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| Design and Thermomechanical Behavior of Full-composite Structurally Integrated Thermal Protection Structure for Near Space Vehicles |
| Received:September 04, 2019 Revised:December 10, 2019 |
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| DOI：10.7643/issn.1672-9242.2020.01.007 |
| KeyWord:structurally integrated thermal protection system thermal protection load carrying thermomechanical behavior high temperature test |
| Author | Institution |
| SHI Sheng-bo |
a.School of Astronautics, b.Shaanxi Aerospace Flight Vehicle Design Key Laboratory, Northwestern Polytechnical University, Xi′an , China;a.School of Astronautics, b.Shaanxi Aerospace Flight Vehicle Design Key Laboratory, Northwestern Polytechnical University, Xi′an , China |
| TANG Shuo |
a.School of Astronautics, b.Shaanxi Aerospace Flight Vehicle Design Key Laboratory, Northwestern Polytechnical University, Xi′an , China;a.School of Astronautics, b.Shaanxi Aerospace Flight Vehicle Design Key Laboratory, Northwestern Polytechnical University, Xi′an , China |
| LIANG Jun |
a.School of Astronautics Engineering, b.Institute of Advanced Structure Technology, Beijing Institute of Technology, Beijing, , China;a.School of Astronautics Engineering, b.Institute of Advanced Structure Technology, Beijing Institute of Technology, Beijing, , China |
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| Abstract: |
| The paper aims to develop a lightweight thermal protection structure and system with integrated thermal protection and load carrying capacities to meet the rigor requirement on structure and thermal protection system of near space vehicles. A full-composite structurally integrated thermal protection system (SITPS) was designed according to the requirements of both load carrying and heat resistant. The ablation properties of composite SITPS were studied by the thermal exposure experimental tests. Ablation and thermal protection mechanism of surface materials were studied. The modeling of thermal and mechanical responses of the SITPS was proposed. The application research of SITPS for the wings of a hypersonic vehicle was carried out. The coupled thermal and mechanical analysis was conducted through the finite element methods. Although the thermal decomposition existed on the heated surface of SITPS after thermal exposure test, the structural properties of the post-test SITPS was still good. The SITPS designed meets the design requirements of both thermal protection and load carrying, and is an ideal thermal protection scheme for the next generation of aerospace vehicles. |
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