Dynamical thermal model for precise satellite temperature distribution analysis in the scope of the mission simulation toolXHPS
Başlık çevirisi mevcut değil.
- Tez No: 852106
- Danışmanlar: PROF. DR. BENNY RİEVERS
- Tez Türü: Yüksek Lisans
- Konular: Havacılık ve Uzay Mühendisliği, Aeronautical Engineering
- Anahtar Kelimeler: Belirtilmemiş.
- Yıl: 2022
- Dil: İngilizce
- Üniversite: Universität Bremen
- Enstitü: Yurtdışı Enstitü
- Ana Bilim Dalı: Belirtilmemiş.
- Bilim Dalı: Belirtilmemiş.
- Sayfa Sayısı: 77
Özet
Advancements in the satellite technology and the accessibility of space becoming easier, the trend in the space sector has shifted towards smaller satellites. In order to optimize the highly-iterative process of satellite design and to avoid catastrophic failures due to the harsh space environment, engineers use various methods to verify their design, such as tests or analyses prior to launch. Thermal design of the satellite is vital for shaping the overall design and usually verified with thermal analysis software. Thermal design is also a very iterative process, starting off with a preliminary analysis of a simple satellite model, supported with assumptions and rough ideas, later on repeating the analysis with an elaborated model where all equipment mounted on the structure. In this study, a MATLAB-Simulink based dynamic satellite simulation tool HPS, developed by ZARM in corporation with DLR is used, to mimic the satellite behavior under the effect of various sources of perturbations and to access the illumination conditions in orbit under different attitude scenarios. Although external fluxes and thermal radiation pressures are modelled with precision in HPS, internal heat transfer within the satellite cannot be modeled dynamically. Therefore, a separate software is needed for the thermal calculations regarding in-orbit hot and cold cases. However, this will not yield a dynamical model where the effect of instantaneous illumination conditions on the thermal model, or the effect of uneven temperature distributions on the satellite attitude is reckoned. At this point, coupling with an additional software is needed at each time step and two software must be run simultaneously. For this purpose, feasibility of an open-source tool used in various applications, OpenFOAM and its heat transfer models are investigated. Although the coupling of software for simultaneous solving could not be achieved, a method for the preliminary thermal analysis of a sample CubeSat in OpenFOAM has been presented. Started by defining the thermal control subsystem, its equipment and in-orbit thermal environment, an introduction is made. The theory of heat transfer is explained, the literature on previous work has been reviewed and a mathematical model to be used in application process is given. The built OpenFOAM case for preliminary analysis is presented, explaining the utilities and functioning of the software. Ways to elaborate the current model for the following, more matured and trustworthy analyses are discussed. The preliminary results obtained and whether OpenFOAM is a suitable tool for this purpose are discussed. Limitations encountered and the future work needed to achieve this objective are given.
Özet (Çeviri)
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