<p>At any time, the pace of space exploration has never stopped. In recent years, thanks to the rapid progress of space science and technology, satellites, probes, stations and other man-made equipment have been launched into space one after another, and manned space activities have become frequent. It is important to note that lightweight is still a major requirement for these equipment, as a lower launch weight allows more loads to be carried. Carbon fiber reinforced plastic (CFRP) is one of the lightweight, high strength materials commonly used in space. As a key component of spacecraft, it will inevitably experience high-speed collision events with space debris and waste recycling during operation in space, leading to more complex thermodynamic problems. In this study, a method to construct the CFRP constitutive under high strain rate impact was reported by identifying the strain rate state, generating the adiabatic temperature and modifying the (secant) stiffness matrix. In the low strain rate compression state, the initial nonlinearity caused by material defects was described by introducing the initial nonlinear modulus increasing factor. In the high strain rate impact state, the nonlinear high strain rate strengthening effect was described by introducing the dynamic strengthening factors of stress and strain based on the mechanical behavior under the reference strain rate. Based on the instantaneous temperature rise obtained from the impact adiabatic equation, the mechanical-thermal coupling effect was described by considering the influence of temperature on modulus and strength. Using incremental constitutive logic, a user-defined material subroutine was developed and feasibility verification was performed in conjunction with the experiment. This research work includes the establishment method of the constitutive of CFRP under high and low strain rate states, which provides a design reference for some extreme space collision events.</p>