| 孙兰,史晨曦,任杰安,孙建亮,曹杰.基于维形要求的新型外热防护材料长期值班贮存寿命评估方法[J].装备环境工程,2025,22(5):50-57. SUN Lan,SHI Chenxi,REN Jiean,SUN Jianliang,CAO Jie.Long-term Standby Storage Life Evaluation Method for a Novel Thermal Protection Material Based on Maintainability Requirements[J].Equipment Environmental Engineering,2025,22(5):50-57. |
| 基于维形要求的新型外热防护材料长期值班贮存寿命评估方法 |
| Long-term Standby Storage Life Evaluation Method for a Novel Thermal Protection Material Based on Maintainability Requirements |
| 投稿时间：2025-03-27 修订日期：2025-04-16 |
| DOI：10.7643/issn.1672-9242.2025.05.008 |
| 中文关键词: 外热防护材料 值班贮存 维形要求 蠕变试验 加速老化试验 寿命评估方法中图分类号:TJ089 文献标志码:A 文章编号:1672-9242(2025)05-0050-08 |
| 英文关键词:thermal protection material long-term standby storage maintainability requirements creep test accelerated aging test life evaluation method |
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| Author | Institution |
| SUN Lan | Beijing Institute of Mechanic and Electric Engineering, Beijing 100074, China |
| SHI Chenxi | Beijing Institute of Mechanic and Electric Engineering, Beijing 100074, China |
| REN Jiean | Beijing Institute of Mechanic and Electric Engineering, Beijing 100074, China |
| SUN Jianliang | Beijing Institute of Mechanic and Electric Engineering, Beijing 100074, China |
| CAO Jie | Beijing Institute of Mechanic and Electric Engineering, Beijing 100074, China |
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| 中文摘要: |
| 目的 针对飞行器新型外热防护材料长期值班贮存期间维形要求，分析其受力特征，设计相关试验，评估其贮存期能否满足维形要求。方法 首先，分析新型外热防护材料在长期值班贮存期间的自然环境剖面和力学环境剖面。其次，通过定量分析外热防护层长期值班贮存的受力特点，分别策划蠕变试验方案、重复加卸载试验方案以及温度湿度双因素加速老化试验方案。最后，根据试验结果得到蠕变变形和运输过载变形叠加的累积变形量，作为是否满足外热防护层维形要求的判据。结果 设计蠕变试验获取了蠕变应变。重复加载卸载试验表明，最大应变与最大载荷有关，中间加载卸载过程的影响可以忽略。通过温度湿度双因素老化试验，获取了压缩模量的表达式以及压缩模量的老化规律，进而得到了贮存环境下的压缩模量，计算得到了运输过载变形。结论 针对飞行器新型外热防护层贮存20 a承载部位凹陷变形不大于1 mm的维形要求，试验及计算结果表明，蠕变变形和运输过载变形之和为0.72 mm，满足贮存寿命要求。 |
| 英文摘要: |
| In order to meet the maintainability requirements of the novel thermal protection material for the spacecraft during long-term standby storage, the work aims to analyze the loading characteristics of the material, design the relevant experiments, and evaluate whether the material can meet the maintainability requirements during the storage. Firstly, the natural and mechanical environmental profiles of the novel thermal protection material during long-term standby storage were analyzed. Secondly, the loading characteristics of the material were quantitatively analyzed to develop the creep test, repeat load-unload test and temperature-humidity accelerated aging test. The deformation of the novel thermal protection material, which was caused by the superposition of creep deformation and transportation overload deformation, served as the criteria for determining whether the thermal protection layer met its maintainability requirements. The creep test was designed to obtain creep strain. The repeat load-unload test showed that the maximum strain was related to the maximum load, while the intermediate loading and unloading processes could be neglected. Through the temperature-humidity accelerated aging test, the compressive modulus expression and its aging law were obtained, allowing the determination of the compressive modulus under storage conditions and the calculation of transportation overload deformation. Aiming at the maintainability requirement that the concave deformation of the bearing part of the novel thermal protection layer of the spacecraft is not more than 1 mm after 20 years of storage. The test and calculation results show that the sum of creep deformation and transportation overload deformation is 0.72 mm, which meets the storage life requirements. |
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