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Uncertainty quantification for the ascent phase of launch vehicles using Bayesian inference 认领 引用
1
作者 CHAO Tao LI Xiaonan +2 位作者 SHANG Xiaobing MA Ping YANG Ming 《Journal of Systems Engineering and Electronics》 SCIE CSCD 2026年第2期485-503,共19页
The launch process of a multi-stage launch vehicle is significantly influenced by uncertain parameters,including air density,aerodynamic parameters,and engine thrust,which often exhibit deviation.Predicting the trajec... The launch process of a multi-stage launch vehicle is significantly influenced by uncertain parameters,including air density,aerodynamic parameters,and engine thrust,which often exhibit deviation.Predicting the trajectory range of the launch vehicle under the influence of uncertainty is essential before launch,and uncertainty quantification serves as a crucial method to address this challenge.In traditional uncertainty quantification for launch vehicles,unknown parameters are often assigned specific distributions based on prior knowledge.However,prior knowledge is sometimes subjective,and unknown parameters are often assigned conservative ranges to meet safety margins.In addition,the flight data of the past launch is precious,especially in quantifying the uncertainty of reusable or same-type launch vehicles.This paper utilizes flight data to estimate parameters base on Bayesian methods and integrates the estimation results with prior knowledge,which can more objectively set the distribution of uncertain parameters.Reasonable distribution has a positive impact on uncertainty quantification,which can avoid control strategies that are not robust enough or overly redundant.Therefore,the uncertainty quantification for launch vehicles is discussed under different information sources.In addition,the algorithm is accelerated based on Gaussian process regression and polynomial chaos expansions. 展开更多
关键词 launch vehicle uncertainty quantification Bayesian inference launch experience Gaussian process regression polynomial chaos expansions
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Dynamic Response of Triceratops with Elliptical Legs under Oblique Space Launches 认领 引用
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作者 Srinivasan Chandrasekaran Puliparambil Unnikrishnan Ashish 《哈尔滨工程大学学报（英文版）》 CSCD 2026年第2期491-507,共17页
The offshore triceratops platform has emerged as a promising candidate for maritime launches due to its innovative and unique responsive characteristics.Their form-dominant design facilitates dynamic equilibrium and e... The offshore triceratops platform has emerged as a promising candidate for maritime launches due to its innovative and unique responsive characteristics.Their form-dominant design facilitates dynamic equilibrium and effectively controls the impact of the deck’s rotational motion during sea-borne launch.A parametric study examines how the shape of buoyant legs influences the dynamic response during rocket launches,utilizing ANSYS AQWA for analysis.The study finds that elliptical legs with an eccentricity of 2 reduce deck responses.While the deck rotation is driven by the quasi-static rocket thrust and the differential heave of the legs,the pitch response arises from the waves and is reduced by using elliptical legs.Numerical studies conducted during rocket launches show an amplified deck response.The vertical force on the deck is maximized during vertical launches and minimized during 30°launches.The pitch moment on the deck increases with launch eccentricity,which is attributed to the cantilever effect of the launch platform. 展开更多
关键词 Triceratops Marine space launch Elliptical legs Oblique rocket launch Dynamic analysis Form dominant response control Compliant platform
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Collaborative scheduling problem pertaining to launch and recovery operations for carrier aircraft 认领 引用
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作者 GUO Fang HAN Wei +3 位作者 LIU Yujie SU Xichao LIU Jie LI Changjiu 《Journal of Systems Engineering and Electronics》 SCIE CSCD 2026年第1期287-306,共20页
The proliferation of carrier aircraft and the integration of unmanned aerial vehicles(UAVs)on aircraft carriers present new challenges to the automation of launch and recovery operations.This paper investigates a coll... The proliferation of carrier aircraft and the integration of unmanned aerial vehicles(UAVs)on aircraft carriers present new challenges to the automation of launch and recovery operations.This paper investigates a collaborative scheduling problem inherent to the operational processes of carrier aircraft,where launch and recovery tasks are conducted concurrently on the flight deck.The objective is to minimize the cumulative weighted waiting time in the air for recovering aircraft and the cumulative weighted delay time for launching aircraft.To tackle this challenge,a multiple population self-adaptive differential evolution(MPSADE)algorithm is proposed.This method features a self-adaptive parameter updating mechanism that is contingent upon population diversity,an asynchronous updating scheme,an individual migration operator,and a global crossover mechanism.Additionally,comprehensive experiments are conducted to validate the effectiveness of the proposed model and algorithm.Ultimately,a comparative analysis with existing operation modes confirms the enhanced efficiency of the collaborative operation mode. 展开更多
关键词 carrier aircraft collaborative scheduling problem launch recovery multiple population differential evolution
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Bi-objective optimization of orbital transfer vehicle based launch and deployment process for LEO constellation 认领 引用
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作者 Peng HAN Chao HUANG +1 位作者 Chuanjiang LI Yanning GUO 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第6期578-597,共20页
This paper addresses the optimization of Launch and Deployment(L&D)strategies for Low Earth Orbit(LEO)satellite constellations using Orbital Transfer Vehicles(OTVs).The problem is formulated as a bi-objective comb... This paper addresses the optimization of Launch and Deployment(L&D)strategies for Low Earth Orbit(LEO)satellite constellations using Orbital Transfer Vehicles(OTVs).The problem is formulated as a bi-objective combinatorial optimization model that simultaneously minimizes the number of launches and the average fuel consumption,thereby reducing launch costs and improving mission reliability.To enhance solution diversity,the∊-constraint method is employed to decompose the original problem into a series of constrained single-objective subproblems.A Cluster and Nearest Sorting initialized Genetic Algorithm with Local Search(CNS-LSGA)is developed to efficiently solve these subproblems.The CNS initialization mechanism is specifically designed to avoid infeasible solutions caused by limited OTV fuel and the high fuel requirements of LEO orbital maneuvers,while two local search operators are incorporated to improve local exploitation.Comparative evaluations across three LEO constellation architectures demonstrate that the proposed framework is both effective and robust,and can consistently obtain greater solution diversity and higher-quality results than the established population-based multi-objective algorithms. 展开更多
关键词 Launch and deployment Bi-objective optimization Orbital transfer vehicle Low Earth Orbit(LEO)constellation e-constraint method Genetic algorithm
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Multi-Phase CFD Simulation of Lifeboat Free-Fall Launch Dynamics with Varying Pitch Angles 认领 引用 被引量：1
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作者 M.Silveira S.Wang C.Guedes Soares 《哈尔滨工程大学学报（英文版）》 CSCD 2026年第3期657-668,共12页
The objective of this study is to simulate the free-fall launch of a lifeboat and to analyse its trajectory,pitch angle,velocity,acceleration,and pressure dynamics using Open Field Operation and Manipulation(OpenFOAM)... The objective of this study is to simulate the free-fall launch of a lifeboat and to analyse its trajectory,pitch angle,velocity,acceleration,and pressure dynamics using Open Field Operation and Manipulation(OpenFOAM).Utilising the overset grid technique,which is well-suited for handling the expected large motions,the study employs multi-phase simulations based on the volume of fluid method.A series of 21 simulations is conducted,varying initial pitch angles and three different drop heights to thoroughly examine the lifeboat's behaviour under various conditions.The analysis of pressure across multiple points along the same transversal and longitudinal planes reveals two significant pressure peaks:one at the bow during water entry and another at the stern,occurring after a secondary water entry triggered by turn-back spins due to restoring moments.Pressure contours indicate that the keel experiences the highest loads,highlighting it as a critical area of concern.Additionally,the kinematics of each scenario is analysed to determine which initial pitch angle would allow the lifeboat to distance itself most effectively from potential hazards without additional impulse.This aspect of the study aims to identify optimal launch conditions that enhance safety and minimise risk during emergency deployments. 展开更多
关键词 CFD simulation Water entry Free-fall launch Lifeboat Overset mesh
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Numerical approach for radiative-heat-transfer of a reusable liquid-propellant launch vehicle 认领 引用
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作者 Zhenhua ZHOU Qian WAN +2 位作者 Lei SHI Guang ZUO Yuhong CUI 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第1期95-110,共16页
The radiative heat flux of the plume from reusable rockets is a critical parameter during the launch and return processes.This paper proposes a method for calculating radiative heat flux with higher accuracy than prev... The radiative heat flux of the plume from reusable rockets is a critical parameter during the launch and return processes.This paper proposes a method for calculating radiative heat flux with higher accuracy than previously reported for a recoverable nine-engine liquid-propellant rocket.Based on the Radiative Transfer Equation(RTE),this study employs the discrete transfer method to solve the transient RTE problem using physical properties to describe the problem while avoiding the need to directly solve mathematical equations.The proposed method can effectively determine the radiative heat flux of the flow field and is applicable to problems involving various geometries.Calculations reveal that during the ascent phase of the rocket,the radiative heat flux at the base of the vehicle reaches its maximum in the initial stages of the lift-off,reaching a maximum of~50 kW/m2,which is 2.24 times the maximum value during the return phase.During the deceleration stage of re-entry into the atmosphere,the maximum radiative heat flux recorded on the sidewall of the rocket is 29.1 kW/m2;the maximum heat flux on the bottom surface is approximately 22.3 kW/m2,accounting for 76.6%of that on the rocket's sidewall.This provides a basis for the thermal protection design of the rocket's bottom and walls as well as for the thermal management of cryogenic propellant tanks.Future research will involve ground engine testing and flight experiments to further validate the proposed model. 展开更多
关键词 HITEMP2010 Liquid propulsion Radiant heat flux Radiative transfer equation Retroplume Reusable launch vehicle
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CIIS Launches Global Security Situation Report(2025) 认领 引用
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《China International Studies》 2026年第2期F0002-F0002,共1页
On April 20,2026,China Institute of International Studies(CIIS)hosted a launch event in Beijing for its inaugural annual publication,Global Security Situation Report(2025).CIIS President Chen Bo presided over the cere... On April 20,2026,China Institute of International Studies(CIIS)hosted a launch event in Beijing for its inaugural annual publication,Global Security Situation Report(2025).CIIS President Chen Bo presided over the ceremony,which was attended by approximately 120 guests,including ambassadors and diplomats from over 60 countries and international organizations. 展开更多
关键词 Beijing launch event Security Situation Annual Publication Global Security Situation Report China Institute International Studies CIIS
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基于语料库的扩展意义单位研究——以COCA语料库中的动词launch为例 认领 引用
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作者 龚泠竹 《教育创新与实践》 2026年第3期187-191,共5页
本文以Sinclair扩展意义单位理论为框架,借助美国当代英语语料库(COCA),采用定量与定性结合的语料库研究方法,从语域分布、搭配、类联接、语义倾向、语义韵五个维度,对高频动词launch的扩展意义单位展开系统分析。研究发现,launch在杂... 本文以Sinclair扩展意义单位理论为框架,借助美国当代英语语料库(COCA),采用定量与定性结合的语料库研究方法,从语域分布、搭配、类联接、语义倾向、语义韵五个维度,对高频动词launch的扩展意义单位展开系统分析。研究发现,launch在杂志、博客、网站等传播类语域使用频次最高,以“LAUNCH+NOUN”为核心类联接,高频搭配以名词为主,覆盖商业科技、政府社会、军事、抽象发展四大语义场,呈现积极推动、制度性启动、破坏性威胁、象征性开启四类语义倾向,并形成正向与负向两种典型语义韵。研究结果揭示了launch在真实语境中的动态意义建构特征,可为英语词汇教学、词典编纂及自然语言处理提供实证依据与教学启示。 展开更多
关键词 扩展意义单位 语料库 COCA launch
Implementation of the Shenzhou-23 Mission and the First Emergency Launch Mission in China’s Manned Space Program 认领 引用
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《Aerospace China》 2026年第1期56-58,共3页
The combination of the Shenzhou-23 crewed spacecraft and the Long March-2F Y23 carrier rocket was transferred to the launch area on May 16,2026.
关键词 Chinas manned space program emergency launch Shenzhou mission Shenzhou crewed spacecraft Long March F Y carrier rocket
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AI enabled launch vehicles:Next potential disruptive technology after reusability 认领 引用 被引量：1
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作者 Haipeng CHEN Xiaowei WANG Feng ZHANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2025年第10期445-447,共3页
In the era of global space industry’s rapid expansion,reusable launch technology has the advantage of cost reduction,but makes launch frequency and flight reliability remain critical.This study proposes that Artifici... In the era of global space industry’s rapid expansion,reusable launch technology has the advantage of cost reduction,but makes launch frequency and flight reliability remain critical.This study proposes that Artificial Intelligence(AI)would be the potential disruptive technology to solve these challenges.AI enables transformative capabilities for launch vehicles which are pointed out in four domains:Agile launch operations enabling automate testing,fault diagnosis,and decision-making for targeting hour-level launch cycles and minute-level fault resolution;high-reliability flight enabling real-time autonomous fault diagnosis,mission replanning,and fault-tolerant control within seconds during anomalies,potentially improving reliability by 1–2 orders of magnitude;rapid maintenance enabling real-time health monitoring and lifespan prediction for swift relaunch decisions;efficient space traffic management enabling predictesolve orbital conflicts amid growing congestion from satellites and debris.The key challenges for AI applications are analyzed as well,including multi-system coupling,uncertain failure modes and narrow flight corridors,limited sensor data,and massive heterogeneous data processing.Finally,the study also proposes that AI promises substantial efficiency gains in launch vehicle design,manufacturing,and testing through multidisciplinary optimization and reduced reliance on physical testing. 展开更多
关键词 Artificial intelligence Flight reliability Launch preparation Launch vehicle Rapid maintenance Safety operation&control
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Launch dynamics modeling and simulation of box-type multiple launch rocket system considering plane clearance contact 认领 引用 被引量：2
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作者 Jinxin Tang Guoping Wang +3 位作者 Genyang Wu Yutian Sun Lilin Gu Xiaoting Rui 《Defence Technology（防务技术）》 SCIE EI CAS CSCD 2025年第5期105-123,共19页
As the performance of the box-type multiple launch rocket system(BMLRS)improves,its mechanical structures,particularly the plane clearance design between the slider on the rocket and the guide inside the launch canist... As the performance of the box-type multiple launch rocket system(BMLRS)improves,its mechanical structures,particularly the plane clearance design between the slider on the rocket and the guide inside the launch canister,have grown increasingly complex.However,deficiencies still exist in the current launch modeling theory for BMLRS.In this study,a multi-rigid-flexible-body launch dynamics model coupling the launch platform and rocket was established using the multibody system transfer matrix method and the Newton-Euler formulation.Furthermore,considering the bending of the launch canister,a detection algorithm for slider-guide plane clearance contact was proposed.To quantify the contact force and friction effect between the slider and guide,the contact force model and modified Coulomb model were introduced.Both the modal and launch tests were conducted.Additionally,the modal convergence was verified.By comparing the modal experiments and simulation results,the maximum relative error of the eigenfrequency is 3.29%.thereby verifying the accuracy of the developed BMLRS dynamics model.Furthermore,the launch test validated the proposed plane clearance contact model.Moreover,the study investigated the influence of various model parameters on the dynamic characteristics of BMLRS,including launch canister bending stiffness,slider and guide material,slider-guide clearance,slider length and layout.This analysis of influencing factors provides a foundation for future optimization in BMLRS design. 展开更多
关键词 Box-type multiple launch rocket system Launch dynamics Plane clearance contact Contact detection algorithm Multibody system transfer matrix method(MSTMM)
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Safety assessment of framed hot launch departure for sea-based rockets in rough sea conditions 认领 引用 被引量：1
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作者 Deng Wang Jianshuai Shao +2 位作者 Nan Cao Yi Jiang Tong Huang 《Defence Technology（防务技术）》 SCIE EI CAS CSCD 2025年第8期83-100,共18页
Sea-based rocket launches encounter significant challenges stemming from dynamic marine environmental interactions.During the hot launch phase,characterized by low-velocity ascent,the departure of the rocket from the ... Sea-based rocket launches encounter significant challenges stemming from dynamic marine environmental interactions.During the hot launch phase,characterized by low-velocity ascent,the departure of the rocket from the oscillatory platform exhibits heightened sensitivity to external disturbances.In the development stage,assessing the launch dynamics and the clearance between the rocket and framed launcher are crucial for improving the reliability of sea-based rocket launches in rough sea conditions.This study presents a high-fidelity dynamic model of maritime hot launch system,demonstrating 3.21%prediction error through rigorous validation against experimental datasets from comprehensive modal analyses and the full-scale rocket flight test.To mitigate collision risks,we develop a computational method employing spatial vector analysis for dynamic measurement of rocket-launcher clearance during departure.Systematic investigations reveal that in rough sea conditions,optimal departure dynamics are achieved at θthrust=270°nozzle azimuth configuration,reducing failure probability compared to conventional orientations.The developed assessment framework not only resolves critical safety challenges in current sea launch systems but also establishes foundational principles for optimizing adapter axial configuration patterns in future designs. 展开更多
关键词 Sea-based rocket Departure safety Clearance measurement Launch dynamics Dynamic model
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Design and experimental validation of an electromagnetic launching mechanism for a tethered net 认领 引用
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作者 Zongming ZHU Weihao LUO +4 位作者 Zongjing LIN Yuzhe KANG Maoying ZHOU Ban WANG Huawei QIN 《Journal of Zhejiang University-SCIENCE A》 SCIE EI CAS CSCD 2025年第1期78-86,共9页
High-altitude rescue is dangerous and difficult.A new rescue method is proposed here based on electromagnetically launched tethered nets.Four electromagnetic launching units are attached to a revolving platform,from w... High-altitude rescue is dangerous and difficult.A new rescue method is proposed here based on electromagnetically launched tethered nets.Four electromagnetic launching units are attached to a revolving platform,from which four projectiles are launched.The four projectiles are connected to a tethered net,bringing it into motion.As the tethered net approaches and comes into contact with the object,the object will be trapped,and the rescue task will then be completed as long as the tethered net can be restored along with the trapped object.The structural design of the electromagnetic launching unit is presented with the established mathematical model.The motion characteristics of the launched projectiles are studied and their exit velocities are modeled and measured.Terminal velocities of these projectiles are characterized,and the final shape and position of the projected tethered net are obtained.This study validates the feasibility of using electromagnetically launched tethered nets to perform high-altitude rescues. 展开更多
关键词 Electromagnetic launching Tethered-net launching High-altitude rescue Trajectory
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Successful Launch of CIIS Special Research Report on Promoting Modernization 认领 引用
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《China International Studies》 2025年第3期F0003-F0003,共1页
On June 9,2025,CIIS held a launch event for its research report“Promoting Modernization Across Countries Through the Global Development Initiative.”The event was attended by CIIS President Chen Bo,Ambassador of Barb... On June 9,2025,CIIS held a launch event for its research report“Promoting Modernization Across Countries Through the Global Development Initiative.”The event was attended by CIIS President Chen Bo,Ambassador of Barbados to China Hallam Henry,Ambassador of Grenada to China Ma Yan,Ambassador of Timor-Leste to China Loro Horta,Ambassador of Bolivia to China Hugo Siles,Ambassador of Venezuela to China Remigio Ceballos Ichaso,Ambassador of Nepal to China Krishna Prasad Oli,Vice Director of the China Foreign Languages Publishing Administration and President of the Institute of Contemporary China and the World Yu Yunquan,Director of the Institute of International Strategy at Party School of the Central Committee(National Academy of Governance)Wu Zhicheng,and Vice Chairman of the National Global Strategy Think Tank at Chinese Academy of Social Sciences Wang Lei,all of whom delivered remarks at the launch. 展开更多
关键词 research report modernization launch event vice director global development initiative ambassador launch president
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Prospects of sea launches for Chinese cryogenic liquid-fueled medium-lift launch vehicles 认领 引用 被引量：11
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作者 Zhengyu SONG Zhifeng XIE +2 位作者 Limin QIU Dalin XIANG Jinglin LI 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2021年第1期424-437,共14页
This paper introduces the sea-launch technology of a cryogenic liquid-fueled medium-lift rocket.It first reviews the current state of sea launch technology,and then gives a brief introduction of China’s New Generatio... This paper introduces the sea-launch technology of a cryogenic liquid-fueled medium-lift rocket.It first reviews the current state of sea launch technology,and then gives a brief introduction of China’s New Generation Medium-lift Launch Vehicle(NGMLV).The innovations in the NGMVL,such as responsive test and launch control,a H3 launch model,and unmanned operations,provide convenience for sea launches.Based on these innovations,this paper proposes a sea launch scheme,including the system configuration,test and launch processes,and an improved adaptive design for the rocket.Then,the launch platform is discussed in detail,which integrates the functions of sea transportation,assembly and test,as well as technical and launch areas.The layout and function divisions,fluid filling,gas supply and distribution systems,and lossless storage technology of LH2 are described in order.This breakthrough in sea launch technology will enable China to launch medium and large satellites and constellations‘both on land and sea’,especially into low-inclination Low-Earth Orbits(LEOs),and it allows China to remain competitive in the fast-paced space industry. 展开更多
关键词 Autonomous operations Launch platform Launch vehicles Liquid hydrogen storage Sea launches
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Supercritical carbon dioxide as a new working medium for pneumatic launch:A theoretical study 认领 引用 被引量：15
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作者 Hong-xin Yao Xue-zhong Wei Hong Ye 《Defence Technology（防务技术）》 SCIE EI CAS CSCD 2021年第4期1296-1306,共11页
Compared with the conventionally gaseous or liquid working media,the specific internal energy of supercritical carbon dioxide(SCD)is higher at the same temperature and pressure,and the critical temperature of carbon d... Compared with the conventionally gaseous or liquid working media,the specific internal energy of supercritical carbon dioxide(SCD)is higher at the same temperature and pressure,and the critical temperature of carbon dioxide is close to room temperature,making SCD a potential new working medium for pneumatic launch.To analyze the feasibility of this conception,an analytical model of a pneumatic catapult is established on basis of the conservations of mass and energy.The model consists of a high-pressure chamber and a low-pressure chamber connected by multiple valves,and there is a movable piston in the low-pressure chamber that can push an aircraft to accelerate.The effects of the launch readiness state of SCD in the high-pressure chamber,the initial volume of the low-pressure chamber and the valve control on the movement of the aircraft are analyzed.It is found that there is a restrictive relation between the temperature and pressure of the launch readiness state of SCD,i.e.,there is a maximum allowable launch readiness pressure when the launch readiness temperature is fixed.If this restrictive relation is not satisfied,the working medium in the low-pressure chamber will drop to its triple point within a few milliseconds,leading to a launch failure.Owing to this restrictive relation,there is an optimal launch readiness state of SCD with the highest working capacity for any allowable launch readiness temperature.The pressure of the low-pressure chamber will decrease significantly as the initial volume increases,leading to a decreased acceleration of the aircraft.The acceleration can be controlled below a critical value by a designed sequential blasting technique of multiple valves.The calculated results show that a 500 kg aircraft can be accelerated from 0 to 58 m/s in 0.9 s with 36 kg of carbon dioxide.This research provides a new technique for the controllable cold launch of an aircraft. 展开更多
关键词 Pneumatic launch Supercritical carbon dioxide Restrictive relation of the launch readiness state Optimal launch readiness state High working capacity
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Dynamics modeling and simulating of the underwater launch system under the impact load 认领 引用
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作者 Shutian Li Bin He +3 位作者 Guoping Wang Tang Li Zhihuan Zhan Xiaoting Rui 《Acta Mechanica Sinica》 SCIE EI CAS CSCD 2025年第8期149-166,共18页
Underwater launch is a transient vibration process under the impact load.The hydrodynamic calculation is an important part of equipment research.In this paper,firstly,combining the theory of the Euler-Bernoulli beam a... Underwater launch is a transient vibration process under the impact load.The hydrodynamic calculation is an important part of equipment research.In this paper,firstly,combining the theory of the Euler-Bernoulli beam and the potential flow,the transfer equation of the Euler-Bernoulli beam considering the hydroelastic effect is derived,which expands the application scope of the transfer matrix.The correctness of the transfer matrix for the beam with hydroelastic behaviors is verified by comparison with the results of the finite element analysis.Then the dynamics model of the underwater launch system is established based on the multibody system transfer matrix method,and the beam with hydroelastic behaviors is employed as the external vehicle.Subsequently,the overall transfer and dynamic equation are derived,resulting in the solution of the wet natural frequency and the dynamic response under the impact load.The comparison with experimental data validates the dynamics model and simulation results and ensures its reliability in practical applications.The dynamic of the system demonstrates that the launching interval and adjacent tube effect will exert an influence on the subsequent emission.This research provides a fast and efficient method for the dynamic calculation of the underwater launch system. 展开更多
关键词 Underwater launch system Transfer matrix method The beam with hydroelastic behaviors Wet modal characteristics Dynamics response
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Research on agile space emergency launching mission planning simulation and verification method 认领 引用 被引量：3
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作者 WU Feng LIU Xiuluo +5 位作者 WANG Jia LI Chao LIU Ying SU Jianbin ZHANG Ailiang WANG Min 《Journal of Systems Engineering and Electronics》 SCIE CSCD 2023年第5期1267-1284,共18页
Space emergency launching is to send a satellite into space by using a rapid responsive solid rocket in the bounded time to implement the emergency Earth observation mission.The key and difficult points mainly include... Space emergency launching is to send a satellite into space by using a rapid responsive solid rocket in the bounded time to implement the emergency Earth observation mission.The key and difficult points mainly include the business process construction of launching mission planning,validation of the effectiveness of the launching scheme,etc.This paper pro-poses the agile space emergency launching mission planning simulation and verification method,which systematically con-structs the overall technical framework of space emergency launching mission planning with multi-field area,multi-platform and multi-task parallel under the constraint of resource schedul-ing for the first time.It supports flexible reconstruction of mis-sion planning processes such as launching target planning,tra-jectory planning,path planning,action planning and launching time analysis,and can realize on-demand assembly of operation links under different mission scenarios and different plan condi-tions,so as to quickly modify and generate launching schemes.It supports the fast solution of rocket trajectory data and the accurate analysis of multi-point salvo time window recheck and can realize the fast conflict resolution of launching missions in the dimensions of launching position and launching window sequence.It supports lightweight scenario design,modular flexi-ble simulation,based on launching style,launching platform,launching rules,etc.,can realize the independent mapping of mission planning results to two-dimensional and three-dimen-sional visual simulation models,so as to achieve a smooth con-nection between mission planning and simulation. 展开更多
关键词 emergency launching launching mission planning launching process simulation satellite orbit planning rocket tra-jectory planning
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Book Launch Event for Stories of the SCO in the New Era Held in Beijing 认领 引用
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《China International Studies》 2025年第4期F0003-F0003,共1页
On August 20,the Xi Jinping Thought on Diplomacy Studies Center held a book launch event“Hand in Hand,Heart to Heart-Toward a Shared Future”for Stories of the SCO in the New Era in Beijing.China's Assistant Mini... On August 20,the Xi Jinping Thought on Diplomacy Studies Center held a book launch event“Hand in Hand,Heart to Heart-Toward a Shared Future”for Stories of the SCO in the New Era in Beijing.China's Assistant Minister of Foreign Affairs Liu Bin and Deputy Secretary-General of the Shanghai Cooperation Organization(SCO)Ahmad Saidmurodzoda delivered speeches at the event,which was also attended by Zhang Deguang,China's former Vice Foreign Minister and the SCO's inaugural Secretary-General. 展开更多
关键词 shared future Shanghai Cooperation Organization Stories SCO New Era Liu Bin hand hand heart heart Xi Jinping Thought on Diplomacy Studies Center book launch event Ahmad Saidmurodzoda
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International Free Lunch Programme Launched at Schoolin Nairobi's Mathare Slum 认领 引用
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《International Understanding》 2025年第1期40-40,共1页
On January 15,2025,the China Road and Bridge Corporation(CRBC)Kenya Office and Africa Star Railway Operation Company Limited(Afristar),in collaboration with the Dream Building Service Association(DBSA),held the launch... On January 15,2025,the China Road and Bridge Corporation(CRBC)Kenya Office and Africa Star Railway Operation Company Limited(Afristar),in collaboration with the Dream Building Service Association(DBSA),held the launching ceremony for the International Free Lunch Programme at a school in the Mathare slum community of Nairobi. 展开更多
关键词 africa star railway operation company limited China road bridge corporation launching ceremony school nairobi dream building service international free lunch programme mathare slum
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