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Article(id=1244288473721586488, tenantId=1146029695717560320, journalId=1243969219109367850, issueId=1244288473163744056, articleNumber=null, orderNo=null, doi=10.20118/j.issn2097-258X.2025.05.008, pmid=null, cstr=null, oa=null, hot=null, price=null, onlineType=0, articleFormat=0, articleType=null, articleTypeStr=null, receivedDate=1745078400000, receivedDateStr=2025-04-20, revisedDate=1748534400000, revisedDateStr=2025-05-30, acceptedDate=null, acceptedDateStr=null, onlineDate=1774591089897, onlineDateStr=2026-03-27, pubDate=1757433600000, pubDateStr=2025-09-10, doiRegisterDate=null, doiRegisterDateStr=null, onlineIssueDate=1774591089897, onlineIssueDateStr=2026-03-27, onlineJustAcceptDate=null, onlineJustAcceptDateStr=null, onlineFirstDate=null, onlineFirstDateStr=null, sourceXml=null, magXml=null, createTime=1774591089897, creator=13701087609, updateTime=1774591089897, updator=13701087609, issue=Issue{id=1244288473163744056, tenantId=1146029695717560320, journalId=1243969219109367850, year='2025', volume='3', issue='5', pageStart='1', pageEnd='94', issueExtLink='null', onlineDate='null', pubDate='null', beforeIssueId=null, nextIssueId=null, price=null, status=1, issueComplete=1, articleOrder=1, issueType=1, specialIssue=null, createTime=1774591089764, creator=13701087609, updateTime=1774591299427, updator=13701087609, preIssue=null, nextIssue=null, ext={EN=IssueExt(id=1244289352621212610, tenantId=1146029695717560320, journalId=1243969219109367850, issueId=1244288473163744056, language=EN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=), CN=IssueExt(id=1244289352621212611, tenantId=1146029695717560320, journalId=1243969219109367850, issueId=1244288473163744056, language=CN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=)}, issueFiles=null}, startPage=88, endPage=94, ext={EN=ArticleExt(id=1244288474107462459, articleId=1244288473721586488, tenantId=1146029695717560320, journalId=1243969219109367850, language=EN, title=Research on the Technology of New Internal Air Bridge Balance, columnId=1244288474023576378, journalTitle=Aerodynamic Research & Experiment, columnName=Research, runingTitle=null, highlight=null, articleAbstract=

A large-scale low-speed wind tunnel turbofan aircraft dynamic simulation test system is established to accurately obtain the dynamic influence of turbofan engine intake and exhaust on the aircraft, providing technical support for the refined development of military and civil turbofan aircraft in China. The technology of internal air bridge balance is one of the core technologies in the test system. The turbine powered simulator (TPS) needs to be driven by high-pressure gas. The stiffness of the high-pressure gas supply pipeline and the high-pressure gas flowing through the fixed end to the measuring end of the balance will bring great measurement interference to the balance, and then affect the force measurement accuracy of wind tunnel test. It is necessary to weaken the rigidity of the high-pressure air supply pipeline and eliminate the interference of air supply. Eliminating or weakening the interference load caused by the air supply pipeline and high-pressure air supply flowing through the pipeline on the balance force measurement is a necessary prerequisite to ensure that high-precision test data can be obtained. In this study, a new type of air bridge disturbance elimination unit structure is proposed. The technical research on the design mechanism and calibration correction of the influence of air bridge stiffness,air supply pressure, air supply temperature and air supply flow on the force measurement interference of the balance is carried out. The final test results show that the corresponding technical indicators of the internal air bridge balance meet the expectations and can meet the needs of turbofan aircraft dynamic simulation wind tunnel test.

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建立大型低速风洞涡扇飞机动力模拟试验系统，准确获得涡扇发动机进排气对飞机的动力影响量，为我国军用和民用涡扇飞机的精细化研制提供技术支撑。内式空气桥天平技术是该项试验系统中的核心技术之一，涡轮动力模拟器（TPS）需要由高压气驱动运转，高压供气管路的自身管路刚度以及高压气体流经天平的固定端至测量端时，会给天平带来较大的测量干扰，对风洞试验的测力精度造成影响，需要对高压供气管路进行刚度减弱、供气消扰处理。消除或减弱供气管路及高压供气流经管路时给天平测力带来的干扰载荷，是确保获得高精度试验数据的必要前提。本文提出了一种新型空气桥消扰单元结构，围绕空气桥自身刚度、供气压力、供气温度、供气流量对天平的测力干扰影响进行了设计机理与校准修正的技术研究。试验结果表明，内式空气桥天平相应的技术指标符合预期，能够满足涡扇飞机动力模拟风洞试验需求。

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(in Chinese), articleTitle=Fatigue life analysis and test verification of flexible joint of air bridge, refAbstract=null), Reference(id=1244288492558205184, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, doi=null, pmid=null, pmcid=null, year=2021, volume=36, issue=6, pageStart=1137, pageEnd=1144, url=null, language=null, rfNumber=[11], rfOrder=19, authorNames=胡卜元, 巫朝君, 吴福章, journalName=航空动力学报, refType=null, unstructuredReference=胡卜元, 巫朝君, 吴福章, 等.基于校准箱的低速风洞一体式喷流试验技术[J].航空动力学报, 2021, 36(6): 1137-1144., articleTitle=基于校准箱的低速风洞一体式喷流试验技术, refAbstract=null), Reference(id=1244288492667257091, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, doi=null, pmid=null, pmcid=null, year=2021, volume=36, issue=6, pageStart=1137, pageEnd=1144, url=null, language=null, rfNumber=[11], rfOrder=20, authorNames=Hu Buyuan, Wu Chaojun, Wu Fuzhang, journalName=Journal of Aerodynamics, refType=null, unstructuredReference=Hu Buyuan, Wu Chaojun, Wu Fuzhang, et al. 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Journal of Aerodynamics, 2021,36(6):1137-1144.(in Chinese), articleTitle=Integrated jet test technology of low speed wind tunnel based on calibration chamber, refAbstract=null)], funds=null, companyList=[AuthorCompany(id=1244288479253873535, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, xref=1., ext=[AuthorCompanyExt(id=1244288479262262144, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, companyId=1244288479253873535, language=EN, country=null, province=null, city=null, postcode=null, companyName=null, departmentName=null, remark=1.AVIC Aerodynamic Research Institute，Harbin 150001，China), AuthorCompanyExt(id=1244288479274845057, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, companyId=1244288479253873535, language=CN, country=null, province=null, city=null, postcode=null, companyName=null, departmentName=null, remark=1.中国航空工业空气动力研究院, 黑龙江　哈尔滨　150001)]), 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flow, figureFileSmall=greOenahn6w49oSydm8Olg==, figureFileBig=/Kfi6I0milouWrfltIo/kA==, tableContent=null), ArticleFig(id=1244288488032551072, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, language=CN, label=图13, caption=干扰量随流量变化规律, figureFileSmall=greOenahn6w49oSydm8Olg==, figureFileBig=/Kfi6I0milouWrfltIo/kA==, tableContent=null), ArticleFig(id=1244288488158380194, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, language=EN, label=Table 1, caption=

Strain of each element and measurement signal output

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单元 Y Mz Mx My X Z
应变4.1×10-45×10-42.0×10-46.0×10-44.5×10-41.9×10-4
信号/μV8.2×10310×1034.0×10312.0×1039.0×1033.8×103
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各元应变及测量信号输出

, figureFileSmall=null, figureFileBig=null, tableContent=
单元 Y Mz Mx My X Z
应变4.1×10-45×10-42.0×10-46.0×10-44.5×10-41.9×10-4
信号/μV8.2×10310×1034.0×10312.0×1039.0×1033.8×103
), ArticleFig(id=1244288489798353064, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, language=EN, label=Table 2, caption=

Combined modal analysis results

, figureFileSmall=null, figureFileBig=null, tableContent=
阶数12345
频率/Hz184.65211.93832.081 038.501 148.30
阶数678910
频率/Hz1 463.402 012.502 020.102 118.302 124.00
), ArticleFig(id=1244288489869656234, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, language=CN, label=表2, caption=

组合模态分析结果

, figureFileSmall=null, figureFileBig=null, tableContent=
阶数12345
频率/Hz184.65211.93832.081 038.501 148.30
阶数678910
频率/Hz1 463.402 012.502 020.102 118.302 124.00
), ArticleFig(id=1244288489949348016, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, language=EN, label=Table 3, caption=

Calibration accuracy of balance without air bridge

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单元 X Y Z Mx My Mz
精度/（%F.S）0.070.030.100.160.070.06
准度/（%F.S）0.090.040.110.170.060.05
), ArticleFig(id=1244288490083565748, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, language=CN, label=表3, caption=

不带空气桥的天平校准精/准度

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单元 X Y Z Mx My Mz
精度/（%F.S）0.070.030.100.160.070.06
准度/（%F.S）0.090.040.110.170.060.05
), ArticleFig(id=1244288490196811960, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, language=EN, label=Table 4, caption=

Calibration accuracy of balance combination with air bridge

, figureFileSmall=null, figureFileBig=null, tableContent=
单元 X Y Z Mx My Mz
精度/（%F.S）0.0910.070.090.0860.080.08
准度/（%F.S）0.0540.040.280.1710.160.05
), ArticleFig(id=1244288490280698044, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, language=CN, label=表4, caption=

带空气桥的天平组合校准精/准度

, figureFileSmall=null, figureFileBig=null, tableContent=
单元 X Y Z Mx My Mz
精度/（%F.S）0.0910.070.090.0860.080.08
准度/（%F.S）0.0540.040.280.1710.160.05
), ArticleFig(id=1244288490385555646, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, language=EN, label=Table 5, caption=

Balance under 0.1~8.3 MPa pipeline air supply pressure zero point change

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单元 X Y Z Mx My Mz
0.1 MPa-1595596231844.22318.7-95
8.3 MPa-1594596231644.92316.3-95
), ArticleFig(id=1244288490465247426, tenantId=1146029695717560320, journalId=1243969219109367850, articleId=1244288473721586488, language=CN, label=表5, caption=

管路供气压力下的天平各元零点变化(0.1~8.3 MPa)

, figureFileSmall=null, figureFileBig=null, tableContent=
单元 X Y Z Mx My Mz
0.1 MPa-1595596231844.22318.7-95
8.3 MPa-1594596231644.92316.3-95
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新型内式空气桥天平技术研究
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徐越 1, 2 , 魏学敏 1, 2 , 陈景伟 1, 2 , 李聪 1, 2 , 靳永峰 1, 2 , 徐铁军 1, 2
气动研究与试验 | 研究 2025,3(5): 88-94
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气动研究与试验 | 研究 2025, 3(5): 88-94
新型内式空气桥天平技术研究
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徐越1, 2, 魏学敏1, 2, 陈景伟1, 2, 李聪1, 2, 靳永峰1, 2, 徐铁军1, 2
作者信息
  • 1.中国航空工业空气动力研究院, 黑龙江　哈尔滨　150001
  • 2.低速高雷诺数气动力航空科技重点实验室　黑龙江　哈尔滨　150001
Research on the Technology of New Internal Air Bridge Balance
Yue Xu1, 2, Xuemin Wei1, 2, Jingwei Chen1, 2, Cong Li1, 2, Yongfeng Jin1, 2, Tiejun Xu1, 2
Affiliations
  • 1.AVIC Aerodynamic Research Institute，Harbin 150001，China
  • 2.Aviation Key Laboratory of Aerodynamics for Low Speed & High Reynolds Number，Harbin 150001，China
出版时间: 2025-09-10 doi: 10.20118/j.issn2097-258X.2025.05.008
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摘要
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建立大型低速风洞涡扇飞机动力模拟试验系统，准确获得涡扇发动机进排气对飞机的动力影响量，为我国军用和民用涡扇飞机的精细化研制提供技术支撑。内式空气桥天平技术是该项试验系统中的核心技术之一，涡轮动力模拟器（TPS）需要由高压气驱动运转，高压供气管路的自身管路刚度以及高压气体流经天平的固定端至测量端时，会给天平带来较大的测量干扰，对风洞试验的测力精度造成影响，需要对高压供气管路进行刚度减弱、供气消扰处理。消除或减弱供气管路及高压供气流经管路时给天平测力带来的干扰载荷，是确保获得高精度试验数据的必要前提。本文提出了一种新型空气桥消扰单元结构，围绕空气桥自身刚度、供气压力、供气温度、供气流量对天平的测力干扰影响进行了设计机理与校准修正的技术研究。试验结果表明，内式空气桥天平相应的技术指标符合预期，能够满足涡扇飞机动力模拟风洞试验需求。

风洞天平  /  空气桥  /  消扰单元  /  有限元计算  /  应变梁

A large-scale low-speed wind tunnel turbofan aircraft dynamic simulation test system is established to accurately obtain the dynamic influence of turbofan engine intake and exhaust on the aircraft, providing technical support for the refined development of military and civil turbofan aircraft in China. The technology of internal air bridge balance is one of the core technologies in the test system. The turbine powered simulator (TPS) needs to be driven by high-pressure gas. The stiffness of the high-pressure gas supply pipeline and the high-pressure gas flowing through the fixed end to the measuring end of the balance will bring great measurement interference to the balance, and then affect the force measurement accuracy of wind tunnel test. It is necessary to weaken the rigidity of the high-pressure air supply pipeline and eliminate the interference of air supply. Eliminating or weakening the interference load caused by the air supply pipeline and high-pressure air supply flowing through the pipeline on the balance force measurement is a necessary prerequisite to ensure that high-precision test data can be obtained. In this study, a new type of air bridge disturbance elimination unit structure is proposed. The technical research on the design mechanism and calibration correction of the influence of air bridge stiffness,air supply pressure, air supply temperature and air supply flow on the force measurement interference of the balance is carried out. The final test results show that the corresponding technical indicators of the internal air bridge balance meet the expectations and can meet the needs of turbofan aircraft dynamic simulation wind tunnel test.

wind tunnel strain gage balance  /  air bridge  /  decoupling unit  /  finite element calculation  /  strain beam
徐越, 魏学敏, 陈景伟, 李聪, 靳永峰, 徐铁军. 新型内式空气桥天平技术研究. 气动研究与试验, 2025 , 3 (5) : 88 -94 . DOI: 10.20118/j.issn2097-258X.2025.05.008
Yue Xu, Xuemin Wei, Jingwei Chen, Cong Li, Yongfeng Jin, Tiejun Xu. Research on the Technology of New Internal Air Bridge Balance[J]. Aerodynamic Research & Experiment, 2025 , 3 (5) : 88 -94 . DOI: 10.20118/j.issn2097-258X.2025.05.008
正文
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飞行器早已进入了喷气时代，为了减小动力系统对飞行器空气动力特性的影响，在飞行器研制中将动力装置和机体进行一体化设计，这种方法成为决定飞行器气动设计成功与否的关键因素之一。开展动力装置-飞机一体化设计的主要验证手段就是进行风洞试验。随着发动机技术的发展，其影响作用也越来越大，动力模拟试验在飞行器研制过程中变得越来越重要，动力模拟风洞试验所占比重也越来越大。在风洞试验中，主要采用涡轮动力模拟器（TPS）和引射式模拟器（引射器）等发动机模拟装置来模拟涡扇发动机，即涡轮动力模拟器试验技术和引射式动力模拟试验技术[1-3]。
涡轮动力模拟器试验技术是目前风洞试验技术中最先进的发动机模拟试验技术，可较为真实地模拟发动机喷流和进气口流动，包括进气与喷流之间的相互干扰。涡轮动力模拟器的工作原理是采用高压空气驱动涡轮，由涡轮带动风扇为进气增压[4]，由进气口进入的空气经外涵排出，驱动涡轮的高压空气经内涵排出。在风洞内进行全机模型的涡轮动力模拟器风洞试验时，因为涡轮动力模拟器需要高压气来进行驱动，高压气流经过管路时会对天平测量带来较大的干扰力，对全模试验的测力精度造成影响，因此，对高压供气管路进行消扰处理十分必要。消除或减弱压缩空气流经天平时给天平测力带来的干扰载荷，是确保获得高精度试验数据的必要前提。
如何考虑内式空气桥天平的结构形式与精度，选用何种空气桥弹性单元结构，如何消除或修正空气桥附加刚度、温度梯度、内部气体压力的影响，如何确保系统的动态稳定性等，都是空气桥设计过程中必须考虑并需要突破的技术难点。
国外将内式空气桥天平技术视为动力模拟风洞试验的核心技术之一，在相关领域早已开展了技术研究。经过几十年的技术发展与突破，目前该项技术在法宇航与德荷宇航已属于成熟技术，但在我国仍处于核心设备研制的初步阶段，因此，在风洞内建立TPS动力模拟试验系统，形成大型低速风洞TPS动力模拟风洞试验能力，满足我国多个型号研制及改型对大尺寸风洞TPS 动力模拟与反推力试验的需求，摆脱对国外风洞该试验技术的依赖，提高空气桥天平技术水平显得尤为重要[5-8]。
涡扇飞机的动力模拟试验系统的集成度高，研制难度大，近些年来国内相继开展了技术研究。2010年，中国航空工业空气动力研究院研制了用于飞机推力矢量后体测力风洞试验用的空气桥天平。测试飞机模型内部空间有限，天平采用环式结构，阻力段采用对称U形结构，双四柱梁元件测量5个分量载荷。天平法向力和力矩测量电桥组合采用前后对称贴片组桥，天平前后采用法兰盘连接。2016年，中国空气动力研究与发展中心利用内式空气桥天平技术进行了TPS反推力试验。该试验采用的是与德荷宇航类似的空气桥天平（见图1）形式为：天平为杆式应变天平，两端法兰连接，由应变片进行温度补偿和电压补偿；空气桥总共两路：一端安装在天平固定端，另一端安装在天平浮动端，消扰单元采用波纹管式，在连接管路上布置两个压力测点和两个温度测点，用于测量空气桥的压力和温度，以便在进行天平修正时，扣除空气桥的压力和温度影响。查阅国内相关资料，国内已实施的空气桥核心消扰的形式是基于波纹管来开展消扰设计（内/外压波纹管）[9]。
20世纪80年代，德国达姆施塔特工业大学对空气桥进行了研究。1982年，德荷风洞联合体（DNW）首次针对大型客机空客A300研制的空气桥进行了功能试验。1983年，对该空气桥进行了校准和生产试验。此空气桥工作压力为6 MPa，规定气体流量为6 kg/s，安装空间直径为0.5 m。
近年来，DNW在DNW-LLF风洞内开展了推进系统集成测试空气桥系统的技术研究。研究结果表明，因受到风洞模型尺寸的限制，DNW/NLR 研究出了更紧凑的空气桥天平系统。新的空气桥系统可以在为模拟发动机提供高压气体的同时最小程度地影响天平的测量。同时，这些小的附加影响被证明是可以重复的和可修正的[10]。
法国国家宇航研究局的ONERA-F1风洞（3.5 m×4.5 m）拥有内式空气桥天平测力技术，可实现全模及半模的涡轮空气马达螺旋桨动力模拟试验，如图2所示。
该内式空气桥天平中间为杆式六分量天平，天平直径为210 mm，有6个供气波纹管，10个位移传感器。其中，上下两根直径较小的管路为高压进气空气桥管路，其余4个直径较大的管路为低压回气空气桥管路。天平两端与空气桥托架为锥形连接，整个系统两端分别用法兰盘与模型及支杆进行连接，空气桥管路结构中的消扰单元是波纹管，且有6套管路，整套内式空气桥天平体积较大[11]。
1　内式空气桥天平设计方法
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1.1　内式天平
目前，风洞试验中应用的天平主要为应变天平，应变天平主要分为杆式和盒式天平两种。考虑到内式空气桥天平在动力模拟试验中的应用，对比分析了杆式天平和盒式天平的安装空间紧凑性和受力解耦特点，内式空气桥天平的主体结构选用杆式天平。固定端和模型端均采用天平适配器法兰止口连接。天平外形尺寸为长700 mm，直径172 mm。采用双四柱截面梁作为弹性元件测量梁，测量升力、侧力、俯仰力矩、偏航力矩、滚转力矩，采用T字形弹性测量梁与支撑片形式，实现飞机阻力载荷测量。内式天平如图3所示。各元载荷测量处的应变计算结果如图4所示。各元设计量程下的应变值与信号输出大小见表1。
1.2　空气桥设计
空气桥天平系统及解耦消扰单元如图5所示。空气桥管路是空气桥天平的核心部件。本套空气桥系统由两路高压供气管路和6个解耦消扰单元组成。每一个管路上呈“鹅颈”式布置三个解耦消扰单元，每一个解耦消扰单元相当于一个十字铰链，组合后能够实现三个位移与三个角度的自由度解耦。在力载荷的作用下实现消扰，最大程度地减弱对测力天平的干扰影响。空气桥最大承压为10 MPa，工作温度为-10~70 ℃，设计通过管路的最大流量为4 kg/s，设计管道内通过气体的流速为80 m/s。
解耦消扰单元结构分为内外层结构，内层主要用于传输高压气体（与常规内/外压波纹管形式不同），外层主要用于实现载荷解耦消扰。
1.3　空气桥天平组合设计方法
根据设计好的天平模型和空气桥模型，构建空气桥天平整体模型，对空气桥天平整体进行计算分析，分别考虑了两路空气桥在整个系统中的刚度占比、阶梯供气压力下空气桥对天平的力与力矩的增量变化、阶梯温度变化下空气桥对天平的力与力矩的增量变化，以及温度与压力耦合工况变化下空气桥对天平的力与力矩的增量变化。空气桥系统的刚度评估如图6所示。空气桥天平模型网格划分如图7所示。
对天平进行强度校核计算，应力云图如图8所示，空气桥天平产生的最大应力在天平的四柱梁上，应力大小大约为648 MPa，符合强度需求。
对天平进行最大压力强度校核，管路需要承受的最大压力为10 MPa，为了验证空气桥天平在最大压力工作下的整体可靠强度，在天平各元最大载荷情况下，对空气桥管路内壁施加10 MPa静压进行计算，如图9所示。
根据计算结果（见表2）可以看出，空气桥天平在同时承受10 MPa静压以及综合载荷情况下产生的最大应力为680 MPa，产生最大应力部位在消扰单元的消扰梁处，材料强度极限为1350 MPa，符合强度需求。
对模型进行整体模态分析如图10所示，通过整体模态分析，一阶频率大于100 Hz，系统结构刚度高，风洞试验时不易产生共振，具有载荷测量的动态响应性能。
2　天平校准
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内式空气桥天平完成加工与粘贴后，在气动院10 T全自动体轴校准台上进行载荷校准，完成各状态下的载荷校准，并进行信号增量—载荷数据的数学处理，得到天平的使用公式，并计算天平的技术性能指标，见表3~表5。压力影响数据表明，空气桥供气时，气体压力对天平影响很小，与以往内/外波纹管式结构相比，影响量减小一个数量级，查阅外文文献材料，与德荷宇航空气桥的技术指标基本相当。
3　喷管测试验证
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涡扇飞机带动力模拟风洞试验，在进行正式模型风洞试验之前需要进行参考喷管试验。通过标准喷管试验可以测量出空气桥天平有供气流量存在时的气体流动影响量。在试验时，将喷管与天平模型端组合在一起，喷管的轴线与天平的轴线处在同一竖直平面内。气流通过空气桥从标准喷管中喷出，喷管对天平产生一定的推力。此时，天平所测量的力是空气桥流动影响产生的力和喷管对天平的作用力的综合力。将标准喷管180°反装，天平测量力为空气桥流动影响产生的力和反方向喷管对天平的综合作用力。
试验整体结构模型如图11、图12所示，喷管在天平正上方，喷管轴线与天平平行，减小对天平产生的影响。高压气流通过通气支杆流经空气桥，最后从喷管喷出。
从图13中的高压气体流量干扰量可以看出，气流干扰量的量级基本与天平重复精度相当，气流干扰量非常小，空气桥的消扰性能优越。
4　结论
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通过研究，可以得出以下结论：
（1）创新性地将内式天平与空气桥进行了一体化的集成设计，得到了空气桥天平组合工况下的最大应变分布规律。
（2）对内式空气桥天平进行了载荷校准试验，校准结果表明，天平及内式空气桥天平具有较高的精准度。在阶梯供气压力状态下，天平各元信号的变化较小，表明新结构形式的空气桥在高压供气压力下对天平的各元干扰量微小。
（3）通过设计标准喷管试验，对空气桥天平的流动影响进行试验验证。试验数据表明，空气桥天平输出数据重复性良好，准度较高，同时对比标准喷管正装和反装两种试验状态的数据，可以得到空气桥天平受到流动影响产生的残余力小。通过残余力数据曲线可以看出，残余力与质量流量成线性关系，且对空气桥天平影响量较小。
文献
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2025年第3卷第5期
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doi: 10.20118/j.issn2097-258X.2025.05.008
  • 接收时间：2025-04-20
  • 首发时间：2026-03-27
  • 出版时间：2025-09-10
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  • 收稿日期：2025-04-20
  • 修回日期：2025-05-30
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    1.中国航空工业空气动力研究院, 黑龙江　哈尔滨　150001
    2.低速高雷诺数气动力航空科技重点实验室　黑龙江　哈尔滨　150001
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小菇属 Mycena 11 5.26
光柄菇属 Pluteus 5 2.39
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