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Article(id=1286676617925727009, tenantId=1146029695717560320, journalId=1146119989267898375, issueId=1286676566465819629, articleNumber=null, orderNo=null, doi=10.7654/j.issn.2097-1974.20260311, pmid=null, cstr=null, oa=null, hot=null, price=null, onlineType=0, articleFormat=0, articleType=null, articleTypeStr=research-article, receivedDate=1751385600000, receivedDateStr=2025-07-02, revisedDate=1778601600000, revisedDateStr=2026-05-13, acceptedDate=null, acceptedDateStr=null, onlineDate=1784697211009, onlineDateStr=2026-07-22, pubDate=1782316800000, pubDateStr=2026-06-25, doiRegisterDate=null, doiRegisterDateStr=null, onlineIssueDate=1784697211009, onlineIssueDateStr=2026-07-22, onlineJustAcceptDate=null, onlineJustAcceptDateStr=null, onlineFirstDate=null, onlineFirstDateStr=null, sourceXml=null, magXml=null, createTime=1784697211009, creator=13041195026, updateTime=1784697211009, updator=13041195026, issue=Issue{id=1286676566465819629, tenantId=1146029695717560320, journalId=1146119989267898375, year='2026', volume='', issue='3', pageStart='1', pageEnd='106', issueExtLink='null', onlineDate='null', pubDate='1782316800000', pubDateStr='2026-06-25', beforeIssueId=null, nextIssueId=null, price=null, status=1, issueComplete=1, articleOrder=1, issueType=1, specialIssue=null, createTime=1784697198739, creator='13041195026', updateTime=1784702152269, updator='13041195026', preIssue=null, nextIssue=null, articleTotal=null, ext={EN=IssueExt(id=1286697343156204129, tenantId=1146029695717560320, journalId=1146119989267898375, issueId=1286676566465819629, language=EN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=), CN=IssueExt(id=1286697343156204130, tenantId=1146029695717560320, journalId=1146119989267898375, issueId=1286676566465819629, language=CN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=)}, issueFiles=null, downloadFileDto=null}, startPage=82, endPage=89, ext={EN=ArticleExt(id=1286676618122859298, articleId=1286676617925727009, tenantId=1146029695717560320, journalId=1146119989267898375, language=EN, title=Research and Prospect on Test-launch Mode of Liquid Launch Vehicle, columnId=1154067058611446771, journalTitle=Missiles and Space Vehicles, columnName=Launch Support, runingTitle=null, highlight=null, articleAbstract=

Liquid launch vehicles, as the primary means for human space access currently and in the foreseeable future, have their testing and launch modes closely tied to the technical status of the launch vehicle, the construction of launch site conditions, and the achievement of high-efficiency launch capability. Through a comprehensive analysis of the main characteristics and underlying reasons at each developmental stage of global liquid launch vehicle test-and-launch modes, the evolution of these modes is divided into three phases: reliability-and-safety-driven, test-efficiency-driven, and flexibility-and-cost-driven. In each phase, the test-and-launch mode of liquid rockets is refined and improved based on the previous stage, with current developments emphasizing safety, reliability, efficiency, and low cost simultaneously. The key factors influencing the selection of test-and-launch modes for liquid launch vehicles are analyzed, including technical feasibility and heritage, launch-site adaptability, test-and-launch efficiency and flexibility, and economic considerations. Major trends in the future development of test-and-launch modes are proposed, providing useful references for the construction of future space launch sites.

, authors=Wenan ZHONG, Junxin ZHANG, authorsList=Wenan ZHONG, Junxin ZHANG, authorCompany=null, correspAuthors=null, authorNote=null, correspAuthorsNote=null, copyrightStatement=null, copyrightOwner=null, extLink=null, articleAbsUrl=null, sourceXml=null, magXml=null, pdfUrl=null, pdf=null, pdfFileSize=null, pdfExtLink=null, richHtmlUrl=null, mobilePdfUrl=null, reviewReport=null, pdfFirstPage=null, abstractGraph=null, abstractGraphContent=null, abstractVideo=null, citation=null, cebUrl=null, magXmlContent=null, mapNumber=null, fund=null), CN=ArticleExt(id=1286676623176995635, articleId=1286676617925727009, tenantId=1146029695717560320, journalId=1146119989267898375, language=CN, title=液体运载火箭测试发射模式研究与展望, columnId=1154067058737275892, journalTitle=导弹与航天运载技术（中英文）, columnName=发射技术, runingTitle=null, highlight=null, articleAbstract=

液体运载火箭作为目前和未来一段时间内人类进入太空的主要运载工具，其测试发射模式的研究关系到运载火箭技术状态管控、发射场条件建设和高效发射能力的达成。通过全面分析全球液体运载火箭测发模式发展各个阶段的主要特征，将发展分为可靠性和安全性主导、测试效率主导、灵活性和成本主导3个阶段，每个阶段的测发模式均在上一个阶段的基础上迭代改进，当前测发模式的发展同时强调安全、可靠、高效、低成本。同时分析了液体运载火箭测发模式选择的主要因素，包括技术可行性和继承性、发射场适应性、测试发射效率和灵活性、经济性等，并提出了未来测发模式发展的主要趋势，为未来航天发射场的建设提供有益借鉴。

, authors=钟文安, 张俊新, authorsList=钟文安, 张俊新, authorCompany=null, correspAuthors=null, authorNote=

钟文安（1970—），男，正高级工程师，主要研究方向为航天测试发射总体技术。

张俊新（1985—），男，高级工程师，主要研究方向为航天测试发射电测总体、流程设计和发射场规划。

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钟文安（1970—），男，正高级工程师，主要研究方向为航天测试发射总体技术。

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钟文安（1970—），男，正高级工程师，主要研究方向为航天测试发射总体技术。

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张俊新（1985—），男，高级工程师，主要研究方向为航天测试发射电测总体、流程设计和发射场规划。

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张俊新（1985—），男，高级工程师，主要研究方向为航天测试发射电测总体、流程设计和发射场规划。

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Test launch process and status of liquid carrier rocket

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过程主要设施设备状态
进场运输车、火车、船、飞机水平
测试测试厂房水平或垂直
总装总装厂房水平或垂直
转运转运机构水平或垂直
加注发射发射工位及配套设施垂直
), ArticleFig(id=1286676627488740190, tenantId=1146029695717560320, journalId=1146119989267898375, articleId=1286676617925727009, language=CN, label=表1, caption=

液体运载火箭测试发射过程与状态

, figureFileSmall=null, figureFileBig=null, tableContent=
过程主要设施设备状态
进场运输车、火车、船、飞机水平
测试测试厂房水平或垂直
总装总装厂房水平或垂直
转运转运机构水平或垂直
加注发射发射工位及配套设施垂直
), ArticleFig(id=1286676627568431967, tenantId=1146029695717560320, journalId=1146119989267898375, articleId=1286676617925727009, language=EN, label=Tab.2, caption=

Main active liquid launch vehicle test and launch modes

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测发

模式

运载火箭
地区型号
三垂中国CZ-2F、CZ-5、CZ-5B、CZ-7、CZ-7A、CZ-8
美国SLS、星舰、火神、新格伦
日本H-3
印度PSLV、GSLV
三平中国CZ-6、朱雀2号、天龙2号
美国猎鹰9、猎鹰重型、安塔瑞斯、阿尔法、电子号、人族1号
欧洲阿里安6
俄罗斯安加拉、联盟号、质子号
一平两垂中国CZ-2系列、CZ-3系列、CZ-4系列、CZ-6A
), ArticleFig(id=1286676627673289568, tenantId=1146029695717560320, journalId=1146119989267898375, articleId=1286676617925727009, language=CN, label=表2, caption=

主要现役液体运载火箭测发模式

, figureFileSmall=null, figureFileBig=null, tableContent=

测发

模式

运载火箭
地区型号
三垂中国CZ-2F、CZ-5、CZ-5B、CZ-7、CZ-7A、CZ-8
美国SLS、星舰、火神、新格伦
日本H-3
印度PSLV、GSLV
三平中国CZ-6、朱雀2号、天龙2号
美国猎鹰9、猎鹰重型、安塔瑞斯、阿尔法、电子号、人族1号
欧洲阿里安6
俄罗斯安加拉、联盟号、质子号
一平两垂中国CZ-2系列、CZ-3系列、CZ-4系列、CZ-6A
), ArticleFig(id=1286676627761369953, tenantId=1146029695717560320, journalId=1146119989267898375, articleId=1286676617925727009, language=EN, label=Tab.3, caption=

Main active liquid launch vehicle test and launch modes

, figureFileSmall=null, figureFileBig=null, tableContent=
测发模式运载火箭
地区型号
三垂中国CZ-10系列
三平中国CZ-12、双曲线2号、力箭2号、引力2号、智神星1号
俄罗斯联盟5、叶尼塞、阿穆尔
), ArticleFig(id=1286676629413925730, tenantId=1146029695717560320, journalId=1146119989267898375, articleId=1286676617925727009, language=CN, label=表3, caption=

主要在研液体运载火箭测发模式

, figureFileSmall=null, figureFileBig=null, tableContent=
测发模式运载火箭
地区型号
三垂中国CZ-10系列
三平中国CZ-12、双曲线2号、力箭2号、引力2号、智神星1号
俄罗斯联盟5、叶尼塞、阿穆尔
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液体运载火箭测试发射模式研究与展望
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钟文安 , 张俊新
导弹与航天运载技术（中英文） | 发射技术 2026,(3): 82-89
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导弹与航天运载技术（中英文） |发射技术 2026 , (3) : 82 -89
液体运载火箭测试发射模式研究与展望
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钟文安, 张俊新
作者信息
  • 西昌卫星发射中心，海口，570203
作者简介:

钟文安（1970—），男，正高级工程师，主要研究方向为航天测试发射总体技术。

张俊新（1985—），男，高级工程师，主要研究方向为航天测试发射电测总体、流程设计和发射场规划。

Research and Prospect on Test-launch Mode of Liquid Launch Vehicle
Wenan ZHONG, Junxin ZHANG
Affiliations
  • Xichang Satellite Launch Center, Haikou, 570203
出版时间: 2026-06-25 doi: 10.7654/j.issn.2097-1974.20260311
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摘要
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液体运载火箭作为目前和未来一段时间内人类进入太空的主要运载工具，其测试发射模式的研究关系到运载火箭技术状态管控、发射场条件建设和高效发射能力的达成。通过全面分析全球液体运载火箭测发模式发展各个阶段的主要特征，将发展分为可靠性和安全性主导、测试效率主导、灵活性和成本主导3个阶段，每个阶段的测发模式均在上一个阶段的基础上迭代改进，当前测发模式的发展同时强调安全、可靠、高效、低成本。同时分析了液体运载火箭测发模式选择的主要因素，包括技术可行性和继承性、发射场适应性、测试发射效率和灵活性、经济性等，并提出了未来测发模式发展的主要趋势，为未来航天发射场的建设提供有益借鉴。

测试发射模式  /  液体运载火箭  /  航班化发射  /  航天发射场  /  “三垂”测发模式  /  “三平”测发模式

Liquid launch vehicles, as the primary means for human space access currently and in the foreseeable future, have their testing and launch modes closely tied to the technical status of the launch vehicle, the construction of launch site conditions, and the achievement of high-efficiency launch capability. Through a comprehensive analysis of the main characteristics and underlying reasons at each developmental stage of global liquid launch vehicle test-and-launch modes, the evolution of these modes is divided into three phases: reliability-and-safety-driven, test-efficiency-driven, and flexibility-and-cost-driven. In each phase, the test-and-launch mode of liquid rockets is refined and improved based on the previous stage, with current developments emphasizing safety, reliability, efficiency, and low cost simultaneously. The key factors influencing the selection of test-and-launch modes for liquid launch vehicles are analyzed, including technical feasibility and heritage, launch-site adaptability, test-and-launch efficiency and flexibility, and economic considerations. Major trends in the future development of test-and-launch modes are proposed, providing useful references for the construction of future space launch sites.

test-launch mode  /  liquid launch vehicle  /  airline-flight-mode  /  launch site  /  three-vertical mode  /  three-horizontal mode
钟文安, 张俊新. 液体运载火箭测试发射模式研究与展望. 导弹与航天运载技术（中英文）, 2026 , (3) : 82 -89 . DOI: 10.7654/j.issn.2097-1974.20260311
Wenan ZHONG, Junxin ZHANG. Research and Prospect on Test-launch Mode of Liquid Launch Vehicle[J]. Missiles and Space Vehicles, 2026 , (3) : 82 -89 . DOI: 10.7654/j.issn.2097-1974.20260311
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0 引 言
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当前，各航天大国均采用液体运载火箭作为主要在役运载工具，将有效载荷送入太空。液体运载火箭测试发射模式（以下简称测发模式）指火箭在发射场执行测试发射任务过程中的主要技术状态。测发模式的设计受火箭技术状态、发射场布局和测试流程的制约，是航天发展领域重要的工程问题［1-3］。
随着世界各国航天任务需求的迅猛增长，航天产业进入了发展高峰期。美国、日本、欧洲等国家和地区运载火箭型号加速迭代，德尔塔4、宇宙神5、阿里安5、H-2等系列运载火箭陆续退役，火神、阿里安6、H-3等新研运载火箭逐步投入使用。特别是美国的SpaceX、蓝色起源、火箭实验室，以及中国蓝箭航天空间科技股份有限公司、星河动力（北京）空间科技有限公司、北京星际荣耀空间科技有限公司等多家商业航天公司的多型运载火箭完成研发投产，推动火箭的测试发射技术快速迭代，航班化发射成为未来运载火箭发射技术的必然趋势［4］。
1 测试发射模式概念与研究现状
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当前技术条件下，通常液体运载火箭均以分段水平状态运输进入航天发射场，以整体垂直状态在发射工位上加注发射，因此测发模式主要描述除进场和发射外，运载火箭在测试过程中需关注的总装（组装）、测试和转运的技术状态，如表1所示。
中国相关研究主要包括：文献［3］从技术继承性、测试发射状态改变程度、发射准备时间、组装测试环境、对有效载荷和箭体结构的要求、快速发射能力、爆炸后发射工位的损失及恢复和环境适应性等维度，比较了“一平两垂”和“三垂”测发模式；文献［5］针对中国小行星探测任务，基于社会准则、经济准则和技术准则，采用决策模型对“一平两垂”和“三垂”模式的优缺点进行分析；文献［6］比较了“三垂”“两平两垂”和“三平”测发模式对发射支持系统设备的不同需求；文献［7］从技术难度与建设投入角度比较了“三垂”和“三平”模式；文献［8］从经济性、复杂性、发射工位利用效率、测试环境、测试状态、技术难度和后续发射任务适应性等角度，对比了“一平两垂”“三垂”和“三平”测发模式；文献［9］从技术状态适应性、建造费用、建设周期、维护成本等角度对“三平”和“三垂”模式进行了对比。
总体而言，测发模式与运载火箭和航天器的技术状态、航天发射场建设布局和自然条件，以及工程总体要求等要素密切相关。以上分析针对中国不同时期不同航天工程的需要，在运载火箭研制和发射场建设论证的过程中发挥了重要作用，但缺乏对测发模式发展演进过程的分析。当前，中国运载火箭型谱扩充，航天发射场拓建加速，科学认识测发模式演进趋势，对有效指导中国未来航天发射场建设具有重要意义。
2 测发模式演进的主导因素分析
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在不同的发展阶段，各国测发模式选择的主导因素不尽相同，呈现出明显的阶段特点。
2.1 可靠性安全性主导早期测发模式设计
全球范围内，液体运载火箭测发模式的研究和工程实践起源于美苏两国，早期液体运载火箭多由洲际弹道导弹改装。受当时技术手段和航天发射质量管理水平的影响，早期运载火箭发射成功率低。20世纪50年代，全球运载火箭发射成功率仅有41.67%，如图1所示。
因此，可靠性和安全性是这一时期测发模式设计的首要考虑因素。按照测试覆盖性要求，火箭多采用“两平两垂”测发模式，在技术区和发射区均进行测试，发射区采用固定式发射平台和近距离测发控技术，部分项目甚至多次重复测试。
2.2 测试效率主导多种测发模式创新
美苏冷战时期，全球航天发射次数进入了第一个高峰期：1964年年发射次数达到100次，此后直到1990年，全球年均发射次数均保持在100次以上。同时，随着航天测试发射领域初期大量工程实践经验的积累，运载火箭可靠性和安全性不断提高，20世纪60年代，全球运载火箭发射成功率提升至82.4%，此后逐步稳定在93%左右。为了进一步有效支撑更大规模的航天工程建设和冷战时期的高密度发射任务，“两平两垂”测发模式周期较长的弊端显现，测发效率提升成为测发模式设计的主要考虑因素。
20世纪60年代初，美国首先取消了技术区水平状态下全流局的测试，仅在技术区停放进行外观检查，之后水平转运，在发射台完成垂直总装，垂直测试后加注发射，称为“一平两垂”模式。中国的CZ-3等火箭同样将技术区测试项目进行了精简，由“两平两垂”模式演进为“一平两垂”模式。运载火箭进场后，直接转运至发射区垂直总装，之后运载火箭始终保持在发射平台上，技术状态基本不变，完成测试和加注发射工位，因此这种模式也被称为“三固”测发模式。
“两平两垂”“一平两垂”等测发模式火箭在发射工位上占位时间较长，不利于任务高效周转，且火箭在发射区环境保障难度大，难以做到与技术区测试厂房中同等保障条件，因此发展发射区占位时间较短的“三垂”和“三平”测发模式成为必然。
20世纪60年代初，美国将部分型号的水平测试取消，发展出“三垂”测发模式。该模式下，运载火箭垂直总装后箭地连接状态保持不变，美国的土星5号、航天飞机、宇宙神5、SLS、星舰，欧洲的阿里安5，日本的H-2A系列，中国的CZ-5、CZ-7、CZ-2F等运载火箭均采用这一模式［10-15］。早期也将这一测发模式称为“垂直上架方案”。
美国土星5号运载火箭，垂直转运至发射区后，需要在垂直状态下测试约40~50天后才加注发射，即相当于增加了发射区的垂直状态下测试，这种测发模式或可称为“四垂”模式，如图2所示。
由于俄罗斯的航天发射场居于内陆，采用铁路直通发射场区的建设方式，因此，俄罗斯发展了依托铁路的“三平”测发模式，如图3所示。俄罗斯的联盟号系列、质子号系列、能源号、N-1、天顶号、旋风号、安加拉等火箭均沿用这一测发模式［16-17］。美国德尔塔4火箭在卡纳维拉尔角发射场也采用“三平”测发模式。
2.3 灵活性和低成本主导的商业化测发模式
近年来，随着民营企业进入航天领域，控制工程投入规模和提高任务适应性成为测发模式选择的主要考虑因素。美国和中国的多家商业航天公司运载火箭多采用进一步优化的“三平”测发模式，运载火箭水平转运至发射区后直接起竖、加注、发射，发射区占位时间缩短至数小时［18］。
在“三垂”测发模式方面，各国的技术路线倾向于缩短发射区占位时间，从而提高滨海发射场发射的适应性以及多任务并行的灵活性。近期主要火箭测发模式如表2所示。
3 测试发射模式比较与选择
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3.1 技术可行性与继承性
技术可行性与继承性，是指系统考虑运载火箭、航天器和发射场的技术状态，并根据当前的技术积累选择测发模式。
a）火箭构型设计。一般而言，运载火箭单芯级结构或“一字捆绑”结构（如图4所示）更适合采用“三平”测发模式，如美国SpaceX的猎鹰系列、安塔瑞斯、阿尔法，中国CZ-6、朱雀2号、双曲线2号、天龙2号等火箭［19］。
b）火箭和卫星结构强度设计。俄罗斯的多向捆绑火箭如联盟号、质子号和暴风雪号等，从箭体结构角度考虑并不适合整体水平转运，但其仍沿用“三平”测发模式，为满足该模式的水平整体转运和起竖需要，对箭体结构相关部位进行了加强。相应的，箭体结构的加强使得火箭结构效率和有效载荷质量比有所损失。为适应“三平”测发模式，其能源号火箭设计了复杂的整体水平转运装置，如图5所示。
美国的德尔塔4火箭，其火箭箭体结构为3个通用芯级捆绑构型，适合采用“三平”测发模式，但由于航天器不满足水平总装的技术状态要求，因此卫星合罩后垂直状态运输至发射区，与火箭垂直对接后加注发射，这种模式被称为“不完全的三平模式”。相比“完全的三平模式”，这种模式要求发射区建设相关的吊装设施，以完成星箭对接工作［20］，如图6所示。
中国的CZ-2F火箭采用“三垂”模式，火箭对于垂直运输方式引起的低频震动开展了技术攻关和试验验证［21］。垂直总装可减少箭体应力变形，提升对接精度［22］。
c）运载火箭和航天器的主要技术状态。苏联的火箭早期即采用捷联惯组，因此可采用“三平”模式；美国、日本和欧洲等国家和地区的运载火箭则采用惯性平台装置，为避免平台倾倒，更适合采用“三垂”模式，或在发射区火箭垂直总装后再安装惯性平台装置［23］。
d）发射场重要设施技术状态。“三平”模式需要研发大规模复杂的机械结构装置用于箭体整体起竖；“三垂”模式则需研发大规模驼重能力大的垂直转运装置，如图7所示。阿波罗任务时期，NASA引进美国矿业领域使用的履带转运装置，有效载荷超过4 000 t，行驶平稳，并具有一定的爬坡能力，以满足土星5号垂直转运的需求；中国则在突破了2 000 t级活动发射平台机电气液多系统集成技术后，才得以采用“新三垂”模式执行CZ-5等火箭的发射任务［24］。
3.2 发射场适应性
运载火箭的测试发射要适应发射场的气候环境、布局和主要设备设施的技术条件，这是运载火箭环境适应性、使用维护性的具体要求，也是未来一体化测试发射理念的要求。
a）地理区位与气候条件。
发射场选址是多因素综合的系统工程问题，滨海布局发射场，是发射场建设的重要趋势［25-26］：对于滨海发射场，考虑到台风、飓风等恶劣天气影响，火箭在滨海发射场测试发射时，通常要求在发射区的占位时间短，因此较为适合采用“三平”或“三垂”模式。“三垂”模式的运载火箭在垂直转运过程中，箭体完全暴露在环境中，需要开展防风减载机构设计；“三平”模式的运载火箭尽量减少发射区设备设施的规模，其起竖臂设计时需满足发射区起竖时运载火箭地面风载要求。
b）发射场布局与道路条件。
采用“三平”测发模式，发射场道路需满足火箭水平运输转弯半径需求。俄罗斯的发射场建设技术区和发射区由铁路联通，方便箭体水平转运。采用“三垂”测发模式，发射场道路建设需尽量平直，减小坡度，如中国文昌航天发射场、日本吉信发射场等。
3.3 测试发射效率和灵活性
随着航天发射需求的不断增多，国内外对航天测试发射的效率提升日益关注，美国猎鹰系列火箭、中国的CZ-6以及其他多家商业公司火箭，均将优化和缩短测试发射流程作为火箭研制的重要指标。
理论上，技术状态改变次数较少的“三垂”“三平”和“三固”等测发模式测试发射所需的时间短，但在实际工程实践中，各种测试发射模式所需的时间还受火箭技术状态、测试项目设置和发射场设备设施能力等条件影响。同时，随着运载火箭投入使用的时间增长，流程也将不断优化，难以简单用测试发射模式进行比较。如美国的德尔塔4（三平）、欧洲的阿里安5（三垂）、日本的H-2A（三垂）、俄罗斯的质子号（三平）和中国的CZ-3A（一平两垂）测试发射周期分别为22~24天、24天、15天、25~30天和19天［27］，如图8所示。
3.4 经济性
运载火箭测试发射模式的选择必须注重成本控制才能有效支撑航天发射场高效可持续运营。当前，从运载火箭和发射场设计，到测试发射过程的成本控制，已经成为航天领域的热点问题［28］。
a）发射场建设的成本。
“三垂”模式所需的大规模箭体垂直总装测试厂房和具有大质量驼重的垂直转运装置建设成本高，肯尼迪航天中心的垂直转运车单台耗资2亿多美元，超过了当时论证CZ-2F火箭整个发射场的经费规模。因此，对于中小型运载火箭，采用“三平”模式从而避免建设垂直总装测试厂房，可以有效降低发射场的建设成本。但对于重型运载火箭，特别是多向捆绑的大尺寸运载火箭，即使是水平总装测试厂房，其建设规模仍较为庞大。
b）测试发射和运营的成本。
大规模的固定设施与转运装置，在测试发射过程中将出现折损，特别是火箭的发射平台、发射架等，应按需开展维修，将产生运营维护的费用。
同时，还应考虑小概率情况下发射工位上运载火箭爆炸对发射场的影响。如2016年在美国猎鹰9火箭静态点火试验过程中发生爆炸，对工位及靠近工位的设备设施造成了不同程度的损伤。
3.5 测发模式比较小结
综上，液体运载火箭的测试发射模式经历了从分级向整体的转变，技术状态变化更少，整体测试和转运的“三平”和“三垂”测发模式成为发展趋势［29］。总体而言，对于中小型液体运载火箭，尽量简化箭体结构构型，采用单芯级或通用芯级捆绑构型，采用“三平”测发模式，是当前发展的最优方案。对于大型、重型运载火箭，或捆绑固体助推、多向捆绑的液体运载火箭，则较为适合发展“三垂”测发模式。
在研在试的主要运载火箭测发模式如表3所示。
4 液体运载火箭测发模式发展趋势与关键技术
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4.1 快速复用
随着人类探索、开发与利用太空的活动不断增多，提高发射效率的必要性日益增强，航班化发射已经成为航天发射场建设发展的必然趋势［30-32］。航班化发射是指发射场能够以稳定的班次发射运载火箭，持续为航天器、人员进入太空提供服务。
可重复使用技术将航天发射的流程由进场、总装、测试、转运、发射，拓展至回收、维护与再次发射，模式形成闭环，更加强调效率和成本，高效性成为未来测发模式设计需要重点考虑的因素。以快速回收复用为基础的“一小时全球到达”的跨域运送模式，必须配合发射场的关键设备设计建设。在快速全球到达的时间链中，运载火箭的加注发射时间占比较大，因此除火箭的复用技术外，必须加强大流量并行快速加注，以及自动化测试发射技术的攻关研究。
4.2 测发解耦
当前的运载火箭测试发射过程中，发射场技术区和发射区工作仍有部分耦合，进行技术区测试工作时，有时需要发射区的设备设施配合完成。在多任务并行时，这种模式不利于工作灵活开展，制约任务的优化统筹。
通过测发解耦，采用测、发分离的工作模式，可以将发射工位从繁杂、冗长的测试准备工作中完全解放出来，仅用于执行加注发射阶段的关键操作，实现多火箭在“候车室”并行测试准备，多“站台”等待发射。技术区功能集成，发射区灵活适应，大幅提高了发射场的综合发射能力。
在测发解耦的模式下，发射场不必过于强调单枚火箭的专属测发模式，而是重在统筹调度多枚火箭的灵活周转，特别是发射工位的灵活运用，要求发射工位能够模块化灵活适配多型运载火箭，同时在高效周转中简单维护甚至免维护。
4.3 前店后厂
随着航天工程规模的扩大和发射任务密度的提高，测试产业链一体化的理念逐步成为航天领域发展的趋势，围绕发射场形成一体化的产业链，以提高整体效率。因此，测发模式也将适应性转变。
采用“前店后厂”的模式较为符合航班化发射对于生产、测试、发射、回收、维护流程快速闭环的需求。“前店”，包括现有典型航天发射场的测试厂房、发射工位及配套的加注供气设备设施等，以及回收场坪、配套港口等；“后厂”，包括火箭的部段生产，及后端测试发射控制中心。此模式下，运载火箭可在进场前完成大多数分系统测试，模糊工厂和发射场的界线，提高整体效率，降低链路成本。
“前店后厂”模式有利于产业聚集，可以同国际化多方交流的航天城规划相融合，经由航天测试发射的核心功能，向产业配套、文化旅游等方向辐射发展。
4.4 简化测发操作
为简化液体运载火箭测发模式，需尽量避免在技术区和发射区的重复测试和操作。应在运载火箭设计和发射场建设的过程中就强调“测试发射一体化”设计理念，确保火箭在发射场具有良好的操作可达性，项目安排合理，从而达到优化测试发射流程的目的。
随着智慧化运载火箭理念的提出和技术攻关，火箭在发射场的相关测试操作将大幅简化，测试发射人力资源得到高效配置。火箭并行测试发射、自动化操作处置和智能化数据分析评估技术的应用，将进一步提升发射场的测试发射效率。
4.5 发射区智能无人化
测发技术经历了从近控到远控的发展过程，当前无人值守已成为确保测试安全性，进一步优化运载火箭在发射区加注发射操作的重要技术发展趋势。美国猎鹰系列、SLS、火神火箭等均已实现了射前无人值守，发射区人工操作大幅减少。中国CZ-5大型低温液体运载火箭的测发控系统已经实现了射前6 h无人值守［33］。
在具体的执行层面，需持续开展自动对接、箭体周边态势感知与应急处置等关键技术攻关。无人值守可减少发射区占位时间，减少运载火箭和航天器在发射区的有人操作数量，但也可能对测试覆盖率和发射可靠性造成影响，必须科学评估并采取相应的技术手段。
发射区智能无人化技术可大幅提升测试发射的安全性，提高发射工位的周转效率，但需严密论证测试操作的可达性和异常处置方案的可行性，确保在紧急情况下有应对之策。
5 结束语
收起
液体运载火箭的测发模式发展多年，经历了从近距离测试到远控测试，从分部段测试到整体测试的转变。测发模式的主导因素由安全、可靠、准时，向着在安全、可靠和准时的基础上，兼顾发射效率、灵活适应性和经济性等多种因素的综合发展。
面向未来航班化、多种窗口和多种航天器载荷的发射需求，围绕快速复用技术的应用，测发模式的内涵向回收复用方向延展，发射场建设测发解耦、灵活匹配、班次发射的理念成为趋势，以功能更加综合、集成、完善的太空港满足人类高效、经济、大规模进入太空的需要。

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doi: 10.7654/j.issn.2097-1974.20260311
  • 接收时间：2025-07-02
  • 首发时间：2026-07-22
  • 出版时间：2026-06-25
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  • 收稿日期：2025-07-02
  • 修回日期：2026-05-13
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