电动泵压式液体火箭发动机系统建模与仿真  

System Modeling and Simulation of Electric Pump Feed Liquid Propellant Rocket Engine

作　　者：刘洋[1,2] 付本帅 杨建刚 何国强[1,2] 何渊博[1] 刘佩进 LIU Yang;FU Benshuai;YANG Jiangang;HE Guoqiang;HE Yuanbo;LIU Peijin(Science and Technology on Combustion, Internal Flow and Thermo-Structure Laboratory, Northwestern Polytechnical University, Xi'an 710072, China;Shanxi Province Aerospace and Astronautics Propulsion Research Institute, Xi'an 710003, China)

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,西安710072 [2]陕西空天动力研究院,西安710003

出　　处：《载人航天》2019年第1期107-115,共9页Manned Spaceflight

基　　金：中央高学基本科研业务费(3102016ZB046)

摘　　要：为了精确描述电动泵压式液体火箭发动机的工作特性,如变工况特性和电机调速特性对系统的影响等,建立了与之适应的动力学模型和仿真模型。采用集中参数法,将电动泵压式液体火箭发动机划分为储箱、泵、管路、推力室和电机等主要部件,并建立了相应的动力学模型,然后利用AMESim软件的二次开发模块,建立了相应的仿真模型,在此基础上开展发动机系统的仿真研究。结果表明:泵转速调节比节流调节更加节能,有利于降低系统质量,但当调节深度较大时容易造成喷注器压降过低;虽然节流调节不存在喷注器压降过低的问题,但能耗较大。因此,电动泵压式液体火箭发动机再进行深度变推力调节时必须两种调节方式结合使用,即先进行转速调节,当喷注压降不足时,再进行节流调节。推力调节过程中,电机的时间常数对燃烧室压强、推力、混合比和离心泵的角加速扬程均有影响,时间常数越小,上述参数到达稳定状态的时间越短,同时,混合比和附加的角加速扬程变化也会更大,对发动机正常工作造成一定的影响,需要在设计时加以注意。In order to accurately describe the working characteristics of the electric pumped liquid rocket engine,such as the influence of off-design characteristics and motor speed regulation characteristics on the system,a dynamic model and a simulation model were established in this paper.The centralized pa-rameter method was used to divide the electric pumped liquid rocket engine into main components such as storage tank,pump,pipeline,thrust chamber and motor,and the corresponding dynamic model was established.Then the corresponding simulation model was established by using the secondary development module of AMESim software,and the simulation study of the engine system was carried out on this basis.The main conclusions were as follows:The regulation through pump speed was more energy-saving than through throttling,which would help to reduce the weight of the system.However,the pressure drop of the injector was easily to be too low when the depth of thrust adjustment was large.Although the throttling regulation did not have the low injector pressure drop problem,but it used more energy.Therefore,deep thrust adjustment must combine two kinds of adjustment methods.To be specific,the speed adjustment was the first choice,when the injection pressure drop was insufficient,then the throttle adjustment followed.During the thrust adjustment process,the pressure,the thrust,the mixing ratio and the angular acceleration lift of the centrifugal pump could all be affected by the time constant of the motor.The smal-ler the time constant,the shorter time for the above parameters to reach the steady state,at the same time,the changes of the mixing ratio and additional angular acceleration lift would be greater,so the normal work of the engine would be impacted.

关 键 词：电动泵压式液体火箭发动机 系统仿真 AMESIM 

分 类 号：V4[航空宇航科学技术]