空间涡轮发电系统设计及性能特性仿真分析  

Design and Simulation Analysis of Performance Characteristics of Space Turbine Power Generation System

作　　者：韩灿 李育隆[1] 田林 于新刚[2] 王鹏程 HAN Can;LI Yulong;TIAN Lin;YU Xingang;WANG Pengcheng(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]北京空间飞行器总体设计部,北京100094

出　　处：《载人航天》2023年第1期110-117,共8页Manned Spaceflight

摘　　要：为解决空间飞行器应急发电问题,利用空间飞行器携带的推进剂为能量源,设计了一套空间涡轮发电系统,建立了稳态及启动过程的数学模型,对系统的稳态和启动特性进行了仿真分析。结果表明:空间涡轮系统可以利用推进剂实现高功率发电,系统可以启动和稳定运行;系统在设计点稳定运行时,推进剂流量为2.1 g/s,燃气发生器室压为1.3 MPa,燃气发生器出口温度为1200 K,输出电功率达到1500 W;当系统运行参数发生扰动偏离设计点时,系统性能会相应变化,混合比不变且氧化剂贮箱增压压力大于设计点0.5 MPa时,涡轮输出功率变为设计值的1.64倍;系统启动过程仿真得到的性能参数和稳态设计值相对误差小于2%,验证了系统设计的合理性。To solve the emergency power generation problem of space vehicles,a space turbine power generation system using the liquid propellant within the space vehicles as energy source was designed.Mathematical models of steady state and starting process of the system were built.Steady state characteristics and starting process characteristics of the system were analyzed by means of simulation.The results showed that the propellant energy could be fully used to generate high power electricity through this system and the system could start and run stably.The propellant flow rate was 2.1 g/s,the gas generator pressure was 1.3 MPa,and the gas generator temperature was 1200 K when the system operated stably at the design point which could generate 1500 W of electrical power.The performance parameters of the system were changed when the operating parameters deviated from the design point.The turbine power was 64%higher than that at design point when the oxidizer tank pressure was increased by 0.5 MPa from the design point.The relative error between the performance parameters obtained from the system starting process simulation and the steady-state design value was less than 2%,which verified the rationality of the system design.

关 键 词：空间飞行 涡轮发电 系统设计 性能仿真 能量利用 

分 类 号：TK05[动力工程及工程热物理]