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/m^(2),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/m^(2);the maximum heat flux on the bottom surface is approximately 22.3 kW/m^(2),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
The water hammer problem is an important issue in the dynamics of liquid propulsion system.This paper aims to use the Lattice Boltzmann Method(LBM)with entropy limiter to study the water hammer problems in propellant ...The water hammer problem is an important issue in the dynamics of liquid propulsion system.This paper aims to use the Lattice Boltzmann Method(LBM)with entropy limiter to study the water hammer problems in propellant feedlines.The dynamic characteristics of valve-closing water hammer and filling water hammer are investigated by this method,and the sensitivity of filling water hammer is analyzed with a single factor sensitivity analysis with 8 factors and 9 levels and a multi-factor sensitivity analysis with L_(27)(3^(13))orthogonal experiment based on range method.It is found that the solving result of LBM with entropy limiter is basically in good agreement with finite volume method,and using the entropy limiter can eliminate numerical oscillations when solving valve-closing water hammer problems and solve the numerical"blow up"when solving filling water hammer problems.It can be seen that the dynamic characteristics of valve-closing water hammer are relatively simple,while there are many factors that affect the filling water hammer and the degree of these effects varies.The effects on the maximum water hammer pressure are relatively uniform,but those on the water hammer response time vary greatly through the skewness analysis.展开更多
This study aims to reveal the influence of Local Momentum Ratio(LMR)on the combustion efficiency of an LOX/GCH4 pintle injector from the perspective of spray characteristics.Hot fire tests were conducted to establish ...This study aims to reveal the influence of Local Momentum Ratio(LMR)on the combustion efficiency of an LOX/GCH4 pintle injector from the perspective of spray characteristics.Hot fire tests were conducted to establish the relationship between combustion efficiency and LMR.The spray characteristics for different LMRs were simulated by the validated volume of fluid-to-discrete phase model method,taking into account the combustion chamber wall confinement.Subsequently,the difference in combustion efficiency was analyzed by comparing the spray simulation results of backpressure conditions similar to hot fire tests.The results indicate that combustion efficiency increased initially(LMR=1.12-1.64)and then decreased(LMR>1.64).Quantitative analysis revealed a linear correlation(R^(2)=0.95)between LMR and combustion efficiency within 1.12<LMR<1.64.As the LMR increased,the improvement in combustion efficiency was attributed to a wider spray distribution range and smaller droplet sizes.The area of the mantle recirculation zone that is detrimental to combustion decreased by approximately 38%,and the droplet size reduced from 37 to 16μm.This effectively enhanced both the mixing of the propellant and the evaporation process.When the LMR exceeded the critical value(1.64 in this study),the impingement of liquid oxygen on the combustion chamber wall was confirmed via overheating discoloration marks on the inner surface of combustion chamber's cylindrical section.The impingement of liquid oxygen on the combustion chamber wall increased the transport of liquid oxygen to the wall,directly reducing the mixing quality and combustion efficiency.The outcomes of this study provide the practical guidance for design and improvement in combustion efficiency of the pintle injector thrust chamber.展开更多
文摘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/m^(2),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/m^(2);the maximum heat flux on the bottom surface is approximately 22.3 kW/m^(2),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.
基金supported by the Natural Science BasicResearch Program of Shaanxi,China(No.2021JC-14)。
文摘The water hammer problem is an important issue in the dynamics of liquid propulsion system.This paper aims to use the Lattice Boltzmann Method(LBM)with entropy limiter to study the water hammer problems in propellant feedlines.The dynamic characteristics of valve-closing water hammer and filling water hammer are investigated by this method,and the sensitivity of filling water hammer is analyzed with a single factor sensitivity analysis with 8 factors and 9 levels and a multi-factor sensitivity analysis with L_(27)(3^(13))orthogonal experiment based on range method.It is found that the solving result of LBM with entropy limiter is basically in good agreement with finite volume method,and using the entropy limiter can eliminate numerical oscillations when solving valve-closing water hammer problems and solve the numerical"blow up"when solving filling water hammer problems.It can be seen that the dynamic characteristics of valve-closing water hammer are relatively simple,while there are many factors that affect the filling water hammer and the degree of these effects varies.The effects on the maximum water hammer pressure are relatively uniform,but those on the water hammer response time vary greatly through the skewness analysis.
基金co-supported by the National Science Foundation Project,China(No.2019-JCJQ-ZQ-019)the National Natural Science Foundation of China(Nos.52476141 and T2221002)。
文摘This study aims to reveal the influence of Local Momentum Ratio(LMR)on the combustion efficiency of an LOX/GCH4 pintle injector from the perspective of spray characteristics.Hot fire tests were conducted to establish the relationship between combustion efficiency and LMR.The spray characteristics for different LMRs were simulated by the validated volume of fluid-to-discrete phase model method,taking into account the combustion chamber wall confinement.Subsequently,the difference in combustion efficiency was analyzed by comparing the spray simulation results of backpressure conditions similar to hot fire tests.The results indicate that combustion efficiency increased initially(LMR=1.12-1.64)and then decreased(LMR>1.64).Quantitative analysis revealed a linear correlation(R^(2)=0.95)between LMR and combustion efficiency within 1.12<LMR<1.64.As the LMR increased,the improvement in combustion efficiency was attributed to a wider spray distribution range and smaller droplet sizes.The area of the mantle recirculation zone that is detrimental to combustion decreased by approximately 38%,and the droplet size reduced from 37 to 16μm.This effectively enhanced both the mixing of the propellant and the evaporation process.When the LMR exceeded the critical value(1.64 in this study),the impingement of liquid oxygen on the combustion chamber wall was confirmed via overheating discoloration marks on the inner surface of combustion chamber's cylindrical section.The impingement of liquid oxygen on the combustion chamber wall increased the transport of liquid oxygen to the wall,directly reducing the mixing quality and combustion efficiency.The outcomes of this study provide the practical guidance for design and improvement in combustion efficiency of the pintle injector thrust chamber.
