The adhesive interface of solid rocket motors is a weak zone prone to interfacial debonding and cohesive failure. Analyzing the meso-scale damage evolution process of adhesive interfaces is fundamental for motor failure assessment. Using an in-situ loading device and a high-resolution micro-CT system， in-situ scanning imaging tests were conducted on the adhesive interface of insulation layer/liner/propellant. The internal three-dimensional micro-digital images were obtained， and the meso-damage modes and evolution processes were analyzed. The digital volume correlation （DVC） method was employed to calculate the deformation fields of the adhesive interface under in-situ tensile conditions. The results show that under external loading， the deformation near the liner/propellant interface is greater than that in other regions. When the external strain reaches 6%， microvoids form due to uneven deformation between particles and the matrix， leading to particle-matrix debonding. At an external strain of 20%， microvoids coalescence causes interfacial damage and failure. The DVC method enabled the calculation of internal displacement and strain fields of the adhesive interface， revealing the deformation characteristics and strain distribution in the tensile process. The area near the liner/propellant interface is identified as the strain concentration zone in the tensile process and the primary site of damage initiation.