided flight phase can reinforce the model accuracy.
Place, publisher, year, edition, pages
2015. , 12 p.
TRITA-AVE, ISSN 1651-7660 ; 2015:55
Engineering and Technology
IdentifiersURN: urn:nbn:se:kth:diva-180472OAI: oai:DiVA.org:kth-180472DiVA: diva2:894206
Subject / course