运载火箭表面防护技术及其研究进展

熊书强; 王一名; 袁佳熙; 王军; 杨洋; 卢鹉; 张崇印; 鞠鹏飞; 朱新远

doi:10.16490/j.cnki.issn.1001-3660.2025.14.001

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表面技术 ›› 2025, Vol. 54 ›› Issue (14) : 1-11. DOI: 10.16490/j.cnki.issn.1001-3660.2025.14.001

研究综述

运载火箭表面防护技术及其研究进展

熊书强¹, 王一名¹, 袁佳熙¹, 王军¹, 杨洋¹, 卢鹉^1,2, 张崇印^1,*, 鞠鹏飞^1,*, 朱新远^1,3

作者信息 +

Research Progress of Launch Vehicle Surface Protection Technology

XIONG Shuqiang¹, WANG Yiming¹, YUAN Jiaxi¹, WANG Jun¹, YANG Yang¹, LU Wu^1,2, ZHANG Chongyin^1,*, JU Pengfei^1,*, ZHU Xinyuan^1,3

Author information +

文章历史 +

摘要

运载火箭是将人类制造的卫星、载人飞船、空间站、空间探测器等各种航天器推向太空的重要载具,其中运载火箭表面防护技术是其成功发射的重要保障。概述了运载火箭表面防护技术,主要包括烧蚀性热防护涂层技术、非烧蚀性热防护涂层技术、环境适用性表面涂层技术和低温绝热材料技术等。烧蚀性热防护涂层是通过质量损耗带走热量的一种有机涂层,可分为两类：环氧类烧蚀防热涂层和硅橡胶类烧蚀防热涂层,前者存在附着力好的优点,但是高温易开裂,涂层韧性差,适用于较低热流密度防护;后者耐温性好,但存在烧蚀易粉化的缺点。非烧蚀性热防护涂层是一类高红外辐射率的陶瓷无机涂层,国外已经发展了三代非烧蚀性热防护涂层材料体系,适用于可重复运载火箭关键部位的热防护,但国内研究基础与工程能力相对不足。环境适用性表面涂层主要用于应对运载火箭地面发射时面临高盐雾、高湿热、高辐射等环境工况,发展了防辐射、抗静电等防护涂层。低温绝热材料起到超低温液氧/液氢工况保温隔热的作用,主要有泡沫材料和气凝胶材料,前者较后者施工工艺更为灵活,满足复杂形状的高效隔热。总结了近年来国内外运载火箭表面防护技术的发展现状和趋势,介绍了运载火箭卫星整流罩、推进剂贮箱和舱体尾部等不同部位面临的不同防隔热需求,为相关的研究工作提供了技术参考。

Abstract

Launch vehicles are crucial vehicles to push various spacecraft, including satellites, manned spacecraft, space stations etc. into space. The surface protection technology of launch vehicles is a vital guarantee for their successful launch. The overview of the surface protection technology of launch vehicles encompasses four major technological domains: ablated thermal protection coating technology, non-ablated thermal protection coating technology, environmentally applicable surface coating technology, and low-temperature thermal insulation material technology. Ablated thermal protection coating is an organic coating that takes away heat through ablation mass loss. It can be divided into two categories: epoxy ablated thermal protection coating and silicone rubber ablated thermal protection coating. The former has advantages of good adhesion, but it is prone to cracking at high temperature, which is suitable for low-heat flow density of protection; The latter has high temperature resistance, but it has disadvantages of ablation and easy powderization. Non-ablative thermal protection coating is a ceramic inorganic coating with high infrared emissivity. Three generations including RGG, TUTI and HETC of non-ablative thermal protection coatings have been developed abroad, which are suitable for thermal protection in key parts of reusable and repeatable launch vehicles. Domestic relevant research institutes have also developed multiple non-ablative protective material systems. However, the domestic research foundation and engineering capabilities are relatively insufficient. Environmentally applicable surface coating mainly meets the environmental conditions such as high salt spray, high humidity and heat, and high radiation during ground launch of the launch vehicles, and protective coatings such as radiation-shielding and anti-static coatings have been developed. Domestic launch sites are gradually shifting from Jiuquan launch sites to Hainan launch sites. Traditional coatings are difficult to meet the requirements of solar radiation, facing the requirements of high-irradiation, anti-salt spray, anti-moisture heat, anti-electrostatic and anti-mildew. Low-temperature insulation materials play the role of insulation under ultra-low-temperature liquid oxygen/liquid hydrogen conditions, mainly including foam materials and aerogel materials. The former is more flexible in construction technology than the latter, and meets efficient heat insulation in complex shapes. Taking polyurethane foam as an example, it is widely used in the thermal insulation conditions of launch vehicles. However, aerogel materials have low density and high temperature resistance, and are currently gradually promoted and used in the aerospace field. This article focuses on summarizing the current development status and trends of surface protection technology for launch vehicles at home and abroad in recent years, introducing the surface protection strategies for different parts of launch vehicles such as satellite fairing, propellant tank and cabin tail, and providing technical references for related research work. With the development of launch vehicle technology, thermal protection materials in the future must meet the basic usage requirements of lightweight, repeatable and low cost. In addition, traditional heat-proof structures often use multi-layer structures to meet functional needs. This type of protective structure is low-quality and efficient, and multi-functional integrated heat-proof coatings of high heat resistance, high heat insulation, and high emission have become the key direction for scientific researchers to develop coatings.

导出引用

熊书强, 王一名, 袁佳熙, 王军, 杨洋, 卢鹉, 张崇印, 鞠鹏飞, 朱新远. 运载火箭表面防护技术及其研究进展[J]. 表面技术. 2025, 54(14): 1-11 https://doi.org/10.16490/j.cnki.issn.1001-3660.2025.14.001

XIONG Shuqiang, WANG Yiming, YUAN Jiaxi, WANG Jun, YANG Yang, LU Wu, ZHANG Chongyin, JU Pengfei, ZHU Xinyuan. Research Progress of Launch Vehicle Surface Protection Technology[J]. Surface Technology. 2025, 54(14): 1-11 https://doi.org/10.16490/j.cnki.issn.1001-3660.2025.14.001

中图分类号： TB34

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