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杨凯威 , 张杨 , 梁欢 , 等 . 高超声速飞行器热流密度/分层温度/炭化层研究 [J ] . 中国空间科学技术 , 2018 , 38 ( 3 ): 33 - 39 .

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陈亚西 . ZrB2对轻质碳/酚醛复合材料烧蚀、隔热及力学性能影响 [D ] . 大连 : 大连理工大学 , 2013 .

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程海明 , 洪长青 , 张幸红 . 低密度烧蚀材料研究进展 [J ] . 哈尔滨工业大学学报 , 2018 , 50 ( 5 ): 1 - 11 .

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冯志海 , 师建军 , 孔磊 , 等 . 航天飞行器热防护系统低密度烧蚀防热材料研究进展 [J ] . 材料工程 , 2020 , 48 ( 8 ): 14 - 24 . DOI: 10.11868/j.issn.1001-4381.2020.000206 http://doi.org/10.11868/j.issn.1001-4381.2020.000206 当前，树脂基烧蚀防热仍被认为是最有效、最可靠、最成熟和最经济的一种热防护方式，在航天飞行器热防护系统中普遍采用。近些年在载人航天、探月工程、深空探测和新型航天飞行器系列工程的需求牵引下，本团队开发了蜂窝增强低密度材料、新型防隔热一体化材料、轻质烧蚀维形材料等先进防热复合材料，并开展了相应的应用基础以及工程应用研究工作，对烧蚀材料复杂防热机理及多重防热机制的协同作用进行了探索研究。随着再入/进入航天飞行器先进热防护系统需求的发展，功能多样化、兼容与集成是低密度树脂基烧蚀防热材料的主要发展趋势。

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国义军 , 石卫波 , 曾磊 , 等 . 高超声速飞行器烧蚀防热理论与应用 [M ] . 北京 : 科学出版社 , 2019 .

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LI W J , HUANG H M , XU X L . A coupled thermal/ fluid/ chemical/ablation method on surface ablation of charring composite [J ] . International Journal of Heat and Mass Transfer , 2017 , 109 : 725 - 736 .

LI W , ZHANG J , FANG G D , et al . Evaluation of numerical ablation model for charring composites [J ] . SCIENCE CHINA Technological Sciences , 2019 , 62 ( 8 ): 1322 - 1330 . DOI: 10.1007/s11431-018-9476-2 http://doi.org/10.1007/s11431-018-9476-2 Charring composites are widely used in the thermal protection system (TPS) to consume the intense aerodynamic heating during vehicle reentry. The ablation and thermal responses for the charring composites can be studied by using a numerical ablation model, in which the surface ablation and volume ablation could be taken into account. The coupling interactions among temperature, gas motion and interior pressure producing the pyrolysis gas could make the computation more complicated. A multi-physics model is developed to simulate the thermal response coupled with volume ablation and surface ablation. After studying four typical ablation cases, the model is validated, and then the heat transfer mechanisms in ablation are investigated. It is found that the viscous dissipation energy by the motion of pyrolysis gas can be neglected in the simulation. Also, the flow of pyrolysis gas plays an important role in the temperature response, especially under high heat flux condition.

聂春生 , 杨光 , 聂亮 , 等 . 飞行器热解炭化材料烧蚀产物对等离子体流场的影响规律 [J ] . 兵工学报 , 2022 , 43 ( 3 ): 513 - 523 . DOI: 10.12382/bgxb.2021.0161 http://doi.org/10.12382/bgxb.2021.0161 高速飞行器表面防热材料在气动加热产生的高温下会热解烧蚀，烧蚀产物进入空气边界层流场后，与流场中的高温空气发生复杂化学反应，对飞行器周围空气流场中组分浓度和等离子体分布产生影响。基于求解热化学非平衡Navier-Stokes方程，建立耦合烧蚀壁面的三维等离子体流场计算方法。理论预测电磁衰减测量项目第2次飞行试验（RAMC-II）的等离子体流场，并与飞行试验数据进行比较，验证方法的可靠性。针对升力体飞行器，分析表面材料烧蚀对等离子体流场的影响规律。结果表明：升力体头部流场的电子数密度最高，飞行器身部区域的电子密度相比头部会降低约2~3个量级，对等离子体流场贡献最重要的离子是NO + 和N + ；烧蚀产物进入流场会使激波的脱体距离变大，等离子体层厚度增加；随着流动向下游发展，飞行器身部的烧蚀速率降低，但烧蚀产物对等离子体流场的影响范围变大，飞行器身部流场的电子数密度会有一定升高；随着马赫数增大，烧蚀速率变大，壁面材料烧蚀影响更加显著，其中驻点线的峰值电子数密度改变较小，但飞行器身部对称面的电子数密度会显著增大；对于成分存在差异的同一类型防热材料，烧蚀产物进入流场后对激波脱体距离和峰值电子数密度的影响存在差异。

NIE C S , YANG G , NIE L , et al . Influence of ablation products of aircraft pyrolytic carbonized material on plasma flow field [J ] . Acta Armamentarii , 2022 , 43 ( 3 ): 513 - 523 . (in Chinese) DOI: 10.12382/bgxb.2021.0161 http://doi.org/10.12382/bgxb.2021.0161 The heat-resistant material on the surface of high-speed aircraft will decompose and ablate at the h igh temperature generated by aerodynamic heating. After entering the flow field，the ablation products react with the high-temperature air in the flow field， thus affecting the component concentration and plasma distribution in the air flow field around the aircraft. Based on solving the thermochemical non-equilibrium Navier-Stokes equations，a three-dimensional plasma flow field calculation method coupling the ablated wall surface is established. The plasma flow field of RAMC-II is predicted and compared with the flight test data to verify the reliability of the proposed method. The influence of material ablation on plasma flow field of lifting body aircraft is analyzed. The results show that the electron density in the flow field on the head of the aircraft is the highest， the electron density in the body area is reduced by two or three orders of magnitude，and NO + and N + contribute most to the electron number density in the flow field. The ablation products injected into the flow field increase the separation distance of shock wave and the thickness of plasma layer. With the development of the flow downstream，the ablation rate of the aircraft body decreases， but the influence range of ablation products on the plasma flow field becomes larger， and the electron number density of the body flow field increases to a certain extent.With the increase in Mach number， the ablation rate of wall increases， and the influence of ablation products is more obvious. The peak electron density on stagnation line changes little， but the electron number density on symmetrical surface of body increases significantly. For the same kind of ablative materials with different components， the influences of ablated products of different materials entering into the flow field on the shock wave separation distance and the peak electron number density are different.

袁野 , 王丽燕 , 曹占伟 , 等 . 碳纤维增强类复合材料烧蚀产物对等离子体流场特性影响的实验研究 [J ] . 兵工学报 , 2020 , 41 ( 2 ): 298 - 304 . DOI: 10.3969/j.issn.1000-1093.2020.02.011 http://doi.org/10.3969/j.issn.1000-1093.2020.02.011 高速飞行器表面的防热材料在气动加热产生的高温下会分解烧蚀并产生等离子体。为分析不同烧蚀条件下碳纤维增强类复合防热材料的烧蚀产物对下游流场特性的影响，利用高频等离子体风洞，采用高频感应加热方式对碳/碳和碳/碳化锆两种复合防热材料进行烧蚀并产生高速等离子体射流，在下游通过朗缪尔探针和平头柱塞量热计获得不同烧蚀状态下的流场电子数密度和驻点热流。研究结果表明：随着两种材料烧蚀率的增加，下游流场中的电子数密度和驻点热流逐渐降低，表明“黑障”风险和气动加热现象得到缓解；碳/碳化锆材料在降低下游流场的电离度和焓值方面优于碳/碳材料；随着材料前方来流焓值的增大，两种材料烧蚀造成的下游流场电离度和焓值的差异会在一定程度上缩小。

YUAN Y , WANG L Y , CAO Z W , et al . Experimental research on the influence of ablation product of carbon fiber reinforced composite material on the plasma flow field characteristics [J ] . Acta Armamentarii , 2020 , 41 ( 2 ): 298 - 304 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2020.02.011 http://doi.org/10.3969/j.issn.1000-1093.2020.02.011 The thermal protection material of high speed flight vehicle would be ablated and release the plasma under the high temperature induced by aerodynamic heating. In order to study the influence of ablation products of carbon fiber reinforced composite material on the flow field characteristics in different conditions of ablation, the high speed plasma jets were established through the ablation of two kinds of carbon fiber reinforced composite thermal protection materials (C/C and C/ZrC) in high frequency plasma wind tunnel. The number density of electrons and the stagnation point heat flux downstream were acquired using Langmuir probe and calorimeter in different conditions of ablation. The results show that the number density of electrons and the stagnation point heat flux in the flow field decrease with the increase in the ablation rate, relieving the “black-out” and aerothermal heating. C/ZrC is superior to C/C in weakening the ionization and the enthalpy of the flow field. With the increase in the enthalpy of the incoming flow, the differences in the ionization and enthalpies of the flow fields induced by the ablation of C/C and C/ZrC decrease to some extent.Key

聂春生 , 袁野 , 周禹 , 等 . 纯碳/碳材料烧蚀对飞行器等离子体流场的影响 [J ] . 兵工学报 , 2021 , 42 ( 2 ): 320 - 326 .

NIE C S , YUAN Y , ZHOU Y , et al . The influence of ablated products of pure carbon/carbon materials on plasma flow field around aircraft [J ] . Acta Armamentarii , 2021 , 42 ( 2 ): 320 - 326 . (in Chinese)

于哲峰 , 胥建宇 , 罗跃 , 等 . 高超声速飞行器烧蚀后退量时序提取及基于神经网络的预测 [J ] . 兵工学报 , 2021 , 42 ( 6 ): 1230 - 1237 . DOI: 10.3969/j.issn.1000-1093.2021.06.013 http://doi.org/10.3969/j.issn.1000-1093.2021.06.013 为了观测高超声速飞行器头部模型在高温流场下的烧蚀现象，在电弧风洞上开展了热考核试验，基于电荷耦合器件相机图像比色测温方法，获得电弧风洞烧蚀模型表面温度随时间演化数据。通过追踪模型边缘温度场变化，给出模型烧蚀过程中形变过程，提取驻点及其他边缘点后退量随时间变化数据。利用最小二乘法和长短期记忆（LSTM）网络方法对烧蚀后退量数据进行拟合与预测，其中LSTM方法主要包括网络结构设计、模型训练、目标函数设定和预测过程的算法实现等。高超声速飞行器烧蚀模型不同位置后退量时间序列预测与试验对比发现：最小二乘法主要适合烧蚀后退量为线性区域的拟合与预测；LSTM方法不但适用于烧蚀后退量线性区域，还适合于端头边缘烧蚀后退量非线性变化区域数据的拟合与预测。

YU Z F , XU J Y , LUO Y , et al . Time series extraction of ablation recession of hypersonic vehicle and its prediction based on LSTM neural network [J ] . Acta Armamentarii , 2021 , 42 ( 6 ): 1230 - 1237 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2021.06.013 http://doi.org/10.3969/j.issn.1000-1093.2021.06.013 The ablation phenomenon of hypersonic vehicle head model in high temperature flow field is studied. The thermal test is made in an arc wind tunnel. The temperature evolution data of the arc wind tunnel ablation model with time is obtained using the colorimetric temperature measurement method of CCD camera image. By tracking the change of the temperature field at the edge of the model, the deformation process of the model during ablation is given, and the time series of stagnation point and other edge points are extracted. Least squares method and long-term short-term memory(LSTM) network method are used to fit and predict the ablation recession data. The LSTM method mainly includes network structure design, network training, objective function setting and algorithm implementation of prediction process. Through comparison between the time series prediction and experiment of ablation recession at different positions of the ablation model, it is found that the least square method is mainly suitable for the fitting and prediction of ablation recession in the linear region; the LSTM method is not only suitable for the linear ablation recession, but also suitable for the fitting and prediction of the nonlinear change of ablation recession.