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摘要:
氧化亚氮(N2O)作为一种无毒绿色、稳定安全的自增压推进剂，广泛应用于单组元和双组元火箭发动机，尤其在姿轨控动力领域具有重要的研究价值与应用潜力。对几类氧化亚氮推进系统的发展历程与研究现状进行综述，总结氧化亚氮推进系统的特点，指出推动其工程应用的关键技术，并进一步展望了氧化亚氮推进技术在姿轨控动力方向的未来研究重点，以期为航天姿轨控动力系统的创新与工程实践提供参考。
Abstract:Both monopropellant and bipropellant rocket engines frequently employ nitrous oxide (N2O) as a non-toxic, stable, and secure self-pressurizing propellant. It holds significant research value and application potential, especially in the field of attitude and orbit control propulsion. In addition to outlining research priorities and development recommendations for N2O propulsion technology in the field of attitude and orbit control, this paper reviews the development history and current research status of several types of nitrous oxide-based propulsion systems, summarizes their features and advantages, and identifies the key technologies facilitating their engineering application. The aim is to provide valuable references for the innovation and engineering practice of aerospace attitude and orbit control propulsion systems.
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图 9 氧化亚氮、乙烷、乙烯、丙烷和丙烯的饱和蒸汽压
Figure 9. Saturated vapor pressures of nitrous oxide, ethane, ethylene, propane and propylene
表 1 氧化亚氮发动机研究概况
Table 1. Research overview of nitrous oxide engines
年份 研究机构 推进剂组成 发动机推力/N 应用 2020 德国-航空航天中心[4] N2O/乙烷 1，22 2000～2010 法国-机电一体化研究中心[9] N2O/PE 1000 探空火箭 2020 新西兰-黎明宇航公司[5] N2O/丙烯 0.49～1.35，6.1～16.7 B1和B20推进器，卫星推进 2000～2010 美国-斯坦福大学[10] N2O/石蜡 “游隼”探空火箭 2010～2020 美国-桑迪亚国家实验室[11] N2O/乙醇 577 空间推进 2010～2020 美国-Firester公司[12] NOFBX 450 推进动力-火星单级入轨火箭 2000～2010 美国-阿拉巴马大学 N2O/丙烷 200 空间推进 2000～2010 美国-阿拉巴马大学[13] N2O/乙醇 1 卫星推进 2000～2010 美国-鲁坦及美国缩尺复合体公司[14] N2O/HTPB 73500 “太空船一号”载人亚轨道飞行器 2010～2020 美国-斯卡尔德复合材料公司和英国-维珍银河公司[15] N2O/HTPB 310000 “太空船二号”载人亚轨道飞行器 2020 美国-脉冲公司[16] N2O/乙烷 26 空间推进 2020 美国-脉冲公司[17] N2O/乙烷 800 空间推进 2010～2020 日本-宇宙航空研究开发机构JAXA[18] N2O/乙醇 700 高超声速飞行器火箭验证平台 2010～2020 日本-宇宙航空研究开发机构JAXA[19] N2O/乙醇 2000 上面级主发动机 2010～2020 日本-宇宙航空研究开发机构JAXA[19] N2O/乙醇 20 系统推进 2010～2020 英国-AEL公司[20] N2O/乙醇（预混） 600 2000～2010 英国-萨里大学[21] N2O 5.00×10−4 “UoSAT-12”卫星推进 2000～2010 中国-北京航空航天大学[22] N2O/HTPB 7000 “北航二号”探空火箭 2000～2010 中国-北京航空航天大学[23] N2O 1 卫星推进 2020～2023 中国-西北工业大学[24] N2O/煤油 500 轨控定推力发动机 2023～2025 中国-西北工业大学[25] N2O/煤油 80～400 轨控变推力发动机 2024 中国-北京交通大学[26] N2O/煤油 2025 中国-北京理工大学[27] N2O/乙烷 2009 中国-国防科学技术大学[28] N2O/乙醇 注：HTPB为端羟基聚丁二烯（hydroxyl-terminated polybutadiene）；PE为聚乙烯（polyethylene））。 
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表 2 氧化亚氮双组元推进剂及其他推进剂的理论计算性能
Table 2. Calculated theoretical performance for nitrous oxide bipropellant and others
推进剂组合 燃烧温度/K 余氧系数α 特征速度C*/(m·s−1) 燃气相对分子质量Mc/(kg·mol−1) 比冲Isp/(m·s−1) N2O/C2H5OH 3219.3 0.8 1560.5 25.65 2460.7 N2O/CH4 3229.6 0.7 1622.7 23.67 2550.5 N2O/C2H6 3302.7 0.7 1615.8 24.38 2538.4 N2O/C2H4 3400.1 0.6 1643.5 24.10 2573.4 N2O/C2H2 3585.2 0.4 1732.3 22.41 2685.3 N2O/C3H8 3320.9 0.7 1609.8 24.69 2528.5 N2O4/MMH 3384.3 0.6 1730.6 20.40 2725.7 LOX/LCH4 3405.9 0.7 1835.6 19.91 2918.3 LOX/JP-10 3631.0 0.7 1755.5 22.98 2777.4 LOX/LH2 2694.7 0.4 2417.1 8.95 3794.6 注：燃烧室压强约为7.09 MPa；喷管出口及环境压强均为 101325 Pa；计算结果为最佳比冲；模型采用冻结流。燃气按理想气体处理，燃烧为绝热过程，喷管膨胀为等熵流动膨胀。
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氧化剂 比冲
性能密度 密度
比冲化学
稳定性毒性 可存
储性自增压
能力气相
燃烧自燃性 易操
作性材料
成本化学
相容性性能调
节能力发动机稳定性/
燃烧效率综合安
全性O2 5 4 4 5 5 1 1 1 1 3 5 5 1 2 3 N2O 3 2 1 4 4 5 5 3 1 5 4 5 2 5 2 Nytrox 4 4 3 4 4 3 3 5 1 4 4 5 5 4 5 注：5为性能最佳, 1为性能最差。
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