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[1]张晓光,程 诚,刘 宇.塞式喷管运载器外流干扰冷流试验研究[J].火箭推进,2015,41(03):46-51.
　ZHANG Xiao-guang,CHENG Cheng,LIU Yu.Cold flow test of outflow influence on vehicle with aerospike nozzle[J].Journal of Rocket Propulsion,2015,41(03):46-51.
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塞式喷管运载器外流干扰冷流试验研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 41 期数: 2015年03期 页码: 46-51 栏目: 研究与设计 出版日期: 2015-06-30
Title:
Cold flow test of outflow influence on vehicle with aerospike nozzle
作者:
张晓光1; 程 诚2; 刘 宇3
西安航天动力研究所，陕西 西安 710100；2. 中航商用航空发动机有限责任公司，上海 201108； 3. 北京航空航天大学，北京 100191
Author(s):
ZHANG Xiao-guang1;  CHENG Cheng2;  LIU Yu3
1. Xi’an Aerospace Propulsion Institute, Xi’an 710100, China; 2. AVIC Commercial Aircraft Engine Co., Ltd., Shanghai 201108, China; 3. Beijing Univ. of Aeronautics and Astronautics, Beijing 100191, China
关键词:
塞式喷管; 升力体; 外流干扰; 风洞; 冷流试验
Keywords:
aerospike nozzlelift bodyoutflow interferencewind tunnelcold flow test
分类号:
V434-34
文献标志码:
A
摘要:
采用风洞冷流试验方法研究了使用塞式喷管的运载器在4个典型飞行马赫数下外流对运载器流场和性能的影响。试验模型由截短的线性塞式喷管和升力体构成，利用纹影显示技术得到了塞式喷管流场结构并测量了不同试验工况下模型的轴向力和升力。结果表明：外流使塞式喷管喷流的膨胀程度变大，横向侧流强度增强；外流干扰下塞式喷管的推力损失包括过膨胀损失和横向侧流损失，试验喷管总推力损失在4.7%～9.6%之间，其中过膨胀损失在3%以内。
Abstract:
Cold flow tests on effects of outflow on flow field and performance of vehicle with aerospike nozzle during flight with four typical Mach numbers are presented in this paper. The model for cold flow test is composed of a truncated linear plug nozzle and a lift body. In the tests, the nozzle flow field structure was displayed with schlieren display technology, and the axial and lift forces of the model were measured under different conditions. The results show that the existence of outflow leads to an increase in nozzle jet expansion degree and lateral flow intensity, and the thrust loss (includes over expansion loss and lateral flow loss) of aerospike nozzle, caused by outflow, is between 4.7% and 9.6% , in which the over

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备注/Memo

收稿日期：2014-12-26；修回日期：2015-01-29 作者简介：张晓光（1986—），男，博士，研究领域为液体火箭推进技术

更新日期/Last Update: 1900-01-01