《纺织复合材料》课程参考文献（Composite Materials Handbook，Volume 3）Chapter 1 GENERAL INFORMATION

MIL-HDBK-17-3F Volume 3,Chapter 1 General Information CHAPTER 1 GENERAL INFORMATION 1.1 INTRODUCTION This standardization handbook has been developed and is maintained as a joint effort of the Depart- ment of Defense and the Federal Aviation Administration,with considerable participation and input from industry,academia and other government agencies.It is oriented toward the standardization of 1)meth- ods used to develop,analyze and publish mechanical property data for composite materials,2)proce- dures to allow design organizations to effectively use the property data published in Volume 2 of this Handbook and other similar databases,and 3)general procedures for designing,analyzing and testing composite structures.In many cases,the standardization is intended to address the needs and require- ments of the customer and regulatory agencies,while providing efficient engineering practices. The standardization of a statistically-based mechanical property data base,procedures used,and overall guidelines for the characterization and use of composite material systems is recognized as being beneficial to both manufacturers and government agencies.A complete characterization of the capabilities of any engineering material system depends on the inherent material physical and chemical composition, which are independent of specific applications.Therefore,at the material system characterization level, the data and guidelines contained in this handbook apply to military and commercial products and provide the technical basis for establishing statistically valid design values acceptable to certifying or procuring agencies. 1.2 PURPOSE,SCOPE,AND ORGANIZATION OF VOLUME 3 For Department of Defense purposes,this handbook is for guidance only.This handbook cannot be cited as a requirement.If it is,the contractor does not have to comply.This mandate is a DoD require- ment only;it is not applicable to the Federal Aviation Administration(FAA)or other government agencies. Volume 3 of MIL-HDBK-17 provides methodologies and lessons learned for the design,analysis, manufacture,and field support of fiber-reinforced,polymeric-matrix composite structures.It also provides guidance on material and process specifications and procedures for utilization of the material data pre- sented in Volume 2.The information provided is consistent with the guidance provided in Volume 1 and intended to be an extensive compilation of the current"best knowledge and practices"of composite ma- terials and structures engineers and scientists from industry,government,and academia.This volume will be continually updated as the"state-of-the-art"of composites technology advances. Volume 3 contains the following chapters,which are arranged in an order,which approximately fol- lows the traditional "building-block"development approach: Chapter 2,Materials and Processes,defines major material systems and processing methods.Ef- fects of various processing parameters on final composite product performance are emphasized. Chapter 3,Quality Control of Production Materials,reviews important issues related to quality control in the production of composite materials.It reviews recommended manufacturing inspection pro- cedures and techniques for material property verification and statistical quality control. Chapter 4,Building Block Approach,outlines the rationale for the traditional multi-level testing and analysis development approach used for many metallic and composite structures programs,particularly in the aerospace industry.It also contains guidance and example building block test programs for various applications,including DoD/NASA prototype and production aircraft,commercial transport aircraft,busi- ness and private aircraft and rotorcraft. 1-1

MIL-HDBK-17-3F Volume 3, Chapter 1 General Information 1-1 CHAPTER 1 GENERAL INFORMATION 1.1 INTRODUCTION This standardization handbook has been developed and is maintained as a joint effort of the Depart￾ment of Defense and the Federal Aviation Administration, with considerable participation and input from industry, academia and other government agencies. It is oriented toward the standardization of 1) meth￾ods used to develop, analyze and publish mechanical property data for composite materials, 2) proce￾dures to allow design organizations to effectively use the property data published in Volume 2 of this Handbook and other similar databases, and 3) general procedures for designing, analyzing and testing composite structures. In many cases, the standardization is intended to address the needs and require￾ments of the customer and regulatory agencies, while providing efficient engineering practices. The standardization of a statistically-based mechanical property data base, procedures used, and overall guidelines for the characterization and use of composite material systems is recognized as being beneficial to both manufacturers and government agencies. A complete characterization of the capabilities of any engineering material system depends on the inherent material physical and chemical composition, which are independent of specific applications. Therefore, at the material system characterization level, the data and guidelines contained in this handbook apply to military and commercial products and provide the technical basis for establishing statistically valid design values acceptable to certifying or procuring agencies. 1.2 PURPOSE, SCOPE, AND ORGANIZATION OF VOLUME 3 For Department of Defense purposes, this handbook is for guidance only. This handbook cannot be cited as a requirement. If it is, the contractor does not have to comply. This mandate is a DoD require￾ment only; it is not applicable to the Federal Aviation Administration (FAA) or other government agencies. Volume 3 of MIL-HDBK-17 provides methodologies and lessons learned for the design, analysis, manufacture, and field support of fiber-reinforced, polymeric-matrix composite structures. It also provides guidance on material and process specifications and procedures for utilization of the material data pre￾sented in Volume 2. The information provided is consistent with the guidance provided in Volume 1 and intended to be an extensive compilation of the current "best knowledge and practices" of composite ma￾terials and structures engineers and scientists from industry, government, and academia. This volume will be continually updated as the "state-of-the-art" of composites technology advances. Volume 3 contains the following chapters, which are arranged in an order, which approximately fol￾lows the traditional "building-block" development approach: Chapter 2, Materials and Processes, defines major material systems and processing methods. Ef￾fects of various processing parameters on final composite product performance are emphasized. Chapter 3, Quality Control of Production Materials, reviews important issues related to quality control in the production of composite materials. It reviews recommended manufacturing inspection pro￾cedures and techniques for material property verification and statistical quality control. Chapter 4, Building Block Approach, outlines the rationale for the traditional multi-level testing and analysis development approach used for many metallic and composite structures programs, particularly in the aerospace industry. It also contains guidance and example building block test programs for various applications, including DoD/NASA prototype and production aircraft, commercial transport aircraft, busi￾ness and private aircraft and rotorcraft

MIL-HDBK-17-3F Volume 3,Chapter 1 General Information Chapter 5,Design and Analysis,addresses the basic design and analysis of composite laminates. The chapter provides an overview of the current techniques and describes how the various constituent properties contained in Volume 2 are used in the design and analysis of a composite structure.It presents standard analyses to provide a common nomenclature and methodology basis for users of MIL-HDBK-17. The analyses cover lamina and laminate stiffness and strength prediction,and compression buckling methods. Chapter 6,Design and Analysis of Structural Joints,describes accepted design procedures and analytical methods for determining stresses and deformations in structural bonded and mechanically fas- tened joints for composite structures. Chapter 7,Damage Resistance,Durability and Damage Tolerance,provides an extensive discus- sion of these three broad topics,which in general terms relate to the ability of a structure to perform the design functions over the life of the structure.Aircraft damage tolerance requirements and compliance approaches,types of damages and damage inspection are covered in the first sections of the chapter. Following these sections,in each of the three main areas,influencing factors,design issues and guide- lines,testing issues,and analysis methods are covered in detail.Most of the information was developed and is applicable to the aircraft industry,but the general guidelines and basic data provided have applica- tion to many other industries. Chapter 8,Supportability,considers the design for and the design of repairs in composite structures based on maintainability and reliability issues.It provides guidelines to the designer of new structures for considering supportability/maintainability issues,provides information relevant to the design of cost-effective repair procedures,and provides information related to logistical requirements for supporting and repairing composite structures. Chapter 9,Structural Reliability,discusses some of the important factors affecting composite struc- ture reliability including static strength,environmental effects,fatigue,and damage tolerance.It briefly discusses deterministic versus probabilistic design approaches. Chapter 10,Thick-Section Composites,details methods of thick-section laminate analysis, thick-section structural analysis techniques,physical property requirements for three-dimensional analy- sis,experimental property determination techniques,and fabrication process simulation techniques and models for thick laminates Chapter 11,Environmental Management,provides guidance for issues related to recycling and re- use of composite materials and structures. Chapter 12,Lessons Learned,documents a variety of issues related to earlier topics in this volume and provides a depository of knowledge gained from a number of involved companies,agencies,and uni- versities 1.3 SYMBOLS,ABBREVIATIONS,AND SYSTEMS OF UNITS This section defines the symbols and abbreviations which are used within MIL-HDBK-17 and de- scribes the system of units which is maintained.Common usage is maintained where possible.Refer- ences 1.3(a),1.3(b),and 1.3(c)served as primary sources for this information. 1.3.1 Symbols and abbreviations The symbols and abbreviations used in this document are defined in this section with the exception of statistical symbols.These latter symbols are defined in Chapter 8.The lamina/laminate coordinate axes used for all properties and a summary of the mechanical property notation are shown in Figure 1.3.1. 1-2

MIL-HDBK-17-3F Volume 3, Chapter 1 General Information 1-2 Chapter 5, Design and Analysis, addresses the basic design and analysis of composite laminates. The chapter provides an overview of the current techniques and describes how the various constituent properties contained in Volume 2 are used in the design and analysis of a composite structure. It presents standard analyses to provide a common nomenclature and methodology basis for users of MIL-HDBK-17. The analyses cover lamina and laminate stiffness and strength prediction, and compression buckling methods. Chapter 6, Design and Analysis of Structural Joints, describes accepted design procedures and analytical methods for determining stresses and deformations in structural bonded and mechanically fas￾tened joints for composite structures. Chapter 7, Damage Resistance, Durability and Damage Tolerance, provides an extensive discus￾sion of these three broad topics, which in general terms relate to the ability of a structure to perform the design functions over the life of the structure. Aircraft damage tolerance requirements and compliance approaches, types of damages and damage inspection are covered in the first sections of the chapter. Following these sections, in each of the three main areas, influencing factors, design issues and guide￾lines, testing issues, and analysis methods are covered in detail. Most of the information was developed and is applicable to the aircraft industry, but the general guidelines and basic data provided have applica￾tion to many other industries. Chapter 8, Supportability, considers the design for and the design of repairs in composite structures based on maintainability and reliability issues. It provides guidelines to the designer of new structures for considering supportability/maintainability issues, provides information relevant to the design of cost-effective repair procedures, and provides information related to logistical requirements for supporting and repairing composite structures. Chapter 9, Structural Reliability, discusses some of the important factors affecting composite struc￾ture reliability including static strength, environmental effects, fatigue, and damage tolerance. It briefly discusses deterministic versus probabilistic design approaches. Chapter 10, Thick-Section Composites, details methods of thick-section laminate analysis, thick-section structural analysis techniques, physical property requirements for three-dimensional analy￾sis, experimental property determination techniques, and fabrication process simulation techniques and models for thick laminates. Chapter 11, Environmental Management, provides guidance for issues related to recycling and re￾use of composite materials and structures. Chapter 12, Lessons Learned, documents a variety of issues related to earlier topics in this volume and provides a depository of knowledge gained from a number of involved companies, agencies, and uni￾versities. 1.3 SYMBOLS, ABBREVIATIONS, AND SYSTEMS OF UNITS This section defines the symbols and abbreviations which are used within MIL-HDBK-17 and de￾scribes the system of units which is maintained. Common usage is maintained where possible. Refer￾ences 1.3(a), 1.3(b), and 1.3(c) served as primary sources for this information. 1.3.1 Symbols and abbreviations The symbols and abbreviations used in this document are defined in this section with the exception of statistical symbols. These latter symbols are defined in Chapter 8. The lamina/laminate coordinate axes used for all properties and a summary of the mechanical property notation are shown in Figure 1.3.1

MIL-HDBK-17-3F Volume 3,Chapter 1 General Information Lamina Laminate 3.Thickness ◆z,Thickness 2,Transverse y,Transverse 1.Longitudinal x,Longitudinal Notation=Hik Where, o,t:Applied Normal,Shear Stress F:Allowable Stress Note:vMajor Poisson's Ratio- e H= e,Y:Extensional,Shear Strain v=Minor Poisson's Ratio- e E.G:Young's,Shear Modulus v;Poisson's Ratio e 1;Longitudinal c;Compression 2;Transverse -Lamina t:Tension 3;Thickness s;Shear 12,13.32:Shear,Poisson's- i= x;Longitudinal [y:Yield y;Transverse Laminate k✉ u:Ultimate,Not Used z:Thickness for Stiffness xy.xz,zy:Shear,Poisson's Examples, -Lamina Ultimate Transverse Tensile Allowable Stress Laminate Compressive Young's Modulus,Thickness Direction FIGURE 1.3.1 Mechanical property notation. 1-3

MIL-HDBK-17-3F Volume 3, Chapter 1 General Information 1-3 FIGURE 1.3.1 Mechanical property notation

MIL-HDBK-17-3F Volume 3,Chapter 1 General Information The symbols f and m,when used as either subscripts or superscripts,always denote fiber and matrix,respectively. The type of stress(for example,cy-compressive yield)is always used in the superscript position. Direction indicators(for example,x,y,z,1,2,3,etc.)are always used in the subscript position. Ordinal indicators of laminae sequence (e.g.,1,2,3,etc.)are used in the superscript position and must be parenthesized to distinguish them from mathematical exponents. Other indicators may be used in either subscript or superscript position,as appropriate for clarity. Compound symbols(such as,basic symbols plus indicators)which deviate from these rules are shown in their specific form in the following list. The following general symbols and abbreviations are considered standard for use in MIL-HDBK-17. Where exceptions are made,they are noted in the text and tables. -(1)area (m2,in2 -(2)ratio of alternating stress to mean stress -(3)A-basis for mechanical property values -(1)length dimension(mm,in) -(2)acceleration (m/sec2,ft/sec?) -(3)amplitude -(4)crack or flaw dimension(mm,in) B -(1)B-basis for mechanical property values -(2)biaxial ratio Btu -British thermal unit(s) b width dimension(mm,in),e.g.,the width of a bearing or compression panel normal to load, or breadth of beam cross-section C -(1)specific heat (kJ/kg C,Btu/lb F) -(2)Celsius CF centrifugal force (N,Ibf) CPF crossply factor CPT -cured ply thickness(mm,in.) CG -(1)center of mass,"center of gravity" -(2)area or volume centroid E centerline -column buckling end-fixity coefficient c -honeycomb sandwich core depth(mm,in) cpm -cycles per minute D -(1)diameter(mm,in) -(2)hole or fastener diameter(mm,in) -(3)plate stiffness(N-m,Ibf-in) d -mathematical operator denoting differential modulus of elasticity in tension,average ratio of stress to strain for stress below propor- tional limit(GPa,Msi) E -storage modulus (GPa,Msi) E" loss modulus (GPa,Msi) Ee -modulus of elasticity in compression,average ratio of stress to strain for stress below pro- portional limit (GPa,Msi) -modulus of elasticity of honeycomb core normal to sandwich plane(GPa,Msi) Esee secant modulus (GPa,Msi) Etan tangent modulus(GPa,Msi) e -minimum distance from a hole center to the edge of the sheet(mm,in) 1-4

MIL-HDBK-17-3F Volume 3, Chapter 1 General Information 1-4 • The symbols f and m, when used as either subscripts or superscripts, always denote fiber and matrix, respectively. • The type of stress (for example, cy - compressive yield) is always used in the superscript position. • Direction indicators (for example, x, y, z, 1, 2, 3, etc.) are always used in the subscript position. • Ordinal indicators of laminae sequence (e.g., 1, 2, 3, etc.) are used in the superscript position and must be parenthesized to distinguish them from mathematical exponents. • Other indicators may be used in either subscript or superscript position, as appropriate for clarity. • Compound symbols (such as, basic symbols plus indicators) which deviate from these rules are shown in their specific form in the following list. The following general symbols and abbreviations are considered standard for use in MIL-HDBK-17. Where exceptions are made, they are noted in the text and tables. A - (1) area (m2 ,in2 ) - (2) ratio of alternating stress to mean stress - (3) A-basis for mechanical property values a - (1) length dimension (mm,in) - (2) acceleration (m/sec2 ,ft/sec2 ) - (3) amplitude - (4) crack or flaw dimension (mm,in) B - (1) B-basis for mechanical property values - (2) biaxial ratio Btu - British thermal unit(s) b - width dimension (mm,in), e.g., the width of a bearing or compression panel normal to load, or breadth of beam cross-section C - (1) specific heat (kJ/kg °C,Btu/lb °F) - (2) Celsius CF - centrifugal force (N,lbf) CPF - crossply factor CPT - cured ply thickness (mm, in.) CG - (1) center of mass, "center of gravity" - (2) area or volume centroid CL - centerline c - column buckling end-fixity coefficient c - honeycomb sandwich core depth (mm,in) cpm - cycles per minute D - (1) diameter (mm,in) - (2) hole or fastener diameter (mm,in) - (3) plate stiffness (N-m,lbf-in) d - mathematical operator denoting differential E - modulus of elasticity in tension, average ratio of stress to strain for stress below propor￾tional limit (GPa,Msi) E' - storage modulus (GPa,Msi) E" - loss modulus (GPa,Msi) Ec - modulus of elasticity in compression, average ratio of stress to strain for stress below pro￾portional limit (GPa,Msi) c ’ E - modulus of elasticity of honeycomb core normal to sandwich plane (GPa,Msi) Esec - secant modulus (GPa,Msi) Etan - tangent modulus (GPa,Msi) e - minimum distance from a hole center to the edge of the sheet (mm,in)

MIL-HDBK-17-3F Volume 3.Chapter 1 General Information e/D -ratio of edge distance to hole diameter(bearing strength) F -(1)stress (MPa,ksi) -(2)Fahrenheit Eb bending stress(MPa,ksi) Fcer crushing or crippling stress(upper limit of column stress for failure)(MPa,ksi) Fsu ultimate stress in pure shear(this value represents the average shear stress over the cross-section)(MPa,ksi) FAW fiber areal weight (g/m2,Ib/in?) FV fiber volume (% -(1)internal (or calculated)stress (MPa,ksi) -(2)stress applied to the gross flawed section(MPa,ksi) -(3)creep stress(MPa,ksi) f -internal (or calculated)compressive stress(MPa,ksi) fe -(1)maximum stress at fracture (MPa,ksi) -(2)gross stress limit (for screening elastic fracture data(MPa,ksi) foot.feet 0 -modulus of rigidity(shear modulus)(GPa,Msi) GPa gigapascal(s) g -(1)gram(s) -(2)acceleration due to gravity (m/s2,ft/s2) H/C honeycomb(sandwich) h -height dimension(mm,in)e.g.the height of a beam cross-section hr -hour(s) -area moment of inertia(mm,in) -slope(due to bending)of neutral plane in a beam,in radians in. inch(es) -(1)torsion constant (Ip for round tubes)(m".in) -(2)Joule K -(1)Kelvin -(2)stress intensity factor(MPa/m,ksi/in) -(3)coefficient of thermal conductivity (W/m C,Btu/ft /hr/in/F) -(4)correction factor -(5)dielectric constant -apparent plane strain fracture toughness or residual strength(MPa/m,ksi/in) Ke critical plane strain fracture toughness,a measure of fracture toughness at point of crack growth instability (MPa/m,ksi/in) Kic -plane strain fracture toughness(MPa/m,ksi/in) KN -empirically calculated fatigue notch factor -plate or cylinder shear buckling coefficient K -(1)theoretical elastic stress concentration factor -(2)t/c ratio in H/C sandwich Kv -dielectric strength(KV/mm,V/mil) KxKy -plate or cylinder compression buckling coefficient k strain at unit stress(m/m,in/in) -cylinder,beam,or column length(mm,in) L' effective column length(mm,in) Ib pound M -applied moment or couple (N-m,in-lbf) Mg megagram(s) MPa -megapascal(s) MS military standard M.S -margin of safety MW -molecular weight MWD -molecular weight distribution 1-5

MIL-HDBK-17-3F Volume 3, Chapter 1 General Information 1-5 e/D - ratio of edge distance to hole diameter (bearing strength) F - (1) stress (MPa,ksi) - (2) Fahrenheit Fb - bending stress (MPa,ksi) Fccr - crushing or crippling stress (upper limit of column stress for failure) (MPa,ksi) Fsu - ultimate stress in pure shear (this value represents the average shear stress over the cross-section) (MPa,ksi) FAW - fiber areal weight (g/m2 , lb/in2 ) FV - fiber volume (%) f - (1) internal (or calculated) stress (MPa,ksi) - (2) stress applied to the gross flawed section (MPa,ksi) - (3) creep stress (MPa,ksi) f c - internal (or calculated) compressive stress (MPa,ksi) fc - (1) maximum stress at fracture (MPa,ksi) - (2) gross stress limit (for screening elastic fracture data (MPa,ksi) ft - foot, feet G - modulus of rigidity (shear modulus) (GPa,Msi) GPa - gigapascal(s) g - (1) gram(s) - (2) acceleration due to gravity (m/s2 ,ft/s2 ) H/C - honeycomb (sandwich) h - height dimension (mm,in) e.g. the height of a beam cross-section hr - hour(s) I - area moment of inertia (mm4 ,in4 ) i - slope (due to bending) of neutral plane in a beam, in radians in. - inch(es) J - (1) torsion constant (= Ip for round tubes) (m4 ,in4 ) - (2) Joule K - (1) Kelvin - (2) stress intensity factor (MPa/m,ksi/in) - (3) coefficient of thermal conductivity (W/m °C, Btu/ft2 /hr/in/°F) - (4) correction factor - (5) dielectric constant Kapp - apparent plane strain fracture toughness or residual strength (MPa/m,ksi/in) Kc - critical plane strain fracture toughness, a measure of fracture toughness at point of crack growth instability (MPa/m,ksi/in) KIc - plane strain fracture toughness (MPa/m,ksi/in) KN - empirically calculated fatigue notch factor Ks - plate or cylinder shear buckling coefficient Kt - (1) theoretical elastic stress concentration factor - (2) tw/c ratio in H/C sandwich Kv - dielectric strength (KV/mm, V/mil) Kx,Ky - plate or cylinder compression buckling coefficient k - strain at unit stress (m/m,in/in) L - cylinder, beam, or column length (mm,in) L' - effective column length (mm,in) lb - pound M - applied moment or couple (N-m,in-lbf) Mg - megagram(s) MPa - megapascal(s) MS - military standard M.S. - margin of safety MW - molecular weight MWD - molecular weight distribution