Entry, Descent, and Landing technological barriers and crewed MARS vehicle performance analysis

Subrahmanyam, Prabhakar; Rasky, Daniel J.

doi:10.1016/j.paerosci.2016.12.005

Cited by 14 publications

(5 citation statements)

References 30 publications

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“…始状态不确定性、环境扰动、导航控制误差等因素影响下的探测器着陆误差椭圆进行离线估计 [53] , 也可通过混沌多项式对系统不确定性随非线性动力学的传播规律进行研究 [54] , 或分析探测器在给定模型误差假设下的能控可达集, 得到能够到达指定着陆点的允许初始状态集合以及指定初始状态下的所有满足工程约束的末端状态集合 [33,55] . 其中, Long等人 [55] 针对火星大气进入段模型不确定性, 采用高斯伪谱法与序列二次规划求解轨迹优化问题, 分析了不同初始状态对着陆任务精度的影响.…”

Section: 在分析探测器着陆误差时既可采用蒙特卡罗法对初unclassified

Research progress of autonomous planetary landing site assessment and selection

Cui

Zhu

et al. 2020

Sci. Sin.-Tech.

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Section: 在分析探测器着陆误差时既可采用蒙特卡罗法对初unclassified

Research progress of autonomous planetary landing site assessment and selection

Cui

Zhu

et al. 2020

Sci. Sin.-Tech.

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“…The temperature data can also be obtained by embedding TCs within the ablative material at specified distances from the surface [19]. Identification of the heat flux of ARD [20,21] and MSL [22][23][24] was carried out by solving the inverse ablation problem based on measurements of the in-depth temperature of a sensing slug and the TPS ablation model. There was almost no temperature distribution mismatch, because the slugs were made of TPS materials.…”

Section: Long-duration Heat Load Measurement Approach By Novel Appara...mentioning

confidence: 99%

Long-duration heat load measurement approach by novel apparatus design and highly efficient algorithm

Zhu¹,

Yi²,

Meng³

et al. 2017

Meas. Sci. Technol.

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Improving the surface heat load measurement technique for vehicles in aerodynamic heating environments is imperative, regarding aspects of both the apparatus design and identification efficiency. A simple novel apparatus is designed for heat load identification, taking into account the lessons learned from several aerodynamic heating measurement devices. An inverse finite difference scheme (invFDM) for the apparatus is studied to identify its surface heat flux from the interior temperature measurements with high efficiency. A weighted piecewise regression filter is also proposed for temperature measurement prefiltering. Preliminary verification of the invFDM scheme and the filter is accomplished via numerical simulation experiments. Three specific pieces of apparatus have been concretely designed and fabricated using different sensing materials. The aerodynamic heating process is simulated by an inductively coupled plasma wind tunnel facility. The identification of surface temperature and heat flux from the temperature measurements is performed by invFDM. The results validate the high efficiency, reliability and feasibility of heat load measurements with different heat flux levels utilizing the designed apparatus and proposed method.

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“…3–5 Therefore, the structural state of TPS is of great importance to the service performance and safety of hypersonic flight vehicles. 6,7…”

Section: Introductionmentioning

confidence: 99%

“…[3][4][5] Therefore, the structural state of TPS is of great importance to the service performance and safety of hypersonic flight vehicles. 6,7 TPS can be generally divided into two classes, including reusable TPS and ablative TPS, in which the latter accommodates high heating rates and heat loads through phase change and mass loss. 8 Ablative materials have been the classical approach to TPS used for over 50 years in a broad range of applications.…”

Section: Introductionmentioning

confidence: 99%

Experimental research on online monitoring of high temperature and high speed airflow ablation of quartz ceramic thermal protection structure using guided wave

Ren

Zheng

Qiu

2023

Structural Health Monitoring

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Thermal protection structure (TPS) plays a key role in protecting hypersonic flight vehicles from harsh service environment and has been widely used. As a common ablative thermal protection material, quartz ceramic TPS realizes thermal insulation by generating ablation during the reentry phases. The structural state of quartz ceramic TPS therefore is of great importance to the service performance and safety of hypersonic flight vehicles, and shows an urgent need for structural health monitoring (SHM). However, the monitoring of real ablation of quartz ceramic structure is barely considered in the current study, let alone online monitoring under harsh service environment, which brings a great challenge to the implementation of reliable ablation monitoring. Aiming at online ablation monitoring of quartz ceramic structure, this paper performs experimental research by taking advantage of guided wave (GW)-based monitoring method. An ablation experiment and monitoring system is built to generate real ablation under high temperature and high speed airflow and perform GW monitoring. The maximal temperature of the system can reach about 2100 °C. The feasibility of ablation monitoring is verified by analyzing ablation-induced influence on GW signals. Gaussian mixture model (GMM) is adopted to combine with GW method to suppress the high temperature variation caused by uncertainty influence on GW signals during the ablation process, so that reliable monitoring of ablation can be realized. Experimental results show that online monitoring of ablation propagation of quartz ceramic structure under high temperature variation is achieved, which can be further used for ablation quantification evaluation.

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Entry, Descent, and Landing technological barriers and crewed MARS vehicle performance analysis

Cited by 14 publications

References 30 publications

Research progress of autonomous planetary landing site assessment and selection

Research progress of autonomous planetary landing site assessment and selection

Long-duration heat load measurement approach by novel apparatus design and highly efficient algorithm

Experimental research on online monitoring of high temperature and high speed airflow ablation of quartz ceramic thermal protection structure using guided wave

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