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Core-shell structured BN/SiO_(2)nanofiber membrane featuring with dual-effect thermal management and flame retardancy for extreme space thermal protection

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Science Bulletin 2025年第5期70卷 722-732页

作者： Duo Pan Ziyuan Han Junting Lei Yutao Niu Hu Liu Sunmi Shin Chuntai Liu Zhanhu Guo State Key Laboratory of Structural Analysis Optimization and CAE Software for Industrial EquipmentNational Engineering Research Center for Advanced Polymer Processing TechnologyZhengzhou UniversityZhengzhou 450001China Key Laboratory of Multifunctional Nanomaterials and Smart Systems Advanced Materials DivisionSuzhou Institute of Nano-Tech and Nano-BionicsChinese Academy of SciencesSuzhou 215123China Department of Mechanical Engineering College of Design and EngineeringNational University of SingaporeSingapore 117575Singapore Mechanical and Construction Engineering Faculty of Engineering and EnvironmentNorthumbria UniversityNewcastle Upon TyneNE18STUK

With the rapid progress of aerospace frontier engineering,the extreme space thermal environment has brought severe challenges to astronauts’space suits,putting forward higher requirements for thermal protection *** this basis,a unique core-shell structured hexagonal boron nitride(h-BN)/silicon dioxide(SiO_(2))nanofiber membrane(HS)was prepared using the coaxial electrospinning method,of which both the thermal insulation SiO_(2)nanofiber cortex and the passive radiation cooling(PRC)h-BN nanofiber core make it a promising dual-effect thermal management ***,when the amount of h-BN is 0.9 g,the resultant HS(HS0.9)exhibits astonishing low thermal conductivity of 0.026 W m−1 K−1 and high reflectivity and emissivity of exceeding 90%over an extremely wide *** expected dual-effect thermal management performance enables the HS to have an ideal cooling effect under both high sunlight intensity and strong light *** addition,HS also shows excellent flame retardant performance arising from the excellent high-temperature stability of h-BN and SiO_(2).What is more,the tensile strength of HS0.9 was also significantly increased from 0.42 to 7.2 MPa by encapsulating polyimide through vacuum ***,the research results of this work provide innovative highlights for high-temperature protection in daily life and even extreme space environments.

关键词： h-BN/SiO_(2)nanofiber membrane Core-shell structure Passive radiative cooling Thermal insulation Flame retardancy

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design of a small-size retarding potential analyzer and a practice of plasma beam energy diagnosis

Design of a small-size retarding potential analyzer and a pr...

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IEEE International Conference on Plasma Science (ICOPS)

作者： X. Wu J. Qi Y. Wang J. Ren Z. Zhang G. Zhang H. Deng W. Wang H. Tang School of Energy and Power Engineering Beihang University Beijing China School of Space and Environment Beihang University Beijing China School of Astronautics Beihang University Beijing China Ministry of Education Key Laboratory of Spacecraft Design Optimization & Dynamic Simulation Technologies Beijing China

ISBN: (数字)9798350360912

ISBN: (纸本)9798350360929

To reduce the perturbation of the probe to the plasma beam, improve the spatial resolution of Ion Energy Distribution Function (IEDF) measurements, and adapt to the needs of miniaturized electric thruster diagnostics, a miniaturized Retarding Potential Analyzer (RPA) is designed. In this paper, based on the RPA design criteria, the mesh and spacing of the small-size grid are determined by analyzing the electron density, temperature, and sheath thickness in the plasma beam obtained from Langmuir probe measurements. In this way, a miniaturized three-grid RPA is designed with an overall size of less than 30 $\mathrm{mm} \times 20 \mathrm{~mm} \times 11 \mathrm{~mm}$. This RPA enables high spatial resolution and high accuracy measurement of IEDF in plasma beam with ion energy up to 800 eV and repeatability accuracy better than 0.5 eV. It has been applied to the diagnosis of ion energy in electric thruster beams. In this work, the spatial distributions of ion energy, plasma density, and electron temperature in the beams of the Kaufman ion source at different accelerating voltages and gas flow rates are measured using RPA and Langmuir single probe, and the axial distribution of ion energy and the evolution laws of the Kaufman ion source beam are analyzed.

关键词： Temperature measurement Voltage measurement Particle beam measurements Energy measurement Ion sources Plasmas Probes

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A plasma equilibrium model for rapid estimation of SF-MPDT performance

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Plasma Science and Technology 2021年第10期23卷 40-48页

作者： Yifeng Fu Cheng Zhou Peng Wu Zhongkai Zhang Zun Zhang Haibin Tang School of Space and Environment Beihang UniversityBeijing 100191People's Republic of China Beijing Institute of Control Engineering Beijing 100094People’s Republic of China School of Astronautics Beihang UniversityBeijing 100191People’s Republic of China Key Laboratory of Spacecraft Design Optimization&Dynamic Simulation Technologies Ministry of EducationBeijing 100083People’s Republic of China Laboratory of Space Environment Monitoring and Information Processing Ministry of Industry and Information TechnologyBeijing 100083People's Republic of China

In this work, a zero-dimensional plasma model for self-field magnetoplasmadynamic thrusters(SF-MPDTs) is proposed, which is based on the ion-number balance equation and energy balance equation, and can calculate the average electron temperature and the average ion temperature inside the discharge chamber conveniently. At the same time, the model can also predict the thruster performance, and the thruster performance predicted by the model is compared with experimental results, which proved the reliability of the model.

关键词： SF-MPDT plasma equilibrium diffusion equation thruster parameters

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design and fabrication of a full elastic sub-micron-Newton scale thrust measurement system for plasma micro thrusters

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Plasma Science and Technology 2021年第10期23卷 29-39页

作者： Zhongkai Zhang Guanrong Hang Jiayun Qi Zun Zhang Zhe Zhang Jiubin Liu Wenjiang Yang Haibin Tang School of Space and Environment Beihang UniversityBeijing 100191People's Republic of China Shanghai Institute of Space Propulsion Shanghai Engineering Research Center of Space EngineShanghai 201112People's Republic of China School of Astronautics Beihang UniversityBeijing 100191People's Republic of China The Institute of Space Systems University of StuttgartStuttgart D-70569GermanyBeijing 100083People's Republic of China Key Laboratory of Spacecraft Design Optimization&Dynamic Simulation Technologies Ministry of EducationBeijing 100083People's Republic of China Laboratory of Space Environment Monitoring and Information Processing Ministry of Industry and Information TechnologyBeijing 100083People’s Republic of China

In this work,a force measurement system is proposed to measure the thrust of plasma microthruster with thrust magnitude ranging from sub-micro-Newtons to hundreds *** thrust measurement system uses an elastic torsional pendulum structure with a capacitance sensor to measure the displacement,which can reflect the position change caused by the applied force perpendicular to the pendulum *** the open-loop mode,the steady-state thrust or the impulse of the plasma micro-thruster can be obtained from the swing of the pendulum,and in the closed-loop mode the steady-state thrust can be obtained from the feedback force that keeps the pendulum at a specific *** thrust respond of the system was calibrated using an electrostatic weak force generation *** results show that the system can measure a thrust range from 0 to 200μN in both open-loop mode and closed-loop mode with a thrust resolution of 0.1μN,and the system can response to a pulse bit at the magnitude of 0.1 m N s generated by a micro cathode arc *** background noise of the closed-loop mode is lower than that of the open-loop mode,both less than 0.1 m N/Hz in the range of 10 mHz to 5 Hz.

关键词： plasma thruster micro-thrust measurement torsional pendulum

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Cathode erosion site distributions in an applied-field magnetoplasmadynamic thruster

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Plasma Science and Technology 2020年第9期22卷 59-65页

作者： Peng WU Yibai WANG Yong LI Baojun WANG Kaiyu ZHANG Haibin TANG Jinbin CAO School of Astronautics Beihang UniversityBeijing 100191People's Republic of China Beijng Institute of Control Engineering Beijing 100190People’s Republic of China School of Space and Environment Beihang UniversityBeijing 100191People's Republic of China Key Laboratory of Spacecraft Design Optimization&Dynamic Simulation Technologies Ministry of EducationBeijing 100083People’s Republic of China Laboratory of Space Environment Monitoring and Information Processing Ministry of Industry and Information TechnologyBeijing 100083People's Republic of China

Erosion can influence cathode life,and is thus considered to be one of the main factors limiting the application of applied-field magnetoplasmadynamic *** this paper,erosion sites on graphite cathodes are studied so as to identify the influence of applied magnetic field and the ratio of propellant mass flow rate supplied from cathode and *** experiment results show that the application of applied magnetic field can significantly reduce the erosion rate of the cathode compared to that without magnetic *** erosion sites on the cathode vary with the relative position of the convergent-divergent magnetic field,and are mainly distributed in the divergent part of the *** erosion sites on the cathodes are found to be related to the propellant *** decreasing anode mass flow rate enlarges the range of *** results are much helpful for the analysis of cathode erosion site location since they provide evidences of erosion mechanisms and point out the directions for further research.

关键词： electric propulsion applied-field magnetoplasmadynamic thruster cathode erosion magnetic field propellant mass flow rate

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High-Resolution Particle Density Measurement for Argon Plasma Plume by Image Reconstruction and Collisional-Radiative Model

SSRN

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SSRN 2022年

作者： Han, Xing Wang, Yimeng Chen, Zhiyuan Wang, Yibai Wu, Jianjun Tang, Haibin Cao, Jinbin School of Space and Environment Beihang University Beijing100083 China School of Astronautics Beihang University Beijing100083 China Key Laboratory of Spacecraft Design Optimization and Dynamic Simulation Technologies of the Ministry of Education Beihang University Beijing100083 China Aircraft and Propulsion Laboratory Ningbo Institute of Technology Beihang University Ningbo315100 China College of Aerospace Science and Engineering National University of Defense Technology Changsha410073 China Laboratory of Space Environment monitoring and Information Processing Ministry of Industry and Information Technology Beijing100083 China

A measurement method of the high-resolution atom and ion density distributions based on the image reconstruction and collisional-radiative model is presented and could apply to the parameter measurement of the axisymmetric argon plasma plume. The projection integral signals of two-band ion spectral lines and one-band atom spectral line are acquired, and the spatial distribution of the light intensity signals are obtained by the image reconstruction technique. The collisional-radiative model includes the major atomic levels and singly ionized argon levels, taking into account electron-impact excitation and ionization, electron-impact deexcitation, three-body recombination processes to obtain the theoretical signal intensity in the wavelength bands as a function of electron temperature, electron density, and atom density. The plasma parameters are determined by the theoretical signal intensity and spatial light intensity with the three filters, and the common coefficient is calibrated by the known parameters of some positions. The method was applied to the plume region of an applied-field magnetoplasmadynamic thruster to verify the feasibility of this method in comparison with the electrostatic probe, and the plasma parameters with a spatial resolution of 0.81 mm/pixel were obtained finally. © 2022, The Authors. All rights reserved.

关键词： Argon

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Electric potential barriers in the magnetic nozzle

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Physical Review E 2020年第5期101卷 053208-053208页

作者： Zhiyuan Chen Yibai Wang Haibin Tang Junxue Ren Min Li Zhe Zhang Shuai Cao Jinbin Cao School of Astronautics Beihang University Beijing 100083 China School of Space and Environment Beihang University Beijing 100083 China Key Laboratory of Spacecraft Design Optimization and Dynamic Simulation Technologies of the Ministry of Education Beihang University Beijing 100083 China Laboratory of Space Environment monitoring and Information Processing Ministry of Industry and Information Technology Beijing 100083 China Shanghai Engineering Centre for Microsatellites Chinese Academy of Sciences Shanghai 201203 China School of Instrumentation and Optoelectronic Engineering Beihang University Beijing 100083 China

Magnetic nozzles are convergent-divergent applied magnetic fields which are commonly used in electric propulsion, manufacturing, and material processing industries. This paper studies the previously overlooked physics in confining the thermalized ions injected from a near-uniform inlet in the magnetic nozzle. Through fully kinetic planar-3V particle-in-cell (PIC) modeling and simulation, an electric potential barrier is found on the periphery of the nozzle throat, which serves to confine the thermalized ions by the electric force. With the initial thermal energy as driving force and insufficient magnetic confinement, the ions overshoot the most divergent magnetic line, which results in the accumulation of positive space charges around the throat. The accumulated charges would create an ion-confining potential barrier with limited extent. Apart from the finite-electron Larmor radius (FELR) effect, two more factors are put forward to account for the limited extent of the potential barrier: the depletion of ion thermal energy and the short-circuiting effect. The influences of inlet temperature ratio of ions to electrons and magnetic inductive strength B0 are quantitively investigated using the PIC code. The results indicate that the potential barrier serves as a medium to transfer the gas dynamic thrust to the magnetic nozzle while providing constrain to the ions, like the solid wall in a de Laval nozzle. In high-B0 regime, the finite-ion Larmor radius (FILR) effect becomes dominant rather than the FELR effect in the plasma confinement of magnetic nozzles.

关键词： Particle acceleration in plasmas Plasma thermodynamics Plasma transport

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Application of the view factor model on the particle-in-cell and Monte Carlo collision code

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Physical Review E 2020年第3期102卷 033311-033311页

作者： Ruojian Pan Junxue Ren Haibin Tang Shuai Cao Juan Li Zhe Zhang Jun Zhou Jinbin Cao School of Space and Environment Beihang University Beijing 100083 China School of Astronautics Beihang University Beijing 100083 China Key Laboratory of Spacecraft Design Optimization and Dynamic Simulation Technologies Ministry of Education Beijing 100083 China Laboratory of Space Environment monitoring and Information Processing Ministry of Industry and Information Technology Beijing 100083 China National Key Laboratory of Science and Technology on Vacuum Technology & Physics Lanzhou Institute of Physics Lanzhou 730000 China School of Instrumentation and Optoelectronic Engineering Beihang University Beijing 100083 China

Particle-in-cell and Monte Carlo collision (PIC-MCC) has been widely adopted as a simulation method for electric propulsion. However, neutral atoms move much more slowly than other species, which can cause a serious reduction in simulation speed. In this work, we investigate the view factor model in combination with the PIC-MCC method and propose a method for simulating three-dimensional neutral atoms. The accuracy of the PIC-MCC method can be significantly improved by updating the neutral distribution periodically. We compare the computational results with the fixed-neutral PIC-MCC model of the miniature ring-cusp discharge experiment at the University of California, Los Angeles (UCLA). The plasma distribution and potential distribution of the simulation match well with the UCLA experimental data. Compared with the fixed-neutral model, the view factor model increases the simulation time by only 33% while it improves the distribution accuracy of neutrals, plasma density, and electric potential, and reduces the simulation errors of discharge current and discharge power from 19.8% to 9.8%. The accuracy of PIC-MCC simulation has been improved at the expense of slightly increasing the computational time.

关键词： Particle-in-cell methods

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Improvements in miniaturized Hall Thrusters by use of high-temperature SmCo magnets and additive manufacturing techniques

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IOP Conference Series: Materials Science and engineering 2019年第1期576卷

作者： A Olano J Ren G Zhang H Tang T Zhang J Li Key Laboratory of Spacecraft Design Optimization & Dynamic Simulation Technologies of Ministry of Education School of Astronautics Beihang University Beijing 100191 People's Republic of China Key Laboratory of Spacecraft Design Optimization & Dynamic Simulation Technologies of Ministry of Education School of Space and Environment Beihang University Beijing 100191 People's Republic of China School of Materials Science and Engineering Beihang University Beijing 100191 People's Republic of China Science and Technology on Vacuum Technology and Physics Laboratory Lanzhou Institute of Physics Lanzhou 730000 People's Republic of China

This work presents the difficulties associated with the miniaturization of Hall Thruster engines and how state of the art materials and new manufacture techniques can potentially solve these problems. Hall Thrusters are electric propulsion systems that require specific magnetic field topography and uniform propellant distribution for optimal operation which is difficult to achieve with typical materials and by conventional manufacturing methods in miniaturized engines. To keep the optimal magnetic field distribution at small thruster sizes, it is shown that new alloys of SmCo permanent magnets can generate the desired magnetic field distribution and that their high-temperature resistance properties assure its operation temperature will be under the maximum operational temperature. In addition, whereas for the small dimensions required for the anode traditional manufacture methods only allow for simple designs, it is explained how the implementation of 3D-printing techniques can improve the uniformity in the azimuthal distribution of the propellant by allowing complex geometries in the design of the anode that are unattainable with traditional manufacturing.

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Publisher Correction: The Scales Project, a cross-national dataset on the interpretation of thermal perception scales

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Scientific data 2020年第1期7卷 11页

作者： Marcel Schweiker Amar Abdul-Zahra Maíra André Farah Al-Atrash Hanan Al-Khatri Rea Risky Alprianti Hayder Alsaad Rucha Amin Eleni Ampatzi Alpha Yacob Arsano Montazami Azadeh Elie Azar Bannazadeh Bahareh Amina Batagarawa Susanne Becker Carolina Buonocore Bin Cao Joon-Ho Choi Chungyoon Chun Hein Daanen Siti Aisyah Damiati Lyrian Daniel Renata De Vecchi Shivraj Dhaka Samuel Domínguez-Amarillo Edyta Dudkiewicz Lakshmi Prabha Edappilly Jesica Fernández-Agüera Mireille Folkerts Arjan Frijns Gabriel Gaona Vishal Garg Stephanie Gauthier Shahla Ghaffari Jabbari Djamila Harimi Runa T Hellwig Gesche M Huebner Quan Jin Mina Jowkar Renate Kania Jungsoo Kim Nelson King Boris Kingma M Donny Koerniawan Jakub Kolarik Shailendra Kumar Alison Kwok Roberto Lamberts Marta Laska M C Jeffrey Lee Yoonhee Lee Vanessa Lindermayr Mohammadbagher Mahaki Udochukwu Marcel-Okafor Laura Marín-Restrepo Anna Marquardsen Francesco Martellotta Jyotirmay Mathur Gráinne McGill Isabel Mino-Rodriguez Di Mou Bassam Moujalled Mia Nakajima Edward Ng Marcellinus Okafor Mark Olweny Wanlu Ouyang Ana Ligia Papst de Abreu Alexis Pérez-Fargallo Indrika Rajapaksha Greici Ramos Saif Rashid Christoph F Reinhart Ma Isabel Rivera Mazyar Salmanzadeh Karin Schakib-Ekbatan Stefano Schiavon Salman Shooshtarian Masanori Shukuya Veronica Soebarto Mohammad Tahsildoost Federico Tartarini Despoina Teli Priyam Tewari Samar Thapa Maureen Trebilcock Jörg Trojan Ruqayyatu B Tukur Conrad Voelker Yeung Yam Liu Yang Gabriela Zapata-Lancaster Yongchao Zhai Yingxin Zhu Zahra Sadat Zomorodian Building Science Group Karlsruhe Institute of Technology Englerstr. 7 76131 Karlsruhe Germany. marcel.schweiker@kit.edu. WIN-Kolleg Thermal comfort and pain Heidelberg Academy of Sciences and Humanities Karlstr. 4 69117 Heidelberg Germany. marcel.schweiker@kit.edu. Mechanical Engineering Department University of Technology Iraq Al sinaea 10066 Baghdad Iraq. CTC/Department of Civil Engineering Federal University of Santa Catarina Rua João Pio Duarte Silva s/n. Córrego Grande 88.040-901 Florianópolis SC Brazil. School of Architecture and Built Environment German Jordanian University Darat Othman Bdeir 11180 Amman Jordan. Civil and Architectural Engineering Department Sultan Qaboos University Al-Khod P.O. Box: 33 PC: 123 Muscat Oman. Laboratory of Building Technology Department of Architecture Institut Teknologi Bandung Ganesha 10 40132 Bandung Indonesia. Department of Building Physics Bauhaus-University Weimar Coudraystr. 11A 99423 Weimar Germany. Energy & Climate Change Group Faculty of Engineering & Physical Sciences University of Southampton University Road SO17 1BJ Southampton United Kingdom. Welsh School of Architecture Cardiff University King Edward VII Avenue CF10 3NB Cardiff United Kingdom. Department of Architecture Massachusetts Institute of Technology Massachusetts Ave 02139 Cambridge United States of America. Faculty of Engineering Environment and Computing BNE Research Centre Coventry University Gulson road CV1 2JH Coventry United Kingdom. Industrial and Systems Engineering Khalifa University Masdar Campus Building 1B 54224 Abu Dhabi United Arab Emirates. Architecture University of Tehran Kish International Campus Niyayesh St. Mirmohanna Blvd 79416-55665 Kish Iran. Department of Architecture Ahmadu Bello University Zaria Nigeria Samaru Zaria Nigeria. WIN-Kolleg Thermal comfort and pain Heidelberg Academy of Sciences and Humanities Karlstr. 4 69117 Heidelberg Germany. Department of Cognitive and Clinical Neurosci

An amendment to this paper has been published and can be accessed via a link at the top of the paper.

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