摘要
为解决传统低温利用系统控制方法存在调节阀门的动作次数多等不足的问题,提出一种基于飞行中推进剂实时偏差计算的变门限利用系统控制方法,可根据飞行时间实时改变调节门限。与传统的利用系统调节方法相比,这种调节方法在保证调节能力的同时,可以确保对发动机利用调节阀门的动作次数最少,对发动机系统和组件的影响也较小。通过仿真计算和飞行试验表明,该方法在满足利用系统调节要求的同时,可以明显减少发动机利用调节阀门的动作次数。
A variable threshold adjustment method is proposed,which is based on real-time propellant deviation calculation.The adjustment threshold can be changed in real time depending on the flight time.Compared with the traditional adjustment method,this method ensures the ability to adjust while ensuring that the engine adjusts the valve with minimal action,the impact on engine components and systems is also minimal.The effect of variable threshold adjustment method is shown by simulation and flight test,this method can obviously reduce the number of times the engine uses the adjustment valve while meeting the requirements of using the system adjustment.
作者
刘秉
李东
杨虎军
何巍
董余红
Liu Bing;Li Dong;Yang Hu-jun;He Wei;Dong Yu-hong(Beijing Institute of Astronautical Systems Engineering,Beijing,100076;Northwestern Polytechnical University,Xi′an,710072;China Academy of Launch Vehicle Technology,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2021年第3期1-5,共5页
Missiles and Space Vehicles
关键词
低温推进剂利用系统
仿真平台
变门限
cryogenic propellant utilization system
simulation platform
variable threshold
