航天推进技术研究院主办
[1]黄仕启,李锦江,孙慧娟.某型膨胀循环发动机高空模拟试验方案研究[J].火箭推进,2017,43(05):39-44.
HUANG Shiqi,LI Jinjiang,SUN Huijuan.Research on altitude simulation test scheme forexpand cycle engine[J].Journal of Rocket Propulsion,2017,43(05):39-44.
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HUANG Shiqi,LI Jinjiang,SUN Huijuan.Research on altitude simulation test scheme forexpand cycle engine[J].Journal of Rocket Propulsion,2017,43(05):39-44.
某型膨胀循环发动机高空模拟试验方案研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
43
期数:
2017年05期
页码:
39-44
栏目:
研究与设计
出版日期:
2017-10-15
- Title:
- Research on altitude simulation test scheme for expand cycle engine
- 分类号:
- V433.9-34
- 文献标志码:
- A
- 摘要:
- 某型膨胀循环发动机在研制初期基于环境压力可能对膨胀循环发动机起动加速性有较大影响的考虑,采用了全程主动引射高空模拟试验方案,试验结果显示环境压力对发动机起动加速性的影响较小。发动机室压和喷管面积比是影响引射方式的主要参数,该型膨胀循环发动机与采用被动引射的某型燃气发生器循环发动机参数相当,这为该型膨胀循环发动机采用被动引射提供了可能,并对膨胀循环发动机采用被动引射高空模拟试验方案的可行性进行仿真研究。
- Abstract:
- Based on the principal that the starting acceleration performance of an expand cycle engine was possibly affected by the ambient pressure in its developing beginning phase,a test scheme of the positive ejection altitude simulation was selected.The test results show that the ambient pressure affects the starting acceleration performance slightly,the chamber pressure and nozzle area ratio of the expand cycle engine are the main parameters affecting the ejection form,and the parameters of a certain gas generator cycle engine with passive ejection are quite same as that of the expand cycle engine,which provide a possible selection for the expand cycle engine to adopt the passive ejection form.Therefore,the feasibility research on the passive ejection altitude simulation test scheme for the expand cycle engine is carried out in this paper.
参考文献/References:
[1] 周德兴,孟庆富.固体火箭发动机测试与试验技术[M].北京:宇航出版社,1994.
[2] SCHÄFER Klaus. Altitude simulation bench for VINCI engine [C]// proceedings of 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Huntsville, Alabama, 2003: 20-23.
[3] 徐万武,谭建国,王振国. 高空模拟试车台超声速引射器数值研究[J]. 固体火箭技术,2003,26(2):71-74
[4] ASHOKKUMAR R, SANKARAN S. Investigation on the performance of second throat supersonic exhaust diffuser for starting higher area ratio nozzles: AIAA 2012-3294 [R]. USA: AIAA, 2012.
[5] 朱子勇,李培昌,瞿骞. 某型号火箭发动机高空模拟试验中扩压器的数值计算与试验比较[J]. 航天器环境工程. 2010,27(4):231-237
[6] 陈健,吴继平,王振国,徐万武. 高空模拟试验台主被动引射方案数值研究[J]. 固体火箭技术. 2011,34(1):126-129.
[7] 张忠利. 超音速二次喉道扩压器气动特性研究[J]. 火箭推进. 2001,27(3):14-22.
ZHANG Zhongli. Research on aerodynamic characteristics of supersonic second-throat diffuser [J]. Journal of rocket propulsion, 2001, 27(3): 14-22.
[8] YEN J C, SAUNDERS G P. Startup and shutdown simulations of a supersonic ejector-diffuser system using CESE method: AIAA 2007-5817 [R]. USA: AIAA, 2007.
[9] 王永忠. 液体火箭发动机高空模拟试验及环境治理[J]. 火箭推进. 2000,26(6):8-20.
WANG Yongzhong. Altitude simulation test and environmental governance of liquid rocket engine [J]. Journal of rocket propulsion, 2000, 26(6): 8-20.
[10] ASHOKKUMAR R, SANKARAN S. Investigation on the performance of second throat supersonic exhaust diffuser for starting higher area ratio nozzles: AIAA 2012-3294 [R]. USA: AIAA, 2012.
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备注/Memo
收稿日期:2017-03-17; 修回日期:2017-06-20 作者简介: 黄仕启(1981—),男,高级工程师,研究领域为液体火箭发动机系统设计
更新日期/Last Update:
2017-11-10