Research on wagon-wheel fuel grain parametric design and internal ballistics performance of hybrid rocket motor
-
摘要:
装药设计和内弹道性能特性研究可为固液火箭发动机的设计和优化提供基础。建立了固液火箭发动机装药设计和内弹道计算的流程与方法，根据燃面退移规律，获得了车轮形装药燃烧面积、药柱通道面积等参数随燃去肉厚的变化关系。针对给定的设计指标及动力系统方案，开展了有中心孔车轮形、无中心孔车轮形、双D形及管形装药方案设计。计算结果表明：在相同的设计要求下，车轮形装药具有更大的燃烧面积、更高的装填分数及更小的药柱长径比；管形装药的氧燃比、燃烧室压强、推力等性能参数随时间变化更小；减小药柱外径可提高管形、双D形装药的装填分数，但同时会提高药柱的长径比。研究结果对车轮形装药固液火箭发动机内弹道特性及规律的认识可起到较好的支撑作用。
Abstract:The study of fuel grain design and internal ballistic performance can provide the foundation for the design and optimization of hybrid rocket motor. Fuel grain design and internal ballistics calculation process and method of hybrid rocket motor were established. Based on the fuel regression rate law, the variation relationships of burning area and fuel port area with fuel thickness of the wagon-wheel fuel grain were obtained. For certain design specifications and propulsion system scheme, fuel grain schemes were designed for wagon-wheel fuel grain with central port, wagon-wheel fuel grain without central port, double-D fuel grain, and tube fuel grain. The calculation results show that wagon-wheel fuel grain can provide larger burning area, higher propellant loading fraction, and lower length-to-diameter ratio. For tube fuel grain, variations of oxidizer-to-fuel ratio, combustion pressure and thrust with time are much less. Decreasing the fuel diameter can increase the propellant loading fraction of tube and double-D fuel grains. However, the length-to-diameter ratio increases at the same time. The results can provide a good support for the understanding of the internal ballistic characteristics and laws of hybrid rocket motors with wagon-wheel fuel grain.
-
图 2 有中心孔车轮形装药示意图
Figure 2. Schematic diagram of wagon-wheel fuel grain with central port
图 3 无中心孔车轮形装药示意图
Figure 3. Schematic diagram of wagon-wheel fuel grain without central port
图 5 特征速度和真空比冲随氧燃比变化
Figure 5. Variation of characteristic velocity and vacuum specific impulse with oxidizer-to-fuel ratio
图 6 各装药设计方案横截面示意图
Figure 6. Schematic diagram of cross section of different fuel grain design schemes
图 7 燃线长度和药柱通道面积随时间变化
Figure 7. Variation of burning line length and fuel port area with time
图 8 氧化剂流率和燃速随时间变化
Figure 8. Variation of oxidizer mass flow rate and fuel regression rate with time
图 9 氧燃比、燃烧室压强和推力随时间变化
Figure 9. Variation of oxidizer-to-fuel ratio, combustion pressure and thrust with time
表 1 各装药设计方案主要结果
Table 1. Main results of different fuel grain design schemes
方案 药型 D/mm L/mm e/mm η/% α t/s pc/MPa F/N L/D 方案1 有中心孔车轮形 300 606 22 68.05 3.16 80.3 3.976 5 000.3 2.02 方案2 无中心孔车轮形 300 625 22 67.80 3.14 80.2 3.980 5 004.3 2.08 方案3 双D形 300 1 051 19 37.81 3.16 81.7 3.976 5 000.2 3.50 方案4 管形 300 1 730 18 22.56 3.15 82.0 3.980 5 004.2 5.77 方案5 双D形 233 1 012 29 67.07 3.15 80.8 3.976 5 000.6 4.34 方案6 管形 179 1 585 39 68.16 3.15 80.9 3.978 5 001.9 8.85 
下载: 导出CSV
-
[1] ALTMAN D. Hybrid rocket development history: AIAA-1991-2515[R].Reston: AIAA, 1991. [2] MARTIN J C, KENNETH K K.Fundamentals of hybrid rocket combustion and propulsion[M].Reston:AIAA, 2006:1-33. [3] FRANKLIN B M.Early developments in hybrid propulsion technology at the air force rocket propulsion laboratory: AIAA-1995-2946[R].Reston: AIAA, 1995. [4] EVANS B, BOYER E, KUO K K, et al.Hybrid rocket investigation at Penn State University's high pressure combustion laboratory: Overview and recent results: AIAA-2009-5349[R].Reston: AIAA, 2009. [5] ESTEY P N, FLITTIE K J.Aquila: The next generation launch service for small satallites: AIAA-1992-1844[R].Reston: AIAA, 1992. [6] TSOHAS J, APPEL B, RETTENMAIER A, et al.Development and launch of the Purdue hybrid rocket technology demonstrator: AIAA-2009-4842[R].Reston: AIAA, 2009. [7] ARVES J, GNAU M, KOINER K, et al.Overview of the hybrid sounding rocket (HYSR) project: AIAA-2003-5199[R].Reston: AIAA, 2003. [8] LARSEN C R.Development of guide to commercial space transportation reusable launch vehicle operations & maintenance: AIAA-2005-6795[R].Reston: AIAA, 2005. [9] ESTEY P, ALTMAN D, MCFARLANE J.An evaluation of scaling effects for hybrid rocket motors: AIAA-1991-2517[R].Reston: AIAA, 1991. [10] HORI K.Application of glycidyl azide polymer to hybrid rocket motor: AIAA-2009-5348[R].Reston: AIAA, 2009. [11] EINAV O, PERETZ A, HASHMONAY B, et al.Development of a lab-scale system for hybrid rocket motor testing: AIAA-2009-4888[R].Reston: AIAA, 2009. [12] FARLANE J S, KNIFFEN R J, LICHATOWICH J.Design and testing of AMROC's 250000 lbf thrust hybrid motor: AIAA-1993-2551[R].Reston: AIAA, 1993. [13] STORY G, ZOLADZ T, ARVES J, et al.Hybrid propulsion demonstration program 250 K hybrid motor: AIAA-2003-5198[R].Reston: AIAA, 2003. [14] FARBAR E, LOUWERS J, KAYA T.Investigation of metallized and nonmetallized hydroxyl terminated polybutadiene hydrogen peroxide hybrid rockets[J].Journal of Propulsion and Power, 2007, 23(2):476-486. doi: 10.2514/1.22091 [15] LEWIN A, DENNIS J, CONLEY B, et al.Experimental determination of performance parameters for a polybutadiene/oxygen hybrid rocket: AIAA-1992-3590[R].Reston: AIAA, 1992. [16] ESTEY P N, MCFARLANE J S, KNIFFEN R J, et al.Large hybrid rocket testing results: AIAA-1993-4279[R].Reston: AIAA, 1993. [17] KNIFFEN R J, MCKINNEY B, ESTEY P.Hybrid rocket development at the American Rocket Company: AIAA-1990-2762[R].Reston: AIAA, 1990. [18] 王铮, 胡永强.固体火箭发动机[M].北京:中国宇航出版社, 1993:61-66.WANG Z, HU Y Q.Solid rocket motor[M].Beijing:China Aerospace Publishing House, 1993:61-66(in Chinese). [19] 李新田, 曾鹏, 田辉, 等.H2O2/HTPB缩比固液火箭发动机药柱燃速试验研究[J].固体火箭技术, 2011, 34(4):457-461. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=gthjjs201104013LI X T, ZENG P, TIAN H, et al.Experimental study on burning rate of sub-scale H2O2/HTPB hybrid rocket motor grain[J].Journal of Solid Rocket Technology, 2011, 34(4):457-461(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=gthjjs201104013 -
下载:
点击查看大图
计量
- 文章访问数: 620
- HTML全文浏览量: 85
- PDF下载量: 241
- 被引次数: 0
