## 1 Introduction  
The brake disc is a crucial component of mechanical braking systems, responsible for rapidly converting kinetic energy into thermal energy through friction, thereby enabling the deceleration or stopping of vehicles or equipment. Its performance is vital to ensuring operational safety and stability [1]. In aircraft braking systems, the brake disc operates under more demanding conditions compared to ground transportation. During landing and taxiing, the disc must endure significant energy conversions, leading to a rapid temperature rise on its surface and generating complex temperature fields and thermal stress distributions [2]. To meet the high-intensity braking requirements, aircraft brake discs are typically made from carbon-based composite materials, known for their exceptional lightweight and high-temperature resistance properties [3]. However, thermal stress accumulation under high-temperature conditions can result in cracking, deformation, or material failure, potentially impacting the functionality of adjacent components and threatening the aircraft's operational safety. Thus, accurately predicting the temperature distribution in brake discs is critical for optimizing structural design and material selection, extending service life, and ensuring operational reliability and safety. Current research on disc brakes for automobiles and trains is abundant [4; 5; 6; 7], but studies on the temperature field of aircraft brake discs remain relatively limited. [PERSON] et al. [8] pioneered the use of finite element methods to analyze the unsteady thermoelastic problem in aircraft braking systems and proposed a criterion for predicting wear rates of disc brakes in 1974. [PERSON] et al. [9] employed thermocouples to measure the temperature at the friction interface and investigated its distribution patterns. [PERSON] [10] introduced a method based on HDFW equations to calculate the maximum temperature on the friction surface during braking. However, these studies largely rely on experimental testing and simplified theoretical analyses, constrained by time, cost, and the complexity of boundary conditions. In order to verify the thermal safety of the brakes during the design phase, a computational model capable of predicting their thermal behaviour is required. [PERSON] et al. [11] established a model considering the heat exchange with the environment, derived formulas, and verified them through experiments, providing theoretical support and a basis for the calculation of the thermal analysis of aircraft brakes. With advancements in computational technology, numerical simulation has emerged as a vital tool for investigating heat transfer problems in brake discs. Constructing heat transfer models enables effective analysis of temperature distributions and their variations under different working conditions. [PERSON] et al. [12] simulated the transient temperature field of carbon-carbon (C/C) composite aircraft brake discs, and clarified the calculation method of thermal load and the determination method of key parameters. By combining experiments and simulations, a real temperature field distribution nephogram was obtained. However, in this study, only 1/8 of the brake disc was used for 3D solid modelling, so there are still differences in the full-scale heat transfer characteristics. The interfacial heat transfer characteristics of C/C composite and the frictional heat generation process are necessary conditions for high-precision numerical simulation. [PERSON] et al. [13] used techniques such as Thermogravimetric Analysis/Fourier Transform Infrared Spectroscopy (TGA/FTIR), Temperature-Programmed Reduction (TPR), and Pyrolysis-Gas Chromatography-Mass Spectrometry (Py-GC-MS) to study the thermal behaviour and surface changes of C/C composites during simulated aircraft braking, providing a basis for a deeper understanding of the performance of this material in braking applications. [PERSON] et al.