A new pressurized feed system of the dual-thrust hybrid rocket motor for flight is presented in this paper.The feed system supplies 90% hydrogen peroxide (90%H 2 O 2) with two different flows of 4.5 and 2 kg s 1.The o...A new pressurized feed system of the dual-thrust hybrid rocket motor for flight is presented in this paper.The feed system supplies 90% hydrogen peroxide (90%H 2 O 2) with two different flows of 4.5 and 2 kg s 1.The oxidizer flow is changed through regulating the mass flow of the high-pressure gas and switching the performance modes of the unique oxidizer flow control valve simultaneously.The models of the gas storage container,pressure regulator valve,control orifice,propellant tank,oxidizer flow control valve and cavitating venturi are generated and used to compute the instantaneous pressure,temperature and mass flow rate.There is a good agreement between the simulated and experimental results.Parameter sensitivity analysis is also conducted.It is found that the throat diameter of the cavitating venturi in feed line 1 is the main factor affecting the mass flow in both boost and sustaining phase.Other parameters have limited effects on the mass flow rate and the transition time of the system.展开更多
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
文摘A new pressurized feed system of the dual-thrust hybrid rocket motor for flight is presented in this paper.The feed system supplies 90% hydrogen peroxide (90%H 2 O 2) with two different flows of 4.5 and 2 kg s 1.The oxidizer flow is changed through regulating the mass flow of the high-pressure gas and switching the performance modes of the unique oxidizer flow control valve simultaneously.The models of the gas storage container,pressure regulator valve,control orifice,propellant tank,oxidizer flow control valve and cavitating venturi are generated and used to compute the instantaneous pressure,temperature and mass flow rate.There is a good agreement between the simulated and experimental results.Parameter sensitivity analysis is also conducted.It is found that the throat diameter of the cavitating venturi in feed line 1 is the main factor affecting the mass flow in both boost and sustaining phase.Other parameters have limited effects on the mass flow rate and the transition time of the system.
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.
