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Article(id=1241784308655002455, tenantId=1146029695717560320, journalId=1241715181215068175, issueId=1241784304989175988, articleNumber=null, orderNo=null, doi=10.6052/1672-6553-2025-043, pmid=null, cstr=null, oa=null, hot=null, price=null, onlineType=0, articleFormat=0, articleType=null, articleTypeStr=null, receivedDate=1733328000000, receivedDateStr=2024-12-05, revisedDate=1745424000000, revisedDateStr=2025-04-24, acceptedDate=null, acceptedDateStr=null, onlineDate=1773994050419, onlineDateStr=2026-03-20, pubDate=null, pubDateStr=null, doiRegisterDate=null, doiRegisterDateStr=null, onlineIssueDate=1773994050419, onlineIssueDateStr=2026-03-20, onlineJustAcceptDate=null, onlineJustAcceptDateStr=null, onlineFirstDate=null, onlineFirstDateStr=null, sourceXml=null, magXml=null, createTime=1773994050419, creator=13701087609, updateTime=1773994050419, updator=13701087609, issue=Issue{id=1241784304989175988, tenantId=1146029695717560320, journalId=1241715181215068175, year='2025', volume='23', issue='10', pageStart='1', pageEnd='96', issueExtLink='null', onlineDate='null', pubDate='null', beforeIssueId=null, nextIssueId=null, price=null, status=1, issueComplete=1, articleOrder=1, issueType=-1, specialIssue=null, createTime=1773994049546, creator=13701087609, updateTime=1773994239413, updator=13701087609, preIssue=null, nextIssue=null, ext={EN=IssueExt(id=1241785101412012589, tenantId=1146029695717560320, journalId=1241715181215068175, issueId=1241784304989175988, language=EN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=), CN=IssueExt(id=1241785101412012590, tenantId=1146029695717560320, journalId=1241715181215068175, issueId=1241784304989175988, language=CN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=)}, issueFiles=null}, startPage=53, endPage=60, ext={EN=ArticleExt(id=1241784308889883483, articleId=1241784308655002455, tenantId=1146029695717560320, journalId=1241715181215068175, language=EN, title=Analysis of Blade Tip Clearance of Coaxial Rigid Rotor in Forward Flight, columnId=1241784307421872311, journalTitle=Journal of Dynamics and Control, columnName=Research Articles, runingTitle=null, highlight=null, articleAbstract=

Blade tip clearance is one of the most critical factors affecting the flight safety of coaxial rigid rotor helicopters. To accurately predict the blade tip clearance during forward flight, this study establishes a rotor/body coupling aeroelastic model based on 15-degree-of-freedom (15-DOF) medium-deformable beam and free wake model. Validation against the rotor natural frequency of XH-59A demonstrates a computational error that less than 5%, demonstrating the accuracy of the forward-flight blade tip clearance prediction method. The proposed method is then applied to analyzing the influence of lateral differential control, pitch angle, and sideslip angle on blade tip clearance during forward flight. The results indicate that lateral differential control can effectively control rotor rolling moment, and lateral differential control serve as a reliable means to ensure safe blade tip clearance during forward flight. Additionally, reduction in fuselage pitch angle during forward flight leads to more critical blade tip clearance conditions. An increase in sideslip angle affects the rotor lift offset and reduce blade tip clearance.

, correspAuthors=Zhihao Yu, 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, authorCompany=null, fund=null, authors=null, authorsList=Jinrui Zhao, Zhihao Yu, Yi Cheng, Feng Fan, Qihuang Jiang), CN=ArticleExt(id=1241784320965283910, articleId=1241784308655002455, tenantId=1146029695717560320, journalId=1241715181215068175, language=CN, title=前飞状态下共轴刚性旋翼桨尖间距分析, columnId=1241784307690307771, journalTitle=动力学与控制学报, columnName=研究论文, runingTitle=null, highlight=null, articleAbstract=

桨尖间距是影响共轴刚性旋翼直升机飞行安全的重要因素之一，为准确分析共轴刚性旋翼前飞过程中的桨尖间距变化规律，本文基于15自由度中等变形梁和自由尾迹模型建立了共轴刚性旋翼/机体耦合气动弹性模型.与XH-59A的旋翼固有特性试验结果进行对比，计算误差小于5%，并完成前飞状态下的桨尖间距计算验证，充分验证了共轴刚性旋翼桨尖间距计算方法的准确性.本文进一步分析了前飞状态下横向差动控制、机身俯仰角、侧滑角等因素对桨尖间距的影响规律，研究表明在共轴刚性旋翼直升机的前飞过程中，横向差动控制可以有效控制旋翼的滚转弯矩，是前飞过程中保证桨尖间距安全的有效手段；前飞过程中机身俯仰角减小会带来更为严苛的桨尖间距；前飞过程中侧滑角增大会影响旋翼的升力偏置，进而减小桨尖间距.

, correspAuthors=余智豪, authorNote=null, correspAuthorsNote=
† E-mail:
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Journal of Northwestern Polytechnical University，2017，35(5):915-921. （in Chinese）, articleTitle=Rotor control strategy analysis of coaxial rigid rotor high-speed helicopter, refAbstract=null)], funds=null, companyList=[AuthorCompany(id=1241784321288245329, tenantId=1146029695717560320, journalId=1241715181215068175, articleId=1241784308655002455, xref=null, ext=[AuthorCompanyExt(id=1241784321296633939, tenantId=1146029695717560320, journalId=1241715181215068175, articleId=1241784308655002455, companyId=1241784321288245329, language=EN, country=null, province=null, city=null, postcode=null, companyName=null, departmentName=null, remark=National Key Laboratory of Helicopter Aeromechanics, CHRDI, Jingdezhen　333001, China), AuthorCompanyExt(id=1241784321305022547, tenantId=1146029695717560320, journalId=1241715181215068175, articleId=1241784308655002455, companyId=1241784321288245329, language=CN, country=null, province=null, city=null, postcode=null, companyName=null, departmentName=null, 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journalId=1241715181215068175, articleId=1241784308655002455, language=EN, label=Table 1, caption=

The technical parameters of XH-59A

, figureFileSmall=null, figureFileBig=null, tableContent=
参数数值
旋翼半径/m 5.49
桨叶片数3×2
桨叶预扭角/（°）-10
旋翼额定转速/（rad/s）35.9
旋翼额定桨尖速度/（m/s）197.1
上下旋翼安装间距/m 0.77
起飞质量/kg 5500
质心（机体坐标系）（0.00，0.00，-0.89）
), ArticleFig(id=1241784334244450624, tenantId=1146029695717560320, journalId=1241715181215068175, articleId=1241784308655002455, language=CN, label=表1, caption=

XH-59A的总体技术参数

, figureFileSmall=null, figureFileBig=null, tableContent=
参数数值
旋翼半径/m 5.49
桨叶片数3×2
桨叶预扭角/（°）-10
旋翼额定转速/（rad/s）35.9
旋翼额定桨尖速度/（m/s）197.1
上下旋翼安装间距/m 0.77
起飞质量/kg 5500
质心（机体坐标系）（0.00，0.00，-0.89）
), ArticleFig(id=1241784334374474049, tenantId=1146029695717560320, journalId=1241715181215068175, articleId=1241784308655002455, language=EN, label=Table 2, caption=

The comparisons of calculated blade natural frequency of XH-59A with literature

, figureFileSmall=null, figureFileBig=null, tableContent=
模态阶次计算值文献[12]误差
一阶摆振1.27 1.33 4.51%
一阶挥舞1.44 1.49 3.22%
二阶挥舞4.38 4.19-4.53%
二阶摆振5.97 5.81-2.75%
三阶挥舞8.859.011.78%
), ArticleFig(id=1241784334617743682, tenantId=1146029695717560320, journalId=1241715181215068175, articleId=1241784308655002455, language=CN, label=表2, caption=

XH-59A的桨叶固有频率计算值与文献值对比

, figureFileSmall=null, figureFileBig=null, tableContent=
模态阶次计算值文献[12]误差
一阶摆振1.27 1.33 4.51%
一阶挥舞1.44 1.49 3.22%
二阶挥舞4.38 4.19-4.53%
二阶摆振5.97 5.81-2.75%
三阶挥舞8.859.011.78%
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前飞状态下共轴刚性旋翼桨尖间距分析
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赵金瑞 , 余智豪 † , 程毅 , 樊枫 , 江期凰
动力学与控制学报 | 研究论文 2025,23(10): 53-60
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动力学与控制学报 | 研究论文 2025, 23(10): 53-60
前飞状态下共轴刚性旋翼桨尖间距分析
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赵金瑞, 余智豪† , 程毅, 樊枫, 江期凰
作者信息
  • 中国直升机设计研究　所直升机动力学全国重点实验室，景德镇　333001

通讯作者:

† E-mail:
Analysis of Blade Tip Clearance of Coaxial Rigid Rotor in Forward Flight
Jinrui Zhao, Zhihao Yu† , Yi Cheng, Feng Fan, Qihuang Jiang
Affiliations
  • National Key Laboratory of Helicopter Aeromechanics, CHRDI, Jingdezhen　333001, China
doi: 10.6052/1672-6553-2025-043
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摘要
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桨尖间距是影响共轴刚性旋翼直升机飞行安全的重要因素之一，为准确分析共轴刚性旋翼前飞过程中的桨尖间距变化规律，本文基于15自由度中等变形梁和自由尾迹模型建立了共轴刚性旋翼/机体耦合气动弹性模型.与XH-59A的旋翼固有特性试验结果进行对比，计算误差小于5%，并完成前飞状态下的桨尖间距计算验证，充分验证了共轴刚性旋翼桨尖间距计算方法的准确性.本文进一步分析了前飞状态下横向差动控制、机身俯仰角、侧滑角等因素对桨尖间距的影响规律，研究表明在共轴刚性旋翼直升机的前飞过程中，横向差动控制可以有效控制旋翼的滚转弯矩，是前飞过程中保证桨尖间距安全的有效手段；前飞过程中机身俯仰角减小会带来更为严苛的桨尖间距；前飞过程中侧滑角增大会影响旋翼的升力偏置，进而减小桨尖间距.

共轴刚性旋翼  /  桨尖间距  /  中等变形梁  /  自由尾迹模型

Blade tip clearance is one of the most critical factors affecting the flight safety of coaxial rigid rotor helicopters. To accurately predict the blade tip clearance during forward flight, this study establishes a rotor/body coupling aeroelastic model based on 15-degree-of-freedom (15-DOF) medium-deformable beam and free wake model. Validation against the rotor natural frequency of XH-59A demonstrates a computational error that less than 5%, demonstrating the accuracy of the forward-flight blade tip clearance prediction method. The proposed method is then applied to analyzing the influence of lateral differential control, pitch angle, and sideslip angle on blade tip clearance during forward flight. The results indicate that lateral differential control can effectively control rotor rolling moment, and lateral differential control serve as a reliable means to ensure safe blade tip clearance during forward flight. Additionally, reduction in fuselage pitch angle during forward flight leads to more critical blade tip clearance conditions. An increase in sideslip angle affects the rotor lift offset and reduce blade tip clearance.

coaxial rigid rotor  /  blade tip clearance  /  medium-deformable beam  /  free wake model
赵金瑞, 余智豪, 程毅, 樊枫, 江期凰. 前飞状态下共轴刚性旋翼桨尖间距分析. 动力学与控制学报, 2025 , 23 (10) : 53 -60 . DOI: 10.6052/1672-6553-2025-043
Jinrui Zhao, Zhihao Yu, Yi Cheng, Feng Fan, Qihuang Jiang. Analysis of Blade Tip Clearance of Coaxial Rigid Rotor in Forward Flight[J]. Journal of Dynamics and Control, 2025 , 23 (10) : 53 -60 . DOI: 10.6052/1672-6553-2025-043
正文
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引言
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共轴刚性旋翼采用两副反向旋转的刚性无铰式旋翼，使得直升机桨盘两侧都存在前行桨叶，依靠前行桨叶产生大部分升力从而对后行桨叶有效卸载，解决了后行桨叶失速带来的速度限制，极大地提升了直升机的前飞速度[1].采用前行桨叶概念设计的共轴刚性旋翼直升机型号主要有X-59A、X-2、S-97和SB-1等，目前共轴刚性旋翼直升机的飞行速度最高可达460 km/h，远超常规构型直升机，是未来直升机发展的重要方向之一[2-5].共轴刚性旋翼直升机在利用升力偏置发挥旋翼升力的潜能的同时，也带来了更为严苛的上下旋翼间距工作状态.因此建立可靠的桨尖间距预估方法，是进行共轴刚性旋翼直升机动力学设计重要基础.如何准确反映共轴刚性旋翼直升机飞行过程中整机姿态对于桨尖间距的影响[6]，是进行桨尖间距计算面临的困难之一.
目前国内外就共轴刚性旋翼直升机的桨尖间距问题已开展相关研究.德国慕尼黑工业大学的Cameron[7]对2 m直径的ABC旋翼的拉力系数、阻力、桨尖间距等变量随升力偏置量的变化规律做了初步研究.西科斯基公司工程师Ruddel[8]阐述了关于桨尖间距与提前操纵角和横向差动周期变距的关系，并通过桨尖间距拍照系统验证了部分前飞状态下的桨尖间距数据.Xin[9]基于Gen Hel开展S-97共轴旋翼直升机的桨尖间距计算工作，并进一步考虑弹性旋翼轴对于桨尖间距的影响.Syal[10]基于自由尾迹模型开展悬停状态下的不同旋翼间距和桨叶扭转对于共轴旋翼气动干扰的影响规律分析.余智豪[11]针对升力偏置和前进比对共轴刚性旋翼的配平和响应的影响开展研究，建立了一套考虑升力偏置的共轴刚性旋翼配平方法.周云[12]针对升力偏置、交叉角等因素开展共轴旋翼桨尖间距规律分析.中国直升机设计研究所开展的4 m直径的共轴刚性旋翼模型桨尖间距测量试验，反映了共轴刚性模型旋翼在不同前进比和升力偏置状态下的桨尖间距变化规律.
共轴刚性旋翼直升机所处流场较为复杂，如果使用传统的线性入流模型或者动态入流模型，将存在较大计算误差.自由尾迹模型可以反映尾迹对于旋翼入流的影响，能够有效提升共轴旋翼气动特性的计算精度[13-18].因此本文采用15自由度中等变形梁模型和自由尾迹模型建立了考虑机体运动与旋翼耦合的共轴刚性旋翼气动弹性模型，并借助该模型开展前飞状态下的桨尖间距规律计算.
1　分析方法
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共轴刚性旋翼采用刚性桨叶设计，桨叶单元可以使用15自由度中等变形梁模型建模[19]，同时由于共轴旋翼飞行器通常存在上下旋翼气动干扰、旋翼机身干扰，因此使用自由尾迹模型进行气动力计算.本文基于拉格朗日型坐标系，描述耦合系统上任一点在惯性坐标系中的位形，采用Hamilton原理推导共轴刚性旋翼飞行器气弹耦合系统动力学方程[20].
1.1　气动力模型
由于共轴旋翼通常处于非定常流场中，因此使用考虑非均匀诱导速度引起尾迹畸变的自由尾迹模型，可以更好地考虑上下旋翼干扰、旋翼尾迹与平尾干扰对于旋翼非定常气动力的影响，本文中采用的共轴旋翼自由尾迹模型示意图如图1所示.
其中单片桨叶的尾迹可以表示：
其中，rb表示涡元在桨叶上径向位置r处的位置矢量，μ为自由速度矢量，ψ为方位角，φ为涡龄，D（ψ，φ）为尾迹畸变.
使用直线涡段离散尾迹，并采用Biot-Savart（B-S）定律计算空间任意点的诱导速度，后延尾迹积分得到空间中任意一点的诱导速度.诱导速度计算公式如下：
其中，dv为诱导速度，Γ为涡元环量，ds为涡元矢量，l为诱导速度点到涡元ds的距离.
根据诱导速度，利用ONERA模型的非定常气动力计算公式计算得到非定常气动力，具体公式如下：
其中dF为桨叶单元的非定常气动力，Cz1代表翼型不考虑动态失速的升力系数，Cz2代表动态失速对于升力系数的修正项，dL为桨叶单元长度.
1.2　结构动力学模型
采用15自由度中等变形梁模型建立桨叶的有限元模型，图2为桨叶有限元单元的自由度分布.
机身运动可以使用五自由度矢量表示：
上式中，xF、yF、zF为参考惯性系的机身运动；αs为机身俯仰运动，低头为正；ϕs为机身滚转，以向右滚转为正.
通过积分求得考虑机身运动的单片桨叶的应变能变分δUb以及动能变分δTb表达式如下：
上式中：u、v、w、ϕ分别为桨叶拉伸、摆振、挥舞、扭转自由度，ψh为旋翼旋转速度，xF、yF、zF、αs、ϕs为机身运动自由度.
将式（5）代入由Hamilton原理推导共轴刚性旋翼飞行器气弹耦合系统的动力学方程：
上式中：δU是耦合系统应变能变分；δT是耦合系统动能变分；δW是耦合系统外力虚功；其组成如下：
上式中：下标fuselage、b分别表示机身和桨叶，Nb为桨叶片数，Nr为旋翼个数，机身作为刚体处理，因此无应变能项.
通过耦合结构动力学模型与自由尾迹模型，推导得到共轴刚性旋翼/机身耦合系统的动力学方程：
上式中，M s（t）为系统质量阵，C s（t）为系统阻尼阵，K s（t）为系统刚度阵，q（t）为广义坐标，F（t）是常量项力，是系统结构非线性力项和气动力项.上式是一个非齐次方程，使用Newmark法求解得到上下旋翼各片桨叶的桨尖响应稳态解qu(t)和qt(t)，之后计算得到上下旋翼相交叉时的桨尖间距.
上式中Qtip(t)为上下旋翼交叉位置处上下旋翼桨尖间距，qu(t)为上旋翼桨尖响应，qt(t)为下旋翼桨尖响应，0.14R为上下旋翼安装间距.
2　模型验证
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为验证本文建立的共轴刚性旋翼桨尖间距计算方法的准确性，采用XH-59A共轴旋翼直升机作为算例开展计算验证，模型验证数据采用文献[8]中相关桨尖间距计算数据.XH-59A的旋翼总体参数如表1所示.
通过求解耦合系统动力学方程得到桨叶固有频率，并开展桨叶固有频率计算验证，采用XH-59A的桨叶结构参数如图3所示.
验证数据采用文献[12]中345 rpm转速下XH-59A的固有特性试验结果，结果显示桨叶固有频率计算值与文献值的误差不超过5%.对比结果可以验证计算模型采用的计算输入符合实际情况，同时建立的15自由度中等变形梁模型是适用于共轴刚性桨叶结构动力学建模.具体的固有频率对比结果如下表2所示.
之后验证不同前飞速度下的桨尖间距计算精度，验证数据采用文献[8]中经过实验验证的数据，对比了不同前飞速度下的桨尖间距计算结果，提前操纵角Γ=30°时桨尖间距（270°相位角）的对比结果如图4所示.通过计算分析，在72 km/h的桨尖间距突增，原因为施加了1°的横向差动控制.
接下来验证较高前飞速度下提前操纵角Γ=50°下桨尖间距（270°相位角）随前飞速度下桨尖间距变化情况，具体对比结果如图5所示.
本文的计算结果可以反映稳态前飞过程中桨尖间距变化规律，且在高速段的计算误差小于低速段，是由于小速度段的上下旋翼气动干扰更为强烈导致的.图6和图7分别为72 km/h前飞和252 km/h前飞速度下上下旋翼桨盘入流情况，从计算结果来看，在小速度段的上下旋翼尾迹干扰十分严重，随着飞行速度的增加，上旋翼的尾迹对于下旋翼的干扰会逐渐减小.
3　桨尖间距影响规律分析
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本节分析前飞过程中横向差动控制、机身俯仰角、侧滑角对桨尖间距的影响规律。
3.1　横向差动控制对于桨尖间距的影响规律
横向差动控制是共轴旋翼最具特色的操纵量，用于控制旋翼桨叶载荷、升力偏置以及桨尖间距[21].上下旋翼操纵公式如下：
式中，θo为总距操纵，A1为纵向周期变距，B1为横向周期变距，B'1为横向差动控制，Γ为提前操纵角.B'1在保证上下旋翼合滚转弯矩为0的前提下，分配上下旋翼的滚转弯矩，实现横向差动控制.
XH-59A的飞行策略是从72 km/h开始施加横向差动控制，图8为采用XH-59A的横向差动控制策略和不施加横向差动控制的桨尖间距计算结果对比，其中180 km/h为提前操纵角变化点，计算过程均采用全机配平，72 km/h前的计算点均不采用横向差动控制.图8显示随着前飞速度的增加，横向差动控制对桨尖间距的影响越来越明显，横向差动控制可以有效保证前飞过程中的桨尖间距安全.
横向差动控制可以有效控制桨毂滚转弯矩，减小桨毂载荷，桨尖间距与旋翼滚转弯矩具有强相关性.图9和图10给出有无横向差动控制对于上下桨毂滚转弯矩的影响规律，结果显示横向差动控制可以有效降低桨毂的滚转弯矩.
综上，横向差动控制可以有效控制桨尖间距，且随着前飞速度的增加，效果会越来越显著.同时横向差动控制可以有效控制高速前飞中的桨毂滚转弯矩，进而保证飞行安全.
3.2　机身俯仰角对于桨尖间距的影响规律分析
本节重点分析机身俯仰角对共轴刚性旋翼桨尖间距的影响，定义机身抬头为正.机身俯仰角影响旋翼入流，以及平垂尾的气动力，因此机身俯仰角可以显著影响桨尖间距.由于不同前飞速度下机身俯仰角对桨尖间距的影响规律具有相似性，因此选取108 km/h和252 km/h作为典型前飞速度开展机身俯仰角对桨尖间距的影响规律分析，具体计算结果如图11~14所示.
计算结果显示随着机身俯仰角减小，桨尖间距逐渐减小.这是由于随着机身俯仰角的减小，机身平尾气动力逐渐减小，此时旋翼的配平策略是增大旋翼纵向周期变距，因此桨尖响应动态值显著增加，桨尖间距逐渐减小.
3.3　侧滑角对于桨尖间距的影响规律分析
本小节重点分析侧滑角对共轴刚性旋翼桨尖间距的影响，定义当侧滑角为正时，航迹向右偏转.由于不同前飞速度下侧滑角对桨尖间距的影响规律具有相似性，因此选取108 km/h和252 km/h作为典型前飞速度开展侧滑角对桨尖间距的影响规律分析，具体计算结果如图15~19所示.从图中可以看出，随着侧滑角的增加，最小桨尖间距逐渐减小，不利于飞行安全.
上旋翼桨毂滚转弯矩的随侧滑角的变化规律显示，随着侧滑角的增大，旋翼上的滚转力矩逐渐增大.为配平这个滚转力矩，需要施加额外的横向操纵量产生反向的滚转弯矩进行配平，这也就引起旋翼桨尖动态响应增大进而导致了更为严酷的桨尖间距.
4　结论
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本文基于15自由度中等变形梁理论和自由尾迹模型建立了共轴刚性旋翼桨尖间距计算模型，桨尖间距的计算精度满足分析需求，并进一步分析了前飞过程中的桨尖间距变化规律，得到以下结论：
（1）横向差动控制可以有效控制旋翼桨叶载荷、升力偏置以及桨尖间距，在前飞中施加适当的横向差动控制，可以有效减小桨毂滚转弯矩，增大桨尖间距.
（2）机身俯仰角会影响旋翼的入流，以及平垂尾的气动力，随着机身低头，桨尖响应动态值增大，桨尖间距减小.在前飞中应避免机身大角度低头，保证飞行安全.
（3）随着侧滑角的增大，旋翼上的滚转力矩逐渐增大，为配平这个滚转力矩，需要施加额外的横向操纵量产生反向的滚转弯矩进行配平，这也就引起旋翼桨尖动响应增大进而导致了更为严酷的桨尖间距.
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2025年第23卷第10期
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doi: 10.6052/1672-6553-2025-043
  • 接收时间：2024-12-05
  • 首发时间：2026-03-20
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  • 收稿日期：2024-12-05
  • 修回日期：2025-04-24
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    中国直升机设计研究　所直升机动力学全国重点实验室，景德镇　333001

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2种不同金属材料的力学参数
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鹅膏菌科Amanitaceae 2 11 5.26 鹅膏菌属 Amanita 10 4.78
小菇科 Mycenaceae 2 12 5.74 丝盖伞属 Inocybe 5 2.39
多孔菌科 Polyporaceae 8 14 6.70 蜡蘑属 Laccaria 5 2.39
红菇科 Russulaceae 3 23 11.00 小皮伞属 Marasmius 6 2.87
小菇属 Mycena 11 5.26
光柄菇属 Pluteus 5 2.39
红菇属 Russula 17 8.13
栓菌属 Trametes 5 2.39
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