Development and evaluation of thermal model reduction algorithms for spacecraft

Modeling and Thermal Analysis of a Moving Spacecraft Subject to Solar Radiation Effect

“…The performance requirements of a spacecraft's mission could be assessed at the earliest stages of design through the development of mathematical models and deployment of computational tools. Recent advances in computer hardware and software have enabled to reduce the computational burden associated with the numerical integration of the high-fidelity equations governing the heat transfer of the aforementioned systems [2,9,26]. Software tools can be deployed to assist the design process and provide guidelines to enable enhanced operability of spacecraft.…”

“…The space environment during the spacecraft travelling time and mission continues to be a major cause of anomalies in many space missions. The most common factors of such anomalies are surface charging and discharging, solar radiation heating loads, and the existence of orbital debris in space as indicated by several published studies [1][2][3][4][5][6][7][8][9][10][11][12]. In addition, the solar load, shielding material, onboard equipment location, thermal control and air conditioning systems must be considered during the design stage of spacecraft/satellites [13][14][15][16][17][18][19].…”

Quasi-Autonomous Spacecraft Thermal Model Reduction

“…This is one important difference between TPWL and POD MOR techniques. The TPWL approach has been applied by Wang, Qian et al in the problem of spacecraft thermal model reduction [30,31], and briefly commented by Deiml et al in [32]; these references will be discussed later. It has also been applied in nonlinear heat transfer problems by Yang and Shen in [33].…”

“…It is important to note that even though the POD modes are an optimal representation of the data, it does not imply their optimality for the reduced model generation. The reader can find more information regarding general POD applications and theory in [37], whereas POD application for spacecraft thermal model reduction is discussed in [31] and [32] and will be reviewed later in section 1.3.…”

“…Deiml et al make in [32] a clear distinction between GMM and TMM in the process of reducing a spacecraft thermal model. The model has the environment -including deep space-, the boundaries (which are the nodes/geometries that have couplings with the environment) and internal nodes/geometries (which are only connected to the model boundaries).…”