冷气模拟火箭级间分离试验憋压过程仿真研究  

Simulation Study on Pressure Holding Process of Cold Air Simulated Rocket Interstage Separation Test

作　　者：李晓豪 潘武贤 李广武 左红星 罗驭川 LI Xiaohao;PAN Wuxian;LI Guangwu;ZUO Hongxing;LUO Yuchuan(Xi'an Aerospace Institute of Solid Propulsion Control and Measurement Technology,Xi'an,710025)

机构地区：[1]西安航天动力测控技术研究所,西安710025

出　　处：《导弹与航天运载技术（中英文）》2024年第4期41-46,100,共7页Missiles and Space Vehicles

摘　　要：级间热分离是固体火箭飞行过程中的核心技术之一,传统的“三合一”试验通常包含了上面级发动机、伺服机构和分离系统三个主要分系统,对实际工程研制来说成本高、周期长,只可用于系统级性能验证试验,不适用于摸索性质的研制性试验。以冷气模拟火箭级间分离试验这一新型地面试验方法为研究背景,结合理论模型、数值仿真以及地面试验验证,对级间分离初始憋压阶段的内流场进行仿真,揭示级间段内气体压强变化规律,阐明冷气模拟火箭级间分离的试验机理,并通过数值模拟分析研究不同蓄压罐初始压力、不同蓄压罐容积、不同管道面积以及不同的级间段容积对气体压力变化的影响,为冷气模拟级间分离试验的设计提供解决方法。Interstage thermal separation is one of the core technologies in the flight process of solid rocket.The traditional"three in one"test usually includes three main subsystems:upper stage motor,servomechanism and separation system.For practical engineering development,it is costly,expensive and long cycle.It can only be used for system level performance verification test,and is not suitable for exploratory developmental test.Based on the new ground test method of cold air simulated rocket interstage separation test,combined with theoretical model,numerical simulation and ground test verification,the internal flow field in the initial pressure holding stage of interstage separation is simulated,the law of gas pressure change in interstage section is revealed,and the test mechanism of cold air simulated rocket interstage separation is expounded;Through numerical simulation analysis,the effects of different initial pressure of pressure accumulator,different volume of pressure accumulator,different pipe area and different volume of interstage section on the change of gas pressure are studied,which provides a solution for the design of interstage separation test of cold air simulation.

关 键 词：冷气模拟 级间分离 憋压过程 数值模拟 压力变化 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]