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A comprehensive fluid-solid coupling dynamic simulation for spatiotemporal distribution of regression rate in hybrid rocket motors 认领 引用
1
作者 Tianfang WEI Guobiao CAI +3 位作者 Hui TIAN Xiangyu MENG Xianzhu JIANG Xiaoming GU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2024年第9期100-112,共13页
The spatiotemporal distribution characteristics of the regression rate are crucial aspects of the research on Hybrid Rocket Motor(HRM). This study presents a pioneering effort in achieving a comprehensive numerical si... The spatiotemporal distribution characteristics of the regression rate are crucial aspects of the research on Hybrid Rocket Motor(HRM). This study presents a pioneering effort in achieving a comprehensive numerical simulation of fluid dynamics and heat transfer in both the fluid and solid regions throughout the entire operation of an HRM. To accomplish this, a dynamic grid technique that incorporates fluid–solid coupling is utilized. To validate the precision of the numerical simulations, a firing test is conducted, with embedded thermocouple probes being used to measure the inner temperature of the fuel grain. The temperature variations in the solid fuel obtained from both experiment and simulations show good agreement. The maximum combustion temperature and average thrust obtained from the simulations are found to deviate from the experimental results by only 3.3% and 2.4%, respectively. Thus, it can be demonstrated that transient numerical simulations accurately capture the fluid–solid coupling characteristics and transient regression rate. The dynamic simulation results of inner flow field and solid region throughout the entire working stage reveal that the presence of vortices enhances the blending of combustion gases and improves the regression rate at both the front and rear ends of the fuel grain. In addition, oscillations of the regression rate obtained in the simulation can also be well corresponded with the corrugated surface observed in the experiment. Furthermore, the zero-dimension regression rate formula and the formula describing the axial location dependence of the regression rate are fitted from the simulation results, with the corresponding coefficients of determination(R2) of 0.9765 and 0.9298, respectively.This research serves as a reference for predicting the performance of HRM with gas oxygen and polyethylene, and presents a credible way for investigating the spatiotemporal distribution of the regression rate. 展开更多
关键词 Hybrid Rocket Motor(HRM) Transient numerical simulation Fluid-solid couplingheat transfer Spatiotemporal distribution of regression rate Dynamic grid
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Multi-disciplinary design optimization with fuzzy uncertainties and its application in hybrid rocket motor powered launch vehicle 认领 引用 被引量：11
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作者 Pengcheng WANG Hui TIAN +1 位作者 Hao ZHU Guobiao CAI 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2020年第5期1454-1467,共14页
In this paper,an Uncertainty-based Multi-disciplinary Design Optimization (UMDO)method combining with fuzzy theory and Multi-Discipline Feasible (MDF) method is developed for the conceptual design of a Hybrid Rocket M... In this paper,an Uncertainty-based Multi-disciplinary Design Optimization (UMDO)method combining with fuzzy theory and Multi-Discipline Feasible (MDF) method is developed for the conceptual design of a Hybrid Rocket Motor (HRM) powered Launch Vehicle (LV).In the method proposed,membership functions are used to represent the uncertain factors,the fuzzy statistical experiment is introduced to analyze the propagation of uncertainties,and means,standard deviations and credibility measures are used to delineate uncertain responses.A geometric programming problem is solved to verify the feasibility of the Fuzzy-based Multi-Discipline Feasible(F-MDF) method.A multi-disciplinary analysis of a three-stage HRM powered LV involving the disciplines of propulsion,structure,aerodynamics and trajectory is implemented,and the mathematical models corresponding to the F-MDF method and the MDF method are established.A two-phase optimization method is proposed for multi-disciplinary design optimization of the LV,including the orbital capacity optimization phase based on the Ziolkowski formula,and the scheme trajectory verification phase based on the 3-degree-of-freedom point trajectory simulation.The correlation coefficients and the quadratic Response Surface Method (RSM) based on Latin Hypercube Sampling (LHS) are adopted for sensitive analysis of uncertain factors,and the Multi-Island Genetic Algorithm (MIGA) is adopted as the optimization algorithm.The results show that the F-MDF method is applicable in LV conceptual design,and the design with the F-MDF method is more reliable and robust than that with the MDF method. 展开更多
关键词 Fuzzy theory Hybrid Rocket Motor(HRM) Launch Vehicle(LV) Sensitive Analysis(SA) Uncertainty-based Multi-disciplinary Design Optimization(UMDO)
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Design and fabrication of a full elastic sub-micron-Newton scale thrust measurement system for plasma micro thrusters 认领 引用 被引量：6
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作者 Zhongkai Zhang Guanrong Hang +5 位作者 Jiayun Qi Zun Zhang Zhe Zhang Jiubin Liu Wenjiang Yang Haibin Tang 《Plasma Science and Technology》 SCIE EI CAS CSCD 2021年第10期29-39,共11页
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 micro-Newtons.The thrust measurement system uses an el... 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 micro-Newtons.The 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 axis.In 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 position.The thrust respond of the system was calibrated using an electrostatic weak force generation device.Experimental 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 thruster.The 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. 展开更多
关键词 plasma thruster micro-thrust measurement torsional pendulum
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Cathode erosion site distributions in an applied-field magnetoplasmadynamic thruster 认领 引用 被引量：4
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作者 Peng WU Yibai WANG +4 位作者 Yong LI Baojun WANG Kaiyu ZHANG Haibin TANG Jinbin CAO 《Plasma Science and Technology》 SCIE EI CAS CSCD 2020年第9期59-65,共7页
Erosion can influence cathode life,and is thus considered to be one of the main factors limiting the application of applied-field magnetoplasmadynamic thrusters.In this paper,erosion sites on graphite cathodes are stu... Erosion can influence cathode life,and is thus considered to be one of the main factors limiting the application of applied-field magnetoplasmadynamic thrusters.In 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 anode.The experiment results show that the application of applied magnetic field can significantly reduce the erosion rate of the cathode compared to that without magnetic field.The 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 field.The erosion sites on the cathodes are found to be related to the propellant supply.The decreasing anode mass flow rate enlarges the range of erosion.These 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. 展开更多
关键词 electric propulsion applied-field magnetoplasmadynamic thruster cathode erosion magnetic field propellant mass flow rate
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Three-dimensional numerical analysis on combustion performance and flow of hybrid rocket motor with multi-segmented grain 认领 引用 被引量：6
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作者 Hui TIAN Yu DUAN Hao ZHU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2020年第4期1181-1191,共11页
This paper presents the combustion characteristics in hybrid rocket motors with multisegmented grain through three-dimensional numerical simulations.Multi-segmented grain is composed of several thin grains with two or... This paper presents the combustion characteristics in hybrid rocket motors with multisegmented grain through three-dimensional numerical simulations.Multi-segmented grain is composed of several thin grains with two or more ports.The numerical model consists of Navier-Stokes equations with turbulence,solid fuel pyrolysis,chemical reactions,a fluid–solid coupling model and a regression rate model.The simulations adopt 90%Hydrogen Peroxide(HP)and PolyEthylene(PE)as the propellant combination.The effects of the rotation,port number,fuel grain segment number and mid-chamber length on the flow field and combustion performances are analyzed.The results indicate that the multi-segmented grain configuration can strengthen the flow field,and the regression rate and combustion efficiency are enhanced.Take the cases with two grain segments and three ports for example,the regression rate is increased by 32.4%-45.1%and the combustion efficiency increases by 6%-8.6%in different rotation angles. 展开更多
关键词 Combustion efficiency Hybrid rocket motor Multi-segmented grain Regression rate Rotation angle
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Coupling plasma plume of a low-power magnetically shielded Hall thruster with a hollow cathode 认领 引用 被引量：7
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作者 Guangchuan ZHANG Junxue REN +3 位作者 Wei LIANG Ning OUYANG Chao LU Haibin TANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2020年第12期3018-3026,共9页
The coupling region of a Hall thruster with a hollow cathode is the region between the cathode and the thruster plume.The characteristics of plasma in that region are complicated and strongly associated with the thrus... The coupling region of a Hall thruster with a hollow cathode is the region between the cathode and the thruster plume.The characteristics of plasma in that region are complicated and strongly associated with the thruster working conditions and the cathode position.In this paper,a laboratory 100 W class magnetically shielded Hall thruster was coupled with a hollow cathode.Optical imaging and electrostatic probe were employed to monitor and scan the plasma plume.Plume characteristics in the coupling region in non-self-sustained mode and self-sustained mode were compared.Evolution of the coupling plume with the cathode position was studied.Experiments show that,when turning the thruster into self-sustained mode or moving the cathode further away axially,the discharge current can be reduced by 6.4–10.6%restraining the electron current and improving ionization.In particular,when the cathode is moved further,the electron conduction near the channel walls is suppressed.The electron current is reduced by 27.4%and the ion beam current is increased by 7%.Overall,this work shows that the working mode of the thruster and the position of the cathode greatly affect the coupling plasma plume.Both play an important role in improving the utilizations of propellant and current. 展开更多
关键词 Coupling region Electron conduction Hall thruster Hollow cathode Utilizations of propellant and current
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A plasma equilibrium model for rapid estimation of SF-MPDT performance 认领 引用 被引量：1
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作者 Yifeng Fu Cheng Zhou +3 位作者 Peng Wu Zhongkai Zhang Zun Zhang Haibin Tang 《Plasma Science and Technology》 SCIE EI CAS CSCD 2021年第10期40-48,共9页
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 a... 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. 展开更多
关键词 SF-MPDT plasma equilibrium diffusion equation thruster parameters
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Autonomous Spacecraft Formation Flying Implementation Near Mars Synchronous Orbit Based on Fuzzy Logic Control 认领 引用
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作者 BIYOGO NCHAMA Vicente Angel Obama HASAN Mehedi +1 位作者 MASUM Sajjad Hossain SHI Peng 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI CSCD 2025年第S1期1-11,共11页
In response to the need for a supportive on-orbit platform for future Mars exploration missions,this paper proposes the design and implementation of an autonomous spacecraft formation flying system near the Martian sy... In response to the need for a supportive on-orbit platform for future Mars exploration missions,this paper proposes the design and implementation of an autonomous spacecraft formation flying system near the Martian synchronous orbit using fuzzy learning-based intelligent control.A detailed analysis of spacecraft relative motion in the Mars environment is conducted,deducing the necessary conditions to reach the Martian synchronous orbit constraints.The modified Clohessy-Wiltshire(C-W)equation with Martian J2(Oblateness index)perturbation is used as a reference to design a fuzzy learning-based intelligent and robust nonlinear control approach,which helps to autonomously track the desired formation configuration and stabilizes it.An introduction to spacecraft propulsion mechanisms is provided to analyze the feasibility of using electrical thrusters for spacecraft formation configuration tracking and stabilization in Martian synchronous orbits.The simulations show the effectiveness of the proposed control system for long-term on-orbit operations and reveal its reliability for designing intelligent deep-space formation flying configurations,such as an autonomous Mars observatory,a Martian telescope,or an interferometer. 展开更多
关键词 Mars space station spacecraft formation flying fuzzy logic-based spacecraft formation control intelligent control
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Numerical and experimental research on axial injection end-burning hybrid rocket motors with polyethylene fuel 认领 引用 被引量：2
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作者 Xiangyu MENG Hui TIAN +3 位作者 Lingfei HE Jingfei GAO Xiaoting NIU Guobiao CAI 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2024年第8期91-105,共15页
This study investigates the end-burning hybrid rocket motors with polyethylene fuel by the numerical simulation and experiment.Based on computational fluid dynamics,a numerical model is developed.The model is validate... This study investigates the end-burning hybrid rocket motors with polyethylene fuel by the numerical simulation and experiment.Based on computational fluid dynamics,a numerical model is developed.The model is validated by two firing tests in this hybrid rocket motor,which uses oxygen and polyethylene as propellants.The results show that the numerical and experimental data are in good agreement,and the error of the chamber pressure is less than 2.63%.Based on the simulation mode,the blowoff limit of the end-burning hybrid rocket motors is investigated.When the nozzle throat diameter and the inner diameter of grain are large,it is more difficult for the hybrid rocket motor to achieve end-burning mode,i.e.,the flame spreading is prevented in the narrow duct.The main reason is that when the nozzle throat and the grain port are large,chamber pressure and oxidizer flow velocity are low.Therefore,the friction velocity considering the pressure and flow velocity is proposed.The critical friction velocity is about 4.054–4.890 m/s in the hybrid rocket motors.When the friction velocity exceeds the critical friction velocity,the combustion mode in hybrid rocket motors changes from the flame spreading mode to the end-burning mode.Moreover,the regression rate formula is obtained by fitting,which shows that the regression rate has a good correlation with combustion chamber pressure.The critical friction velocity and regression rate formula can provide an important reference for end-burning hybrid rocket motors. 展开更多
关键词 Hybrid rocket motor End burning Blowoff limit Flame propagation Regression rate
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