分级燃烧循环

分级燃烧循环发动机变工况的模糊控制

Fuzzy Control in Changing Conditions for Staged Combustion Cycle Engine

分级燃烧循环火箭发动机的动态特性研究

Dynamic Characteristic Study of Staged Combustion Cycle Rocket Engine

基于分布参数线性化模型的分级燃烧循环液体火箭发动机频率特性计算

Frequency Characteristics Computation of Liquid Rocket Engine Based on Distributed Parameter Models

分级燃烧循环发动机启动过程的变结构控制

Variable Structure Control in the Start Process for Staged Combustion Cycle Engine

液体发动机分级燃烧循环最高室压通用模块化计算方法

A general modular method for calculating the maximum combustion chamber pressure of the liquid engine with stage combustion cycles

针对分级燃烧循环液体火箭发动机启动过程的特点，提出了一种变结构控制系统。

A variable structure control system for the start up process of staged combustion cycle liquid rocket engine is presented in this paper .

本文给出了用该程序对采用液氧、丙烷作为推进剂的分级燃烧循环进行计算的结果。

The stage combustion cycle using the liquid oxygen and methane as propellant is calculated with the program , and the calculation results are also given .

研究了一种模糊控制方法，并用于分级燃烧循环液体火箭发动机变工况过程的反馈控制。

A fuzzy control is studied , which is used for the feedback control in the changing condition process of the staged combustion cycle liquid rocket engine .

本文通过对国内外分级燃烧循环发动机和有关单级入轨发动机涡轮泵研究结果的分析，提出了三组元涡轮泵性能参数的限制范围与要求。

Domestic and international study results of staged combustion cycle engines and turbopumps of single-stage-to-orbit ( SSTO ) engines are analyzed . According to these analysis results , range limits and requirements of tripropellant turbopump performance parameters are derived .

阐述了涡轮泵的技术发展水平在液体火箭发动机研制中的重要地位；分级燃烧循环系统发动机涡轮泵的设计特色；

The following contents are discussed in the paper , the essential position of turbopump technology in liquid rocket engine development , the design charateristics of turbopump for stage-combustion engines , and the general assembling design features of turbopumps in USSR .