The multi-bolt metal/laminated composite joints is one of the typical joint forms for design of aircraft structures. However, considering that the stiffness and thermal properties of advanced composite materials are obviously different from those of metals, the thermal matching design for multi-bolt metal/laminated composite joints at high temperature becomes an urgent problem. To explore the thermal deformation mechanism and collaborative design law of multi-bolt metal/laminated composite joints at high temperature environment, this study takes a typical eight-bolt metal/laminated composite joints as research object. Finite element modeling and experimental research are adopted to systematically investigate the thermal deformation response of eight-bolt metal/laminated composite joints from room temperature 20oC to high temperature 175°C. Additionally, the influence laws of factors such as metal panel material type, laminated composite layup sequence, panel thickness, as well as the bolt preload on the bend deflection are systematically discussed. The research results show that: the stiffness and thermal properties of the connected structure panel play a controlling role in the thermal deformation of multi-bolt metal/laminated composite joints while the effects of the bolt preload on the deflection can be neglected. The above experimental research and discussion results can provide important design experience and valuable experimental cases for the thermal matching design of multi-bolt metal/laminated composite joints of aircrafts.