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| 1 | Plume aerodynamic effects of cushion engine in lunar landing显示文摘During the second period of China 'Tanyue' Project, the explorer will softland on the moon. The cushion engines are used to decelerate the explorer and reduce the impact on the lunar ground. It is necessary to study its plume effects on the explorer component. The self-developed PWS (Plume WorkStation) software based on direct simulation Monte Carlo (DSMC) method is used to simulate the plume effects of two 150 N engines. Due to the complex structure of the explorer, PWS uses a decoupling method to treat the boundary mesh, which mainly interacts with simulation particles, and has no relation with the computational grids. After the analytical expressions of plane surfaces and curved surfaces of each boundary block are given, the particle position within or without the boundary blocks can be easily determined. Finally the 3D plume field of two 150 N engines is simulated. The pressure, temperature and velocity distributions of plume field are clearly presented by three characteristic slices. The aerodynamic effects on the explorer bottom, the landfall legs and antenna are separately shown. The compression influence on the plume flow of four landfall legs can be observed. | He Bijiao He Xiaoying Zhang Mingxing Cai Guobiao | 2013 | Chinese Journal of Aeronautics2013，26，2： | 9 |
| 2 | Research on vacuum plume and its effects显示文摘In vacuum environment, the exhaust flow of attitude control thrusters would expand freely and produce the plume, which possibly causes undesirable contamination, aerodynamic force and heating effects to the spacecraft. Plume work station (PWS) is developed by Beihang University (BUAA) for numerically simulating the vacuum plume and its effects. An approach which combines the direct simulation Monte Carlo (DSMC) method and difference solution of Navier-Stokes (N-S) equations is applied. The internal flows in nozzles are simulated by solving the NS equations. The flow parameters at nozzle exit are used as the inlet boundary condition for the DSMC calculation. Experimental studies are carried out in a supersonic low density wind tunnel which could simulate the 60-80 km altitude environment to investigate the plume and its effects. To demonstrate the capability of PWS, numerical simulations are performed for the vacuum plume of several typical attitude control thrusters. The research results are of great help for the engineering design. | He Bijiao Zhang Jianhua Cai Guobiao | 2013 | Chinese Journal of Aeronautics2013，26，1： | 6 |
| 3 | Design of double-layer anti-sputtering targets for plume effects experimental system显示文摘在一个真空房间使用的一个电的推进器的劈啪作响背的效果在推进器,真空房间和试验性的设备上有不利效果。一个劈啪作响反的目标(著名计算机生产厂商) 能由减少劈啪作响背的免职效果扩大真空房间的操作生活。在国际设备使用的真空房间成功地合并了著名计算机生产厂商。改进著名计算机生产厂商表演,一个双层结构著名计算机生产厂商基于羽毛效果,试验性的系统(足) 被设计。结构 AST 主要结束当第二等的结束作为一个快门被设计解决象服务生活,劈啪作响的材料的背流动率,经济和系统安全那样的因素时,作为一座公寓被设计。验证双层著名计算机生产厂商的效果, AST 有或没有的劈啪作响的效果第二等结束被一个 DSMC 照片算法评估。另外,赤裸的房间的试验性的确认和目标被执行。结果显示第二等的结束石墨表能减少背流动收益约 50% 。双层著名计算机生产厂商的设计能为一个劈啪作响反的目标的设计作为一本参考书被介绍。 | SHANG ShengFei CAI GuoBiao ZHU DingQiang HE BiJiao | 2016 | Science China(Technological Sciences)2016，59，8： | 4 |
| 4 | Investigation on aerodynamic force effect of vacuum plumes using pressure-sensitive paint technique and CFD-DSMC solution显示文摘Pressure-sensitive paint(PSP) technique was employed to experimentally investigate the aerodynamic force effect of vacuum plume in this study. The characterization and comparison for two types of PSP were firstly conducted in an air pressure range from0.05 to 5000 Pa. The PSPs were prepared using PtTFPP as the active dye and different binders, i.e., polymer-ceramic(PC) and poly(1-trimethylsilyl-1-propyne) [poly(TMSP)]. The static calibrations showed that PtTFPP/poly(TMSP) had a higher pressure sensitivity and a lower temperature dependency compared to PtTFPP/PC in this pressure range. The pressure distributions of a single and two interacting plumes impinging onto a flat plate model were measured using PSP technique. The experimental data were compared to numerical solutions that combined both the computed fluid dynamics(CFD) and direct simulation Monte Carlo(DSMC) methods. Remarkable agreements were achieved, demonstrating the feasibility and accuracy of the numerical approach.Finally, the aerodynamic force effect of interacting plumes at different separation distances was investigated numerically. | WU Jing BITTER Martin CAI GuoBiao HE BiJiao KAEHLER Christian | 2017 | Science China(Technological Sciences)2017，60，7： | 3 |
| 5 | Experimental and numerical analysis of the heat flux characteristic of the plume of a 120-N thruster显示文摘The convective heat transfer of the plume of a 120-N thruster is investigated experimentally and numerically. Numerical results agree well with experimental results in that there is a nonlinear decrease in convective heat transfer with an increasing cone angle. It is also found that convective heat transfer decreases with increasing distance from the thruster outlet. Furthermore, the convective heat transfer of the plume mainly concentrates within a 35° cone angle and the heat flux decreases to the same order as solar radiation at the Earth’s surface when the cone angle exceeds 60°. The results of the study will help improve spacecraft design. | ZHANG MingXing CAI GuoBiao HE BiJiao TANG ZhenYu ZHOU Hao | 2019 | Science China(Technological Sciences)2019，62，10： | 3 |
| 6 | Research on Vacuum Plume and Its Effects显示文摘 | He Bijiao Zhang Jianhua Cai Guobiao | 2012 | Chinese Journal of Aeronautics2012，，： | 1 |
| 7 | Simulation of rocket plume and lunar dust using DSMC method显示文摘 | Xiaoying He Bijiao He Guobiao Cai | 2011 | Acta Astronautica2011，，： | 1 |
| 8 | Simulation of two-phase plume field of liquid thruster显示文摘When the liquid propellant thruster works,its plume field would contain many propellant liquid droplets,especially at pulse state.Liquid droplets may move along with the gas flow and deposit on the components of spacecraft as contamination.The simulation of the plume field involving the gas molecules and liquid droplets is an important part in contamination studies of thruster plume.Based on the PWS software developed by Beihang University(BUAA),axial-symmetric two-phase direct simulation Monte Carlo(DSMC) method is used with the liquid droplet taken as a kind of solid particle.The computation of gas-to-particle effect and gas reflection on the particle surface are decoupled.The inter-particle collision is also considered.The gas parameters at nozzle exit of 120N engine after 20 ms pulse work are taken as the entrance condition of the numerical simulation.Four test cases are conducted for comparison of different collision modules.Simulation results show that the effects of liquid propellant droplets mainly concentrate near the axis line of engine.The particle-to-gas collision would cause evident differences in the gas field and subtle differences in the particle phase.The liquid droplets in the plume field are generally accelerated and convected by the gas molecules.The DSMC method is proved to be a feasible solver to numerically simulate the two-phase flow involving solid phase and rarefied gas flow. | HE XiaoYing HE BiJiao CAI GuoBiao | 2012 | Science China(Technological Sciences)2012，55，6： | 1 |
| 9 | Experiment of Hall thruster plume effects on different ground experimental conditions显示文摘Reducing the influence of back-sputtering effect can effectively improve the accuracy of the measurement of the Hall thruster plume effect.Quartz crystal microbalance(QCM)was used to measure the deposition and sputtering distribution of HET-40 thruster plume on two different experimental conditions:case1,using liquid nitrogen heat sinks and case 2,without using liquid nitrogen heat sinks.Meanwhile,X-ray photoelectron spectroscopy(XPS)was used to analyze the composition of the QCM surface after two experiments.The results of the two experiments showed that the sputtering rate under the condition of case 1 was slightly higher than case 2.Especially within the range of 90°to 110°relative to the thruster axis,case 1 experiment result showed sputtering effect,while case 2 experiment showed deposition effect.Through analysis of the experimental results,it can be found that using liquid nitrogen heat sink to reduce the temperature of the inner wall surface of vacuum chamber can effectively adsorb the particles sputtered by the plume and reduce the concentration of back-sputtering particles,leading to the above phenomenon. | SU Yang CAI Guobiao HE Bijiao SHANG Shengfei LIU Peng LIANG Wei | 2019 | 航空动力学报2019，34，7： | 0 |
| 10 | Stable Runge-Kutta discontinuous Galerkin solver for hypersonic rarefied gaseous flow based on 2D Boltzmann kinetic model equations显示文摘A stable high-order Runge-Kutta discontinuous Galerkin(RKDG) scheme that strictly preserves positivity of the solution is designed to solve the Boltzmann kinetic equation with model collision integrals. Stability is kept by accuracy of velocity discretization, conservative calculation of the discrete collision relaxation term, and a limiter. By keeping the time step smaller than the local mean collision time and forcing positivity values of velocity distribution functions on certain points, the limiter can preserve positivity of solutions to the cell average velocity distribution functions. Verification is performed with a normal shock wave at a Mach number 2.05, a hypersonic flow about a two-dimensional(2D) cylinder at Mach numbers 6.0 and 12.0, and an unsteady shock tube flow. The results show that, the scheme is stable and accurate to capture shock structures in steady and unsteady hypersonic rarefied gaseous flows. Compared with two widely used limiters, the current limiter has the advantage of easy implementation and ability of minimizing the influence of accuracy of the original RKDG method. | Wei SU Zhenyu TANG Bijiao HE Guobiao CAI | 2017 | Applied Mathematics and Mechanics(English Edition)2017，38，3： | 0 |
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