| Thermal protection system design of low-temperature tank is one of the critical techniques for developing many kinds of reusable launch vehicle (RLV). Thermal analysis is one of the most important processes for designing the low-temperature tank protection system of RLV. The conventional thermal analysis method for the low-temperature tank thermal protection system of the expendable launch vehicle (ELV) is not applicable for RLV. In order to overcome these above problems, the thermal analysis method for the thermal protection system of RLV is studied comprehensively in this dissertation. The main contents of this dissertation are as follows:(1) The history of thermal protection system of launch vehicle is introduced, and the difference between the thermal protection system of ELV and RLV is analyzed. The thermal environment conditions of thermal protection system in different flight phases such as preparation on ground, ascend, orbital and reentry are described.(2) The heat conduction theoretical model of low-temperature tank is proposed, and the mathematical computation method is provided. Besides, the boundary conditions of low-temperature tank in different flight phases are analyzed. Through thermal conduction analysis, the temperature-distributing rule of thermal protection system under different environment are specified, which are the foundation for completing the optimization design of low-temperature tank thermal protection system in the whole flight mission.(3) The one-dimension thermal stress analysis model based on one-dimension temperature field is proposed. The analysis method for the tank with board-shell structure model using the revised one-dimension thermal stress model is provided. The correctness of the model and method is testified by the simulation results.The results obtained in this dissertation can provide designing the thermal protection system of RLV with the theoretical basic and computational reference. |
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