为预示低温推进剂贮箱在地面停放阶段的压力变化并研究贮箱内物理过程的相互作用关系,建立了包含液体推进剂和混合气体两相的二维轴对称volume of fluid(VOF)计算流体力学(CFD)模型,并引入了基于热力学平衡假设的推进剂相变模型.对实验...为预示低温推进剂贮箱在地面停放阶段的压力变化并研究贮箱内物理过程的相互作用关系,建立了包含液体推进剂和混合气体两相的二维轴对称volume of fluid(VOF)计算流体力学(CFD)模型,并引入了基于热力学平衡假设的推进剂相变模型.对实验液氢贮箱进行仿真得到的压力上升速率与实验结果相差9.1%.通过对地面加压停放阶段下的液氢和液氧贮箱的仿真发现:造成液氢贮箱压力上升的主要因素是壁面漏热对气枕的加热作用,而液氢蒸发影响更小,液氧贮箱在加压停放阶段初期明显受到液氧相变的影响.两个贮箱中液面附近的对流运动在不同的气液传热过程作用下有不同的变化趋势,对流运动会影响推进剂的相变进而影响贮箱的压力变化.展开更多
The problem of removing unused liquid propellant residues from the tanks of spent spacecraft and orbital stages of Launch Vehicles(LV)leads to their explosion and the formation of space debris in orbits.To provide a s...The problem of removing unused liquid propellant residues from the tanks of spent spacecraft and orbital stages of Launch Vehicles(LV)leads to their explosion and the formation of space debris in orbits.To provide a solution to this problem,a method for removing liquid propellant residues from the LV tanks after the mission completion is proposed.The method is based on the gasification of liquid propellant residues in the tanks under acoustic-vacuum exposure and the discharge of the gasification products into the surrounding outer space.Experimental investigations were carried out on a Ground-based Experimental Installation(GEI)to determine the coefficient of heat transfer from the surface of an acoustic radiator to a liquid.The obtained coefficient was then used to calculate the energy costs for the gasification of kerosene.Numerical estimates are given on the example of the tank with kerosene residues from a spent second stage of the LV“Soyuz-2.1 v”.The optimal discharge rate at which kerosene does not freeze is 0.14 m^(3)/s.Moreover,the acoustic exposure leads to an increase in the mass of evaporated kerosene over a given time by96.1%,and the energy costs are 1756.7 kJ(approximately 50% of the remaining electrical energy).展开更多
To study the gas dynamic and heat transfer phenomena inside a single isolated longitudinal solid propellant surface crack,two3-D geometric models with different crack shapes were constructed.Concerning the influence o...To study the gas dynamic and heat transfer phenomena inside a single isolated longitudinal solid propellant surface crack,two3-D geometric models with different crack shapes were constructed.Concerning the influence of propagation of jet from the igniter on the flame spreading phenomena in the crack,flow region around the opening of the crack was also included in the above geometric models.A theoretical framework was then adopted to model the conjugate heat transfer in the combustion channel and the crack cavity.Numerical simulation results indicate that the ignition shock wave can spread into the crack cavity.Extremely high overpressure and pressurization rate were observed along the crack front.It is possible that the crack may propagate before the flame front reaches it.An ignited region located at the crack front near to the channel surface in downstream direction was generated long before the flame front reached the crack opening in both models.展开更多
In this paper,a new fast and efficient algorithm,Chebyshev super spectral viscosity(SSV)method,is introduced to solve the water hammer equations.Compared with standard spectral method,the method's advantage essent...In this paper,a new fast and efficient algorithm,Chebyshev super spectral viscosity(SSV)method,is introduced to solve the water hammer equations.Compared with standard spectral method,the method's advantage essentially consists in adding a super spectral viscosity to the equations for the high wave numbers of the numerical solution.It can stabilize the numerical oscillation(Gibbs phenomenon)and improve the computational efficiency while discontinuities appear in the solution.Results obtained from the Chebyshev super spectral viscosity method exhibit greater consistency with conventional water hammer calculations.It shows that this new numerical method offers an altemative way to investigate the behavior of the water hammer in propellant pipelines.展开更多
文摘为预示低温推进剂贮箱在地面停放阶段的压力变化并研究贮箱内物理过程的相互作用关系,建立了包含液体推进剂和混合气体两相的二维轴对称volume of fluid(VOF)计算流体力学(CFD)模型,并引入了基于热力学平衡假设的推进剂相变模型.对实验液氢贮箱进行仿真得到的压力上升速率与实验结果相差9.1%.通过对地面加压停放阶段下的液氢和液氧贮箱的仿真发现:造成液氢贮箱压力上升的主要因素是壁面漏热对气枕的加热作用,而液氢蒸发影响更小,液氧贮箱在加压停放阶段初期明显受到液氧相变的影响.两个贮箱中液面附近的对流运动在不同的气液传热过程作用下有不同的变化趋势,对流运动会影响推进剂的相变进而影响贮箱的压力变化.
基金co-supported by the:state assignment of the Ministry of Education and Science of the Russian Federation-“Research of liquid vaporization processes in the fuel tanks of launch vehicles to improve the environmental safety and economic efficiency of launch vehicles with liquidpropellant rocket engines”(No.2019-0251)state assignment of the Institute of Mathematics of the Siberian Branch of the Russian Academy of Sciences-“Models and methods of data processing to support decision-making processes”(No.FWNF-2022-0016)。
文摘The problem of removing unused liquid propellant residues from the tanks of spent spacecraft and orbital stages of Launch Vehicles(LV)leads to their explosion and the formation of space debris in orbits.To provide a solution to this problem,a method for removing liquid propellant residues from the LV tanks after the mission completion is proposed.The method is based on the gasification of liquid propellant residues in the tanks under acoustic-vacuum exposure and the discharge of the gasification products into the surrounding outer space.Experimental investigations were carried out on a Ground-based Experimental Installation(GEI)to determine the coefficient of heat transfer from the surface of an acoustic radiator to a liquid.The obtained coefficient was then used to calculate the energy costs for the gasification of kerosene.Numerical estimates are given on the example of the tank with kerosene residues from a spent second stage of the LV“Soyuz-2.1 v”.The optimal discharge rate at which kerosene does not freeze is 0.14 m^(3)/s.Moreover,the acoustic exposure leads to an increase in the mass of evaporated kerosene over a given time by96.1%,and the energy costs are 1756.7 kJ(approximately 50% of the remaining electrical energy).
文摘To study the gas dynamic and heat transfer phenomena inside a single isolated longitudinal solid propellant surface crack,two3-D geometric models with different crack shapes were constructed.Concerning the influence of propagation of jet from the igniter on the flame spreading phenomena in the crack,flow region around the opening of the crack was also included in the above geometric models.A theoretical framework was then adopted to model the conjugate heat transfer in the combustion channel and the crack cavity.Numerical simulation results indicate that the ignition shock wave can spread into the crack cavity.Extremely high overpressure and pressurization rate were observed along the crack front.It is possible that the crack may propagate before the flame front reaches it.An ignited region located at the crack front near to the channel surface in downstream direction was generated long before the flame front reached the crack opening in both models.
文摘In this paper,a new fast and efficient algorithm,Chebyshev super spectral viscosity(SSV)method,is introduced to solve the water hammer equations.Compared with standard spectral method,the method's advantage essentially consists in adding a super spectral viscosity to the equations for the high wave numbers of the numerical solution.It can stabilize the numerical oscillation(Gibbs phenomenon)and improve the computational efficiency while discontinuities appear in the solution.Results obtained from the Chebyshev super spectral viscosity method exhibit greater consistency with conventional water hammer calculations.It shows that this new numerical method offers an altemative way to investigate the behavior of the water hammer in propellant pipelines.
