The focus of this thesis has been to design a Linear Parameter-Varying (LPV) control system for the European Launch Vehicle (LV) VEGA. More exactly, the objective has been to stabilize the LV during its atmospheric flight from liftoff to Main Engine Cut Off (MECO) when disturbances are present, such as wind gusts, sensor noise and computational delays. The thesis covers a derivation of a 3D LV model and theory, design, and simulation of an LPV controller. The LV model is derived from translational and rotational dynamic equations affecting a six Degrees of Freedom (DoF) LV. The LV is simplified to a 2D model and Jacobian linearizations are conducted in a systematic manner to derive a linear state space representation. This report then establishes wellknown requirements for a typical LV during ascent. An LPV controller model is designed with a lower Linear Fractional Transform (LFT) configuration and is augmented with a selection of frequency dependent filters on the input and output channels designed to satisfy the requirements. Lastly, the LV control system is simulated through a linear LPV simulation with user specified inputs. The result from the simulation concludes the LV is stable and is operating as intended while satisfying its requirements.