Abstarct: In this thesis, the separation mechanism of an aerospace system by a frangible joint ring composite has been investigated, the way and feasibility of the research being connected to the reality depended on it being investigated both in the scientific and experimental fields. In the initial design of the separation ring, the thickness of the separation place was determined to be 5 mm, the stresses on the separation ring were very low, then by changing the design, we achieved a thickness of 2 mm in an optimal and logical design with an ideal thickness at the separation place. And in the analysis phase, carbon fibers and thermosetting epoxy resin have been used. In the analysis, the amount of force and how to apply it, the angles of the fibers, and the boundary conditions for the assembly set were determined in Abaqus software. And according to the mechanical stress analysis, the maximum stress applied to the laxyers in different directions is 338 megapascals. which is separated with the least amount of explosion and withstands the incoming forces well during maneuvering and moving. Separation was investigated in explosion analysis using 10 g/m Paten explosive core and its results were compared with the experimental explosion test. The purpose of the explosion test and numerical analysis is to separate the composite ring from the predetermined location.