The Global Energy Interconnection Conference will be held in Mar.2019 in Beijing,China. We are collecting research papers worldwide to publish a special issue.1 New Energy Generation Design and Equipment Development o...The Global Energy Interconnection Conference will be held in Mar.2019 in Beijing,China. We are collecting research papers worldwide to publish a special issue.1 New Energy Generation Design and Equipment Development of Photovoltaic, Photothermal, Wind and other New Energy Generation Systems,New Energy Generation Simulation and Planning, Test and Inspection Technology, Power Prediction and展开更多
Oxygen(O_(2))is essential for life support and rocket propulsion in Mars exploration missions,and in situ oxygen production from the Martian atmosphere is of profound scientific and engineering significance.In this ar...Oxygen(O_(2))is essential for life support and rocket propulsion in Mars exploration missions,and in situ oxygen production from the Martian atmosphere is of profound scientific and engineering significance.In this article,we propose a novel method for O_(2) production from the Martian atmosphere by using glow discharge ionization combined with a self-developed oxygen-permeable membrane(OPM).Experiments under simulated Martian atmospheric conditions examined parameter impacts on the O_(2) production rate and assessed the operating characteristics and glow discharge plasma tolerance of the OPM.Results indicate that(1)the proportion of O_(2) produced positively correlates with the ionization voltage under fixed discharge electrode spacing,pressure,and flow rate,reaching a maximum of 8.18%(saturating at 4600–5400 V);(2)O_(2) yield rises with the carbon dioxide(CO_(2))flow rate at a constant pressure,with the maximum value reaching 0.5 g/h;(3)titanium(Ti)and molybdenum(Mo)electrodes exhibit higher application potential under high voltage conditions;(4)the OPM operates at temperatures above 800℃ and shows few changes in the main body sections after 24 h of plasma tolerance testing.This study lays the foundation for future development of a mature Mars oxygen production prototype with lower energy consumption and higher efficiency.展开更多
The parachute deployment conditions during the terminal entry phase in Mars landing missions exhibit critical impact on landing precision.In this article,aiming at the requirements of safe parachute deployment and acc...The parachute deployment conditions during the terminal entry phase in Mars landing missions exhibit critical impact on landing precision.In this article,aiming at the requirements of safe parachute deployment and accurate landing,a multidimensional parachute deployment box for determining deployment condition during Mars landing was proposed.First,an extremerange optimization model was established,synthesizing the dynamics and constraints of both parachute descent and powered descent phases.Then,on the basis of the two-dimensional altitude-velocity deployment box,a multi-dimensional parachute deployment box characterized by altitude,velocity,flight-path angle,and extreme range was constructed through the integration of extreme range information.Furthermore,an evaluation index for landing precision was formulated and a deployment control logic was proposed for minimizing landing deviation.Finally,the proposed deployment box was simulated in a Mars landing mission.The results demonstrate that the proposed box effectively satisfies safe deployment and landing precision demands,eliminating the range-to-go error at the terminal of the entry phase.展开更多
Dear Editor,This letter proposes a convex optimization-based model predictive control(MPC)autonomous guidance method for the Mars ascent vehicle(MAV).We use the modified chebyshev-picard iteration(MCPI)to solve optimi...Dear Editor,This letter proposes a convex optimization-based model predictive control(MPC)autonomous guidance method for the Mars ascent vehicle(MAV).We use the modified chebyshev-picard iteration(MCPI)to solve optimization sub-problems within the MPC framework,eliminating the dynamic constraints in solving the optimal control problem and enhancing the convergence performance of the algorithm.Moreover,this method can repeatedly perform trajectory optimization calculations at a high frequency,achieving timely correction of the optimal control command.Numerical simulations demonstrate that the method can satisfy the requirements of rapid computation and reliability for the MAV system when considering uncertainties and perturbations.展开更多
In this study, we present an innovative Mars Ionosphere-Thermosphere Model(MITM), which is a time-dependent, threedimensional(3-D) model that comprehensively represents the self-consistently coupled thermosphere and i...In this study, we present an innovative Mars Ionosphere-Thermosphere Model(MITM), which is a time-dependent, threedimensional(3-D) model that comprehensively represents the self-consistently coupled thermosphere and ionosphere of Mars within the altitude range of 70-300 km. The model incorporates an extensive range of parameters, including neutral number densities of CO_(2), CO,O, O_(2), N_(2), NO, N(^(2)D), N(^(4)S), Ar, and He;ion number densities of CO_(2)^(+), CO^(+), O^(+), O_(2)^(+), N_(2)^(+), NO^(+), N^(+) ions, and electrons;neutral temperature;and neutral wind fields. The MITM code employs a high-resolution grid system in a spherical geographical coordinate system, with a horizontal resolution of 5° latitude by 7.5° longitude. This altitude-resolved grid system enables accurate depiction of spatial variations in the Martian thermosphere and ionosphere. To showcase the capabilities of the MITM, we present two simulation cases: one during the equinox and another during the solstice. Both simulations reproduce key features of the Martian thermosphere and ionosphere including the characteristics of horizontal circulation, diurnal variations in chemical composition, and distribution of electron density. The MITM offers a robust framework for understanding the intricate interactions and processes that shape the Mars thermosphere and ionosphere,which are crucial for enhancing our understanding of Martian upper atmosphere and ionosphere.展开更多
文摘The Global Energy Interconnection Conference will be held in Mar.2019 in Beijing,China. We are collecting research papers worldwide to publish a special issue.1 New Energy Generation Design and Equipment Development of Photovoltaic, Photothermal, Wind and other New Energy Generation Systems,New Energy Generation Simulation and Planning, Test and Inspection Technology, Power Prediction and
基金supported by the Open Fund of the National Key Laboratory of Deep Space Exploration(No.NKDSEL2024004-2)the National Natural Science Foundation of China(No.42173045)supported by the Shandong Provincial Natural Science Foundation(No.ZR2025QC448).
文摘Oxygen(O_(2))is essential for life support and rocket propulsion in Mars exploration missions,and in situ oxygen production from the Martian atmosphere is of profound scientific and engineering significance.In this article,we propose a novel method for O_(2) production from the Martian atmosphere by using glow discharge ionization combined with a self-developed oxygen-permeable membrane(OPM).Experiments under simulated Martian atmospheric conditions examined parameter impacts on the O_(2) production rate and assessed the operating characteristics and glow discharge plasma tolerance of the OPM.Results indicate that(1)the proportion of O_(2) produced positively correlates with the ionization voltage under fixed discharge electrode spacing,pressure,and flow rate,reaching a maximum of 8.18%(saturating at 4600–5400 V);(2)O_(2) yield rises with the carbon dioxide(CO_(2))flow rate at a constant pressure,with the maximum value reaching 0.5 g/h;(3)titanium(Ti)and molybdenum(Mo)electrodes exhibit higher application potential under high voltage conditions;(4)the OPM operates at temperatures above 800℃ and shows few changes in the main body sections after 24 h of plasma tolerance testing.This study lays the foundation for future development of a mature Mars oxygen production prototype with lower energy consumption and higher efficiency.
基金Supported by the National Natural Science Foundation of China(62073034)。
文摘The parachute deployment conditions during the terminal entry phase in Mars landing missions exhibit critical impact on landing precision.In this article,aiming at the requirements of safe parachute deployment and accurate landing,a multidimensional parachute deployment box for determining deployment condition during Mars landing was proposed.First,an extremerange optimization model was established,synthesizing the dynamics and constraints of both parachute descent and powered descent phases.Then,on the basis of the two-dimensional altitude-velocity deployment box,a multi-dimensional parachute deployment box characterized by altitude,velocity,flight-path angle,and extreme range was constructed through the integration of extreme range information.Furthermore,an evaluation index for landing precision was formulated and a deployment control logic was proposed for minimizing landing deviation.Finally,the proposed deployment box was simulated in a Mars landing mission.The results demonstrate that the proposed box effectively satisfies safe deployment and landing precision demands,eliminating the range-to-go error at the terminal of the entry phase.
基金supported by the National Defense Basic Scientific Research Program(JCKY2021603B030)the National Natural Science Foundation of China(62273118,12150008)the Natural Science Foundation of Heilongjiang Province(LH2022F023).
文摘Dear Editor,This letter proposes a convex optimization-based model predictive control(MPC)autonomous guidance method for the Mars ascent vehicle(MAV).We use the modified chebyshev-picard iteration(MCPI)to solve optimization sub-problems within the MPC framework,eliminating the dynamic constraints in solving the optimal control problem and enhancing the convergence performance of the algorithm.Moreover,this method can repeatedly perform trajectory optimization calculations at a high frequency,achieving timely correction of the optimal control command.Numerical simulations demonstrate that the method can satisfy the requirements of rapid computation and reliability for the MAV system when considering uncertainties and perturbations.
基金This work is supported by the B-type Strategic Priority Program of the Chinese Academy of Sciences (Grant No. XDB4100000)the pre-research Project on Civil Aerospace Technologies No. D020105 funded by CNSAthe Strategic Priority Research Program of Chinese Academy of Sciences (Grant XDA17010404, XDA17010201)。
文摘In this study, we present an innovative Mars Ionosphere-Thermosphere Model(MITM), which is a time-dependent, threedimensional(3-D) model that comprehensively represents the self-consistently coupled thermosphere and ionosphere of Mars within the altitude range of 70-300 km. The model incorporates an extensive range of parameters, including neutral number densities of CO_(2), CO,O, O_(2), N_(2), NO, N(^(2)D), N(^(4)S), Ar, and He;ion number densities of CO_(2)^(+), CO^(+), O^(+), O_(2)^(+), N_(2)^(+), NO^(+), N^(+) ions, and electrons;neutral temperature;and neutral wind fields. The MITM code employs a high-resolution grid system in a spherical geographical coordinate system, with a horizontal resolution of 5° latitude by 7.5° longitude. This altitude-resolved grid system enables accurate depiction of spatial variations in the Martian thermosphere and ionosphere. To showcase the capabilities of the MITM, we present two simulation cases: one during the equinox and another during the solstice. Both simulations reproduce key features of the Martian thermosphere and ionosphere including the characteristics of horizontal circulation, diurnal variations in chemical composition, and distribution of electron density. The MITM offers a robust framework for understanding the intricate interactions and processes that shape the Mars thermosphere and ionosphere,which are crucial for enhancing our understanding of Martian upper atmosphere and ionosphere.
