Design and integrated simulation of a pressurized feed system of the dual-thrust hybrid rocket motor

作     者：LI JunHai YU NanJia ZENG Peng CAI GuoBiao 

作者机构：School of AstronauticsBeihang University 

出 版 物：《Science China(Technological Sciences)》 (中国科学（技术科学英文版）)

年 卷 期：2013年第56卷第4期

页      码：989-1000页

摘      要：A new pressurized feed system of the dual-thrust hybrid rocket motor for flight is presented in this *** feed system supplies 90% hydrogen peroxide (90%H 2 O 2) with two different flows of 4.5 and 2 kg s *** oxidizer flow is changed through regulating the mass flow of the high-pressure gas and switching the performance modes of the unique oxidizer flow control valve *** models of the gas storage container,pressure regulator valve,control orifice,propellant tank,oxidizer flow control valve and cavitating venturi are generated and used to compute the instantaneous pressure,temperature and mass flow *** is a good agreement between the simulated and experimental *** sensitivity analysis is also *** is found that the throat diameter of the cavitating venturi in feed line 1 is the main factor affecting the mass flow in both boost and sustaining *** parameters have limited effects on the mass flow rate and the transition time of the system.

主 题 词：pressurized feed system mathematical modeling liquid propellant tank variable flow dual-thrust hybrid motor 

学科分类：080703[080703] 082502[082502] 08[工学] 0807[工学-电子信息类] 0825[工学-环境科学与工程类] 

核心收录：

D　O　I：10.1007/s11431-013-5156-y

馆 藏 号：203319468...