This article deals with the problem of non-fragile linear parameter varying (LPV) switching attitude tracking control for a near space hypersonic vehicle (NSHV). Firstly, nonlinear attitude dynamics of the NSHV is modeled as a slow-fast loop polytopic LPV model by using Jacobian linearization and Tensor-Product (T-P) model. Secondly, for less conservative controller design purpose, the flight envelope is divided into four sub-regions. Slow loop and fast loop LPV controllers are designed for each sub-region. Based on switching character function, these slow loop and fast loop LPV controllers are then switched in order to guarantee the closed-loop NSHV system to be asymptotically stable and satisfy a specified performance criterion. The existed conditions of the desired non-fragile LPV switching controller are deduction by linear matrix inequations (LMIs) and the system stability analysis is given by multiple Lyapunov functions (MLPs), compared with existing control scheme, the proposed method is less conservative. Finally, numerical simulations have demonstrated the effectiveness of the proposed method.