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

作　　者：黄卫东[1] 朱恒伟[1] 王克昌[1] 陈启智[1] 

机构地区：[1]国防科技大学

出　　处：《上海航天》1997年第2期11-15,共5页Aerospace Shanghai

摘　　要：提出了一种新的液体火箭发动机分级燃烧循环最高室压计算方法。该方法按照预定的计算顺序，对发动机系统的各个模块进行叠代计算，采用拟牛顿法求解系统未知量。该方法对各种分级燃烧循环方式最高室压的计算具有通用性，已在计算机上采用面向对象程序设计实现。给出了用该程序对ＲＤ－１２０和ＲＤ－７０４发动机最高室压进行计算的结果。A new modular method for calculating the maximum combustion chamber pressure with stage combustion cycles is proposed in this paper.The modules of the engine system are calculated iteratively in a predetermined sequence,and a modified Newton method is used to find the unknown variables of the system.This method is general for calculating the maximum chamber pressure of the liquid rocket engine with stage combustion cycles.The program based on the method is achieved by the object oriented programming.The maximum combustion chamber pressures of RD 120 and RD 704 are calculated with the program,and the calculation results are also given.

关 键 词：液体火箭发动机 分级燃烧循环 室压 模块化 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]