| Citation: | LIU Changguo, SHI Zhehang, CHEN Hongyu, et al. Test on working characteristics of 490 N engine for satellites under off-rated conditions[J]. Journal of Aerospace Power, 2022, 37（12）：2771-2781 doi: 10.13224/j.cnki.jasp.20210726
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Accurately mastering the working characteristics and margin of liquid rocket engine under different parameters is crucial to its reliability. High-altitude simulation and ground hot fire tests of the second generation 490 N engine under off-rated conditions were carried out, and the influence of thrust and mixing ratio changes on the engine working characteristics was studied. Results indicated that, the engine can work normally within the wide envelope scope of mixing ratio 1.54—1.80 and vacuum thrust 372—584 N under high-altitude simulation environment. With the increase of thrust, the vacuum specific impulse and throat temperature both rose, the combustion chamber efficiency increased, kept stable and decreased in turns, and the nozzle efficiency increased slightly. As the mixing ratio increased, the vacuum specific impulse and throat temperature also increased, the combustion chamber efficiency did not change obviously, and the nozzle efficiency decreased slightly. For the rated mixing ratio, the combustion chamber pressure fluctuated smoothly within the range of 0.61—1.56 MPa, enabling to work with the vacuum thrust of 345—900 N. However, it produced combustion oscillation of low/middle frequency (207 Hz) coupled with the feed system at 0.51 MPa. The intensifying erosion of hot flow and increasing temperature in the throat under high working conditions accelerated the loss of coating, which reduced the long-term working life of engine. Nonetheless, it can still meet the working life requirements of 25 000 s for satellite identification within a certain off-rated range and single ignition duration.
| [1] |
LIU C G,CHEN J,HAN H Y,et al. A long duration and high reliability liquid apogee engine for satellites[J]. Acta Astronautica,2004,55: 401-408. doi: 10.1016/j.actaastro.2004.05.030
|
| [2] |
STECHMAN C, KRISMER D, UENO F. Off-limit testing of the model R-4D 110 IBF (490 N) bipropellant rocket engine[R]. AIAA-2004-3694, 2004.
|
| [3] |
杨成虎,林庆国,刘昌国. 高性能液体远地点发动机技术发展[J]. 火箭推进,2013,39(4): 1-7,40. YANG Chenghu,LIN Qingguo,LIU Changguo. Technology development of high-performance liquid apogee engine[J]. Journal of Rocket Propulsion,2013,39(4): 1-7,40. (in Chinese doi: 10.3969/j.issn.1672-9374.2013.04.001
|
| [4] |
ZIDEK R A, KOLMANOVSKY I V. Deterministic drift counteraction optimal control for attitude control of spacecraft with time-varying mass[R]. AIAA-2016-0369, 2016.
|
| [5] |
赵婷,陈夏超,杨成虎,等. 面向高轨卫星的液体轨控发动机研制进展[J]. 火箭推进,2018,44(1): 1-7, 21. ZHAO Ting,CHEN Xiachao,YANG Chenghu,et al. Developing progress of liquid bipropellant orbit control engine for high orbit satellite[J]. Journal of Rocket Propulsion,2018,44(1): 1-7, 21. (in Chinese doi: 10.3969/j.issn.1672-9374.2018.01.001
|
| [6] |
刘昌国,赵婷,姚锋,等. 第二代490 N轨控发动机研制及在轨飞行验证[J]. 推进技术,2020,41(1): 49-57. LIU Changguo,ZHAO Ting,YAO Feng,et al. Development and on-orbit flight verification of the second generation 490 N liquid apogee engine[J]. Journal of Propulsion Technology,2020,41(1): 49-57. (in Chinese doi: 10.13675/j.cnki.tjjs.190343
|
| [7] |
JASSOWSKI D M, ROSENBERG S D, SCHOENMAN L. Durability testing of the AJ10-221 490 N high performance (321 sec Isp) engine[R]. AIAA-1993-2130, 1993.
|
| [8] |
CHAZEN M L, SICHER D. High performance bipropellant rhenium engine[R]. AIAA-1998-3356, 1998.
|
| [9] |
GRAY C. Development of a 1 10l bf dual mode liquid apogee engine[R]. AIAA-1990-2424, 1990.
|
| [10] |
SCHULTE G. High performance 400 N MMH/NTO bipropellant engine for apogee boost maneuvers[R]. AIAA-1999-2466, 1999.
|
| [11] |
刘昌国,赵婷,陈锐达,等. 星用490 N发动机喷注器局部燃气泄漏试验[J]. 航空动力学报,2021,36(3): 664-672. LIU Changguo,ZHAO Ting,CHEN Ruida,et al. Test on injector local gas leakage of 490 N engine for satellites[J]. Journal of Aerospace Power,2021,36(3): 664-672. (in Chinese
|
| [12] |
陈泓宇,吴凌峰,赵婷,等. 490 N发动机身部局部燃气泄漏时工作状况试验分析[J]. 推进技术,2021,42(8): 1848-1854. CHEN Hongyu,WU Lingfeng,ZHAO Ting,et al. Experimental analysis of 490 N engine working conditions with body local gas leakage[J]. Journal of Propulsion Technology,2021,42(8): 1848-1854. (in Chinese doi: 10.13675/j.cnki.tjjs.200661
|
| [13] |
林庆国. 空间轨控发动机高效燃烧室仿真与试验研究[D]. 长沙: 国防科技大学, 2015.
LIN Qingguo. Simulation and experiment research on the high efficient combustion chamber for space orbit maneuvering rocket engine[D]. Changsha: National University of Defense Technology, 2015. (in Chinese)
|
| [14] |
王慧洁,许坤梅. 液体火箭发动机燃烧室壁液膜冷却的数值模拟[J]. 航空动力学报,2018,33(11): 2660-2668. WANG Huijie,XU Kunmei. Numerical simulation of liquid film cooling for combustion chamber wall of liquid rocket engine[J]. Journal of Aerospace Power,2018,33(11): 2660-2668. (in Chinese doi: 10.13224/j.cnki.jasp.2018.11.012
|
| [15] |
张奎好,王成刚. 变轨发动机大型高空模拟试验台[J]. 导弹与航天运载技术,2004,33(1): 57-60. ZHANG Kuihao,WANG Chenggang. Large altitude simulation test stand for orbit maneuver motor[J]. Missiles and Space Vehicles,2004,33(1): 57-60. (in Chinese doi: 10.3969/j.issn.1004-7182.2004.01.011
|
| [16] |
蔡国飙, 李家文, 田爱梅, 等. 液体火箭发动机设计[M]. 北京: 北京航空航天大学出版社, 2011.
|
| [17] |
杨立军, 富庆飞. 液体火箭发动机推力室设计[M]. 北京: 北京航空航天大学出版社, 2013.
|
| [18] |
孙得川,陈杰,林庆国. 喷管性能的化学动力学分析[J]. 推进技术,2003,24(3): 222-224. SUN Dechuan,CHEN Jie,LIN Qingguo. Chemical kinetics analysis for nozzle performance[J]. Journal of Propulsion Technology,2003,24(3): 222-224. (in Chinese doi: 10.3321/j.issn:1001-4055.2003.03.009
|
| [19] |
孙得川,陈杰,刘昌国,等. 喷管性能计算的软件实现[J]. 上海航天,2002(6): 18-20, 50. SUN Dechuan,CHEN Jie,LIU Changguo,et al. Software of one-dimensional nozzle performance calculation[J]. Aerospace Shanghai,2002(6): 18-20, 50. (in Chinese doi: 10.19328/j.cnki.1006-1630.2002.06.005
|
| [20] |
李志勋,王宏亮,赵 曙,等. 液体轨控发动机真空矢量推力现场校准影响因素分析[J]. 载人航天,2019,25(6): 715-719, 748. LI Zhixun,WANG Hongliang,ZHAO Shu,et al. Analysis of influence factors on field calibration of vacuum vector thrust for liquid attitude control engine[J]. Manned Spaceflight,2019,25(6): 715-719, 748. (in Chinese doi: 10.3969/j.issn.1674-5825.2019.06.003
|
| [21] |
MANSKI D,HAGEMANN G. Influence of rocket design parameters on engine nozzle efficiencies[J]. Journal of Propulsion and Power,1993,12(1): 41-47.
|
| [22] |
ARIF K, JOSE S, BRIAN C. Investigation of feed system coupled low frequency combustion instabilities in hybrid rockets[R]. AIAA-2007-5366, 2007.
|
| [23] |
刘上,刘红军,孙宏明,等. 液体火箭发动机中频耦合振荡初步研究[J]. 推进技术,2013,34(1): 101-108. LIU Shang,LIU Hongjun,SUN Hongming,et al. Preliminary study of medium frequency coupled oscillation in liquid rocket engine[J]. Journal of Propulsion Technology,2013,34(1): 101-108. (in Chinese doi: 10.13675/j.cnki.tjjs.2013.01.020
|
| [24] |
MARCO L, FRANCESCO D M, JOHAN S, et al. System analysis of low frequency combustion instabilities in liquid rocket engines[R]. AIAA-2015-4208, 2015.
|
| [25] |
MATTHEW J C,JAMES R H,VIGOR Y. Liquid-propellant rocket engine throttling: a comprehensive review[J]. Journal of Propulsion and Power,2010,26(5): 897-923. doi: 10.2514/1.49791
|
| [26] |
潘兆义,赵青芮,王国强,等. 铌铪合金表面硅化物涂层的高温失效行为分析[J]. 火箭推进,2019,45(2): 66-73. PAN Zhaoyi,ZHAO Qingrui,WANG Guoqiang,et al. Failure behavior analysis of silicide coating on Nb-Hf alloy at surface high temperature[J]. Journal of Rocket Propulsion,2019,45(2): 66-73. (in Chinese doi: 10.3969/j.issn.1672-9374.2019.02.011
|
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