航天推进技术研究院主办
[1]王一白,刘宇,覃粒子.瓦状塞式喷管的设计和试验分析[J].火箭推进,2008,34(01):1-6.
Wang Yibai,Liu Yu,Qin Lizi.Design and experimental analysis of tile-shaped aerospike nozzles[J].Journal of Rocket Propulsion,2008,34(01):1-6.
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Wang Yibai,Liu Yu,Qin Lizi.Design and experimental analysis of tile-shaped aerospike nozzles[J].Journal of Rocket Propulsion,2008,34(01):1-6.
瓦状塞式喷管的设计和试验分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
34
期数:
2008年01期
页码:
1-6
栏目:
研究与设计
出版日期:
2008-02-29
- Title:
- Design and experimental analysis of tile-shaped aerospike nozzles
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 为了分析瓦状塞武喷管的气动特性。提出轴对称内喷管和塞锥的型面设计方 法，设计了两单元的模型发动机，内喷管面积比为5．8l，总面积比为24．36、29．43、33．88、 37．58。采用高压空气为介质对模型发动机进行冷流试验，分析内喷管倾角和底部二次流变化、 以及有无底部盖板对推力性能和底部压强的影响情况。介绍了试验发动机的结构与设计参数． 给出了试验模型照片、测量参数曲线和性能数据处理。结果表明：瓦状塞式喷管模型的高度 补偿效果较为明显，在整个工作高度有较高的推力系数效率，200模型的最高效率为96％；底 部压强凸线反映出了底部气动特性由开放状态到闭合的转变过程；内喷管倾角增大，底部压 强增大即增加底部推力．但存在一个优化性能的最佳倾角；底部加入二次流可以增加底部压 强，提高性能，但其影响范围在1％一2％，少量的二次流对增加性能的效果较好；底部盖板会 影响底部的气动特性．底部压强是否受环境压强的影响取决于底部处于开放或闭合状态。
- Abstract:
- Simple design methods of the tile-shaped aerospike nozzle with the axisymmetric thrust cell and the concave plug were presented，and the two-module experimental models were designed． The area ratio of internal nozzle is 5．8 1 and the total area ratios of the aerospike models are 24．36，29．43，33．88 and 37．58．Cold-flow tests on the tile-shaped models were carried out using hig}lly pressurized air．The effects of the variations of the inclination ansle and the amount of base bleed on the performance and the base pressure were examined in the tests．Test apparatus，struc-tures photographs and design parameters of the main parts of the experimental engine were introduced． Chamber pressure，thrust and ambient pressure were acquired and the data analyses were al- 80 delivered．It is shown that good altitude compensation capacities and hi【gh efficiencies were obtained in the tests．The maximum nozzle thrust efficiency of the tile-shaped nozzles tested here is 96％．The base pressure increases when the inclination ansle becomes bigger and there is an optimum tingle for the optimum performance．The bleed Call increase the base pressure，the effect of bleed on the performance is within 1％-2％and a little bleed can improve the performance effectivly． The effects’of base sidewalls on base pressure were also analyzed．The results indicate that whether the base pressure changes with the ambient backpressure or not depends on the base region is working at open or closed condition．
参考文献/References:
[1]Vuilamy D，Duthoit V，Berry W．European Investigation of
Clustered Hug Nozzles[R]．AIAA 99-2350．
[2]Onofri M．Plug Nozzles：Summery of Flow Features and
Engine Performance[R]．ALAA 2002_0584．
[3]Tomita T'Takahashi M，Tamura H．Flow Field of Clustered Plug Nozzles[R]．AM 97-3219．
[4]戴梧叶．塞式喷管的实验与数值模拟研究[D]．北京：北京
航空航天大学．2002．
[5]覃粒子．塞式喷管型面设计与优化[D]．北京：北京航空航
天大学。2004．
[6]王一白．塞式喷管的性能实验与系统设计研究叫．北京：
北京航空航天大学。2004．
[7]王长辉．塞式喷管气动特性的实验和数值模拟研究[D]．
北京：北京航空航天大学．2005．
[8]戴梧叶，刘字，马彬，等．。瓦”状塞式喷管的数值模拟与
实验[J]．推进技术，2002，23(4)：292—297．
[9]Rao G．Spike Nozzle Contour for Optimum Thrust[J]．Ballistic Missile and space Technology，1961，V01．2，92_101．
[10]Angelino G．Approximate Method for Plug Nozzle Design
[J]．AIAAJournal，1964，2(10)：1934-1935．
[11]Wang Y'QinL Liu Y，etaL Cold-flow Experimental Stud-ies on Performance of the Tile-shaped Aerospike Nozzles
[R]．AnA 2007-5477．
[12]Tomita T'Takahashi M，Ododera T，et a1．E＆cts of Base Bleed on Thrust Performance of a Linear Aerospike Nozzte[R]．AIA A 99—2586．
备注/Memo
收稿日期：2007-08—16；修回日期：2007—10-02。国家发明专利：塞式喷管[ZL02158695．0]。 作者简介：王一白(197扣)，男，博士。讲师，研究领域为先进航天推进理论与技术。 万方
更新日期/Last Update:
1900-01-01