SpaceX“超重-星舰”项目剖析：技术革新与中国航天的镜鉴

刘测产; 陈少将; 邹晨晨; 郭鸿宇; 钟文安

doi:10.13224/j.cnki.jasp.20250055

SpaceX“超重-星舰”项目剖析：技术革新与中国航天的镜鉴

doi: 10.13224/j.cnki.jasp.20250055

刘测产^{1, 2},
陈少将²,
邹晨晨²,
郭鸿宇²,
钟文安^2,*, ,

1.
中国人民解放军网络空间部队信息工程大学，郑州 450001
2.
西昌卫星发射中心，四川凉山彝族自治州 615000

详细信息

作者简介:
刘测产（1978-），男，高级工程师，硕士，专业研究方向为航天测试发射总体技术

通讯作者:
钟文安（1970-），男，正高级工程师，硕士，专业研究方向为航天测试发射总体技术。E-mail：33383992@qq.com

中图分类号: V417；V475
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出版历程
- 收稿日期: 2025-02-05
- 网络出版日期: 2026-07-03

Analysis of “Superheavy Starship” project: technological innovation and references for China’s aerospace

1.
People’s Liberation Army Information Engineering University，Zhengzhou 450001；China
2.
Xichang Satellite Launch Center，Liangshan Yi Autonomous Prefecture，Sichuan 615000，China

摘要

摘要:
聚焦美国SpaceX公司的“超重-星舰”项目，深入剖析其技术体系与发展进程。详细梳理了星舰首飞至第九飞的技术细节、试飞表现及改进路径，全面展示其在可重复使用、推进、结构材料、导航控制等多领域的创新成果，如塔架机械臂回收技术、猛禽发动机全流量分级燃烧循环等。同时探讨项目面临的技术难题与应对策略，精准展望其在商业航天、深空探测、军事应用等方面的广阔前景，研究表明中国航天在大推力发动机工程化、复用技术成熟度、商业航天闭环生态等方面仍存差距，需从技术攻坚、成本管控、产业培育、国际竞合及人才培育等维度精准施策，走自主创新与市场化协同的航天强国建设路径。
- SpaceX /
- 超重-星舰 /
- 综合飞行试验 /
- 可重复使用航天器 /
- 推进技术
Abstract:
This research focuses on the “Superheavy Starship” project of SpaceX in the United States, deeply analyzing its technological system and development process. The technical details, flight test performances and improvement paths from the first to the ninth flights of Starship are comprehensively sorted out, fully demonstrating its innovative achievements in multiple fields such as reusable technology, propulsion, structural materials, and navigation control, such as the launch tower robotic arm recovery technology and the full-flow staged combustion cycle of the Raptor engine. Meanwhile, the technical problems faced by the project and the corresponding coping strategies are discussed, accurately foreseeing its broad prospects in commercial aerospace, deep space exploration, military applications, etc. Targeted and constructive inspirations and suggestions are put forward from the dimensions of technological breakthroughs, cost management, business expansion, international cooperation and talent cultivation in combination with the current situation of China’s aerospace, so as to facilitate the development of China’s aerospace.
- SpaceX /
- superheavy-starship /
- integrated flight test /
- reusable spacecraft /
- propulsion technology

HTML

图 1 星舰组合体超重助推B9和星舰飞船S25试飞^[4]

Figure 1. Starship integrated flight test: super heavy B9 and starship S25^[4]

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图 2 星舰飞船表面铆接的隔热瓦^[8]

Figure 2. Thermal insulation tiles riveted to the surface of the starship^[8]

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图 3 星舰第五飞使用机械臂原位捕获回收超重助推（来源：SpaceX）

Figure 3. In-situ capture and recovery of the super heavy using a robotic arm during IFT-5 （source：SpaceX）

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图 4 猛禽发动机系统原理图^[5]

Figure 4. Raptor engine system schematic^[5]

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图 5 猛禽发动机实图^[15]

Figure 5. Actual pictures of raptor engine^[15]

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表 1 星舰与全球主流重型火箭的参数对比表

Table 1. Comparison of Parameters between Starship and Global Mainstream Heavy Rockets

参数	星舰（Starship）	太空发射系统（SLS Block 1）	猎鹰重型（Falcon Heavy）	新格伦（New Glenn）	火神（Vulcan Centaur）
高度与构型	121.3 m（两级可重复使用）	98m（两级，含固体助推器）	70 m（两级，芯级+ 2枚助推器）	98 m（两级）	约61.6 m（两级，标配高度高，选配固体助推器）
直径	9 m（全箭统一直径）	8.4 m（芯级）	3.7 m（芯级），总宽12.2 m（含助推器）	7 m（全箭统一直径）	5.4 m（芯级）
起飞质量	约5000 t	约2608 t（载人版）/ 约2951 t（货运版）	约1420 t	约1500 t	547～780 t （取决于助推器数量）
起飞推力	7590 t （33台猛禽发动机）	3980 t（4台RS-25 + 2枚固体助推器）	2280 t （27台梅林1D 发动机）	1750 t（7台BE-4 液氧甲烷发动机）	1560 t （6个助推器）
LEO 运载能力	150 t（可重复使用）/ 250 t（一次性）	95 t（载人版）/ 130 t（货运版）	63.8 t	45 t（一级复用）	27.2 t（VC6S构型，含6枚助推器）
GTO 运载能力	21 t（可重复使用）	27 t	约26.7 t	13.6 t（一级复用）	约14.4 t（VC6S构型，含6枚助推器）
推进剂类型	液氧/液态甲烷（LOX/CH₄）	液氢/液氧（LOX/LH₂）+ 固体推进剂	液氧/煤油（LOX/RP-1）	一级:液氧/液态甲烷（LOX/CH₄）；二级：液氧/液氢（LOX/LH₂）	液氧/甲烷（LOX/CH₄）+ 固体推进剂
发动机配置	一级：33×猛禽发动机；二级：3×猛禽发动机+3×猛禽发动机（真空版）	芯级: 4×RS-25 氢氧发动机；助推器:2×5段式固体火箭助推器（SRB）	芯级+2枚助推器各9台梅林1D发动机，共27台；二级: 1×梅林发动机真空版	一级: 7×BE-4液氧甲烷发动机；二级: 2×BE-3U液氢液氧发动机	一级: 2×BE-4液氧甲烷发动机；助推器: 0,2,4或6枚GEM 63XL固体助推器；二级: 2×RL10
可重复使用性	完全可重复使用（一级超重助推和二级星舰飞船均垂直着陆回收）	完全一次性	部分可重复使用（两个侧助推器和中心芯级可回收，整流罩可回收）	部分可重复使用（一级助推器设计复用25次，二级一次性）	完全一次性
发射成本（预估）	远期目标<1000万美元（完全复用）初期约9000万美元	约4.1亿美元（载人版）/ 3.5亿美元（货运版）	9000万美元（可复用）/ 1.5亿美元（一次性）	>7 000万美元	1.65亿美元（VC6S构型，一次性）

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