Tructure deformation and fracture behavior of a hydroxyl-terminated polybutadiene (HTPB) propellant by using in-situ uniaxial tensile experiments performed on a scanning electron microscope (SEM). Above all, the experimental procedures explore the particle atrix interfacial debonding as the primary source of failure with the composite strong propellant [5,6].Publisher’s Note: MDPI stays neutral with regard to jurisdictional claims in published maps and institutional affiliations.Copyright: 2021 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access short article distributed under the terms and circumstances on the Creative Commons Attribution (CC BY) license (licenses/by/ four.0/).Micromachines 2021, 12, 1378. ten.3390/mimdpi/journal/micromachinesMicromachines 2021, 12,two ofWith the improvement of computational technologies, Matous and Inglis [7] create the micromechanics model with all the Lanabecestat Purity & Documentation finite element mesh division. That is with regards to studying the meso-damage from the propellant, the failure and failure mechanism with the bonding interface, at the same time as the internal causes of macro mechanical properties of propellant. The study by Matous and Inglis also set the bonding components inside the interface layer amongst the particles and matrix to simulate the generation and development of interface dehumidification harm. This showed that the interfacial debonding may be the principal reason for the macroscopic stress-strain nonlinearity with the propellant. On this basis, Chang [8] found that the interface damage is closely associated with the size and relative position of particles. H. Arora [9] simulated the deformation and damage evolution procedure of polymer-bonded explosives. It was located that the particle geometries had an awesome influence around the onset of failure. The mechanical properties with the bonding interface in between the particles and matrix are crucial variables that could affect the macro stress-strain partnership of propellant. Based on the traits of meso-damage of propellant, Li [10] introduced the bonding interface element involving particle and matrix and described the propagation characteristics of interface harm by a bilinear cohesion model. They studied the interface debonding course of action of propellant and its influence on macro mechanical DMPO Chemical response by way of finite element calculation. An approximate characterization from the mechanical response of propellant particle/matrix interface by bilinear cohesion model was carried out by Zhi [11]. It was found that the initial modulus and tensile strength of propellant improved with the boost on the filling volume fraction. Further, the random distribution of particle position hardly impacted its mechanical properties. Elsewhere, Han [12] found that the bilinear cohesion model is not correct sufficient to reflect the interface mechanical behavior of actual propellant. However, it was evident that the price dependent exponential cohesion model can accurately simulate the crack propagation procedure of HTPB propellant below mixed loading mode. Cui [13] proposed a novel time-dependent cohesive zone material (CZM) according to the Maxwell box to simulate relaxation responses. According to their research, Ahmad [14] and Zhi [15] compared the stress-strain curve obtained by numerical simulation together with the test curve to establish the optimization objective function of harm parameters. The dehumidification damage parameters obtained through step-by-step iterative calculation were utilized to simulate the meso-damage procedure.