Research of heat transfer processes during pre-launch chilldown of PS consumption lines of upper-stage LV
Research of heat transfer processes during pre-launch chilldown of PS consumption lines of upper-stage LV
复制标题
上级低压PS消耗线启动前降温传热过程研究
DOI：
10.1016/j.ijhydene.2017.07.038
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发表时间：
2017
期刊：
影响因子：
--
通讯作者：
A. Galeev
中科院分区：
文献类型：
--
作者：
A. G. Galeev;V. Firsov;I. Antyukhov;A. Galeev
本文研究了利用低温部件对上级推进系统(PS)的消耗线进行发射前冷却时的换热过程。运行在高效低温推进剂部件上的推进系统可用于运载火箭的第一级和较高级，以便将航天器送入最终轨道。低温聚苯乙烯具有较高的比冲，对环境友好，这可能会引起人们对其应用的日益浓厚的兴趣。低温推进剂部件的低温在冷却、燃料和存储部件以及排放燃料箱和启动PS时可能会带来相当大的挑战，特别是在长期太空飞行的零重力条件下。为了克服这些挑战，人们正在开发复杂的实验装置，以及用于计算具有强烈相变的非稳态多相传热过程的测试方法以及物理和数学模型。从质量守恒方程和能量守恒方程出发，提出了冷却和低温部件流动过程的数学模拟方法，这些方程与供应管道、储气罐气体包层和装入低温液体的储罐体积有关。根据试验台和试飞结果确定了闭合依赖比，用于求解试验台和PS低温供应系统部件的传热和摩擦方程，并结合台架和试飞结果研究了12KRB低压发动机KVD-1液氢发动机消耗线发射前冷却过程中的换热过程。12KRB上级冷却和加油的结果可用于在设计和研制安加拉A5V重型运载火箭液氧/液氢发动机RD0146 KVTK先进上级时验证计算模型。
The paper deals with heat transfer processes during pre-launch chilldown of consumption lines of the upper stage propulsion systems (PS) by a cryogenic component. Propulsion systems operating on high-efficiency cryogenic propellant components may be used at the first as well as at the upper stages of launch vehicles to deliver spacecrafts into final orbits. Cryogenic PS produce high specific impulse being environmentally friendly, which may provide a growing interest towards their application. Low temperature of cryogenic propellant components may pose considerable challenges when chilling down, fueling and storing components as well as draining fuel tanks and starting PS, especially under zero gravity conditions in long-term space flights. Complex experimental facilities (EF) along with test methods as well as physical and mathematical models for calculating nonsteady multiple-phase heat transfer processes with intense phase transformations are being developed to overcome these challenges. The methods for mathematical modelling of the chilldown and cryogenic component flow processes have been proposed considering mass - and energy-conservation equations in relation to supply lines, tank gas blanket and tank volume filled with cryogen liquid. Closing dependency ratios have been specified according to results of bench and flight testing of PS to solve equations for heat transfer and friction in the cryogenic supply system components of test stand (TS) and PS.Also, the paper studies heat transfer processes during pre-launch chilldown of consumption lines (CL) of 12KRB LV PS with the lox/liquid hydrogen engine KVD-1 considering results of bench and flight testing of the block.Findings on chilldown and fueling of the 12KRB upper stage may be used to verify calculation models while designing and developing the KVTK advanced upper stage with the lox/liquid hydrogen engine RD0146 of the Angara-A5V heavy class launch vehicle.