002 Hsb Imagebroschuere 2008 Abstract 16072012 0

HANDBUCH STRUKTURBERECHNUNG

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Prepared: Date:Checked:

Issue C Year 2008

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Dr. M. Schagerl J. Ribke / J. Broede 27.08.2008 IASB

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Luftfahrt-TechnischesHandbuch (LTH )


HSB

Fundamentals and Methodsfor

Aeronautical Design and Analyses

issued by


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Application in Aircraft Design

Lower door frame shell

Doublers

Section

Chemically milled sheet

Milled frames


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Application in Spacecraft Design

Ariane 4

Shell structures and tanks

Typical shell design:Sheet with riveted stringers

and frames


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Application in Engine Design

Compressor rotor

Engine (thrust 22000 − 33000 lbs),short and medium range aircraft

Turbine blade Segment of a vane ring

Intermediate housing

Turbine rotor disc


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Application in Helicopter Design

Multi−Purpose Helicopter

Cross−sectional view of pitchcontrol cuff and flexbeam

1. Main rotor blade2. Swashplate3. Main rotor hub shaft4. Rotating control rod

5. Driving unit6. Standard hub cap support7. Standard rotor hub cap8. Damper

Control cuff

Inplane stiffenerSandwich construction

Main rotor without bearing


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Application in Satellite Design

for tankCFRP support structure

Solar panel

CFRP sandwich

Bolted joint

Flange

X−Ray Satellite

Sandwich panel

Supply unit

Payload unit


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Aeronautical Fasteners

Selection of fasteners and bolts

Nut design forhigh dynamic strength

Example of a jointwith a barrel nut


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Contents

DefinitionsMaterials

JointsStatic AnalysesStatic StabilityStatic Strength

Fatigue and Damage ToleranceVibrations


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1 INDUSTRIE-AUSSCHUSS STRUKTUR-BERECHNUNGSUNTERLAGEN (IASB)

The ”Industrie-AusschussStruktur-Berechnungsunterlagen (IASB)” is a committee, which devel-ops fundamentals and methods for the analysis of aeronautical structures and their application.

The IASB was founded on25th November 1968 and consists of members from aeronautical indus-tries, research and academic institutions and civil and military authorities. Currently, the followinginstitutions are members of the IASB:

Authorities:Wehrtechnische Dienststelle für Luftfahrtzeuge,

Musterprüfwesen für Luftfahrtgerät der Bundeswehr (WTD 61)Luftfahrt Bundesamt (LBA)

Industries:AIRBUS DEUTSCHLAND GmbHEADS ASTRIUM - SPACE TRANSPORTATIONEADS MILITARY AIR SYSTEMSELBE FLUGZEUGWERKE GmbHEUROCOPTER DEUTSCHLAND GmbHFATEC ENGINEERINGFOKKER AESPGCT DESIGN ORGANISATION GmbHIABGmbHIMA DRESDEN GmbHLIEBHERR AEROSPACE LINDENBERG GmbHMT AEROSPACE AGMTU AERO ENGINES AGROLLS ROYCE DEUTSCHLAND Ltd & CO KGRUAG AEROSPACE GmbHXTREMEAIR GmbHZIM GmbH

Institutions:DLR BRAUNSCHWEIG, Institut für Faserverbundleichtbau undAdaptronikFRAUNHOFER INSTITUT LBF, Institut für Betriebsfestigkeitund SystemzuverlässigkeitHAW HAMBURG, Department Fahrzeugtechnik und FlugzeugbauNLR, Aerospace Vehicles DivisionTU BRAUNSCHWEIG, Institut für Flugzeugbau und LeichtbauTU CHEMNITZ, Institut für Allgemeinen Maschinenbau und KunststofftechnikTU DARMSTADT, Fachgebiet Konstruktiver Leichtbau und BauweisenTU DELFT, Faculty of Aerospace EngineeringTU DRESDEN, Institut für Leichtbau und Kunststofftechnik

The IASB is a member of the committee of theLTH (Luftfahrt-TechnischesHandbuch), which issponsored by the German Ministry of Defence.


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2 HANDBUCH STRUKTUR-BERECHNUNG (HSB)

2.1 General

The IASB documents methods and procedures in the ”HandbuchStruktur-Berechnung (HSB)”.The content of this handbook is based on international and national agreements and requirementsconcerning aeronautics. It is updated continuously.

The HSB is not for sale and is intended only for the use of selected recipients. Recipients areidentified by the issuing committee IASB. The HSB is issued inelectronic form, either on websites accessible via a member’s intranet or by DVD.

2.2 Responsibility

Only the IASB is responsible for the contents of the HSB. The IASB decides all relevant HSBitems, e.g.:

• Acceptance or rejection of the proposed HSB contributions

• Form, contents and consistency of the accepted HSB contributions

• Publication of the analytical methods, material values, test procedures, etc.

• Release of the agreed HSB contributions

• Formal selection of HSB recipients

The IASB decides all items by majority votes during the IASB meetings, which generally takeplace three times each year.

2.3 Application

The HSB is used for different disciplines, e.g.:

• Preliminary and final design of structural dimensions

• Definition of required tests regarding the development / justification of structural components

• Agreement of methods with different producers / suppliers

• Evaluation of structural components concerning justification

• Basis for the choice of materials

• Basis for the qualification of materials for suppliers


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Particularly, the HSB is used for analyses of structural components in:

• Aircraft design: fuselage, wing, etc.

• Spacecraft design: shell, engine support, etc.

• Satellite design: metallic and composite components, antennas, etc.

• Helicopter design: fuselage, rotor, etc.

• Engine design: rotor, stator, etc.

Although the focus lies on aeronautical topics the HSB can begenerally applied to the analysis oflightweight structure components used by other industries, e.g. rail vehicles, automobiles.

3 HSB ACCEPTANCE

The German military authority WTD61 and the German civil authority LBA are active members ofthe IASB. Thus it is guaranteed that all HSB contributions are accepted by the German authorities,which simplifies the procedure concerning evaluations and justifications of structural components.

All decisions within the IASB are taken in agreement with theindustries, universities, institutesand authorities that are active IASB members. The contributions to the HSB

• are in agreement with national and international methods and will be updated continuously

• contain international requirements (e.g. MIL, FAR, JAR)

• are the basis for corresponding requirements being used in different industries

• are the basis for specific projects (e.g. ”A320-Guidelines”)

• are available for different international institutions

• are the basis for specifications to be valid for suppliers andsub-contractors

4 HSB CONTENT

The technical contents of the HSB are organized by the chapters:

• Chapter 00000: Definitions

• Chapter 20000: Joints

• Chapter 40000: Static Stability

• Chapter 60000: Fatigue and Damage Tolerance

• Chapter 10000: Materials

• Chapter 30000: Static Analyses

• Chapter 50000: Static Strength

• Chapter 70000: Vibrations

A brief description of the chapters including examples is given in the following paragraphs.


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4.1 Chapter 00000: Definitions

Amongst other topics this chapter contains:

• List of symbols to be used

• Coordinate system

• Atmosphere data

• Internal pressure loads of transport aircraft

• List of units to be used

• Definition of sonic loads

• Determination of section data

• Inter- and extrapolation

• Regression analyses

• Statistics

Example: For the section given below the coordinate of the centre of shearxM is calculated pro-vided that the moment of inertiaIx is known.

By using given formulas it follows:Ix = 300600 mm4 andxM = −24, 8 mm.

S = Gravity centerM = Shear center


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4.2 Chapter 10000: Materials


• Metallic materials: aluminium alloys, titanium alloys, steels, heat resistant alloys

Product forms: sheet, plate, bar, extrusion, forging, tube, casting

• Composites: carbon Fibre Reinforced Plastics, Glass FibreReinforced Plastics

Product forms: tape, Prepreg, Roving

• Fibre-Metal-Laminates: ARALL, Glare

Product form: sheet

Example: For metallic materials, tempers and product forms, the following values are given fordifferent thicknesses and orientations:

Characteristic ValueStatic Strength tensile ultimate (tu)

tensile yield (ty)compressive yield (cy)shear ultimate (su)bearing ultimate (bru)bearing yield (bry)

Stiffness E-Moduli (tension, compression)Deformation elongation at failureSpecific Mass densityCorrosion Stress Corrosion Cracking (SCC)Fracture Toughnessplane strain, plane stressTemperature Value coefficients, stiffness

Furthermore, general information is given concerning the optimum material choice.


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4.3 Chapter 20000: Joints


• Analytical evaluation of joints

• Bearing strengths of non-removable joints

• Interaction of shear and tension loads

• Load-displacement behaviour of joints under shear loads

• Analyses of bolted and riveted areas

• Analyses of the rivet forces

• Guideline for the evaluation of allowable rivet forces

• Allowable rivet forces: solid rivets, interference fit rivets, blind rivets

• Analyses of bolted joints

• Allowable bolt forces

• Strength of bolts and nuts

• Analyses of the failure loads of metallic lugs

Example: For a single-shear-joint made of the aluminium alloy 2024-T3 riveted by countersunkLockbolt interference fit fasteners the static failure loads are to be determined.

From the given table the loads (in N) can be taken (sheet thicknesst, nominal diameterd):

t d (mm)mm 4.0 4.8 6.42.0 33302.5 4020 49303.0 5450 76504.0 9520


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4.4 Chapter 30000: Static Analyses


• One-dimensional systems: bars, straight and curved beams,circular rings

• Two-dimensional systems: membranes, plates, shells

• Statically undetermined systems

• Notched components: stress concentration factors, riveted joints, lugs

• Load introduction problems: flange, joints

• Composites: laminate theory

• Temperature problems: evaluation of loads, stiffness, deformations

Example: Determination of the stress concentration factor of an infinite plate with two circularholes of different diameters under uniaxial normal stresses.

Given: Geometry, applied remote stressσ

Solution: The stress concentration factorα1 can be found from the diagram:


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4.5 Chapter 40000: Static Stability


• Buckling of straight beams, plates, shells

• Stability of circular frames

• Buckling of composites

Example: The buckling stressσ of a plane sheet with riveted stiffeners is to be determined.

Given:

1. Geometry of sheet: thicknesst, pitch of the stiffenersb, pitch of the rivetsp, rivet diameterd

2. Geometry of stiffeners: thicknessts, width bs, heighths

3. Materials: E-Modulus of the sheet and the stiffenersE

4. Loading: uniaxial compression

Solution: The buckling stress is determined as

σ = k ·π2

·E

12 · (1 − ν2)· (t/b)2

The buckling factork depends on the datat, b, p, d, ts, bs, hs and can be taken from given diagrams.


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4.6 Chapter 50000: Static Strength


• Interaction of static loads applied on beams

• Static strength hypotheses

• Plasticity of one-dimensional systems

• Overcritical loads: Beams, plates, shells

• Static strength of composites and sandwich designs

• Evaluation of static strength tests

Example: The static strength of a component loaded by compression andshear is to be determined.

Given: Applied compression stressσg and shear stressτg

Solution: Interaction curve, which describes the static strength under combined loads:

(σ/σo)n + (τ/τo)

m = 1

whereσo is the normal stress corresponding toτ = 0 andτo is the shear stress corresponding toσ = 0. The dataσo, τo, n andm are known from test results.

Plotting the valuesσg, τg in theσ-τ -diagram, one obtains the Reserve Factors:

• RF > 1, if the pointσg, τg is located inside the interaction curve

• RF = 1, if the pointσg, τg is located on the interaction curve

• RF < 1, if the pointσg, τg is located outside the interaction curve

Interaction curves are given for different cases.


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4.7 Chapter 60000: Fatigue and Damage Tolerance


• Fatigue

– HAIGH diagrams and S-N diagrams of notched specimens

– WEIBULL parameters to describe the S-N curves

– Information about the fatigue strength of riveted joints and lugs

– Information about methods to enhance the fatigue life

• Damage Tolerance

– Stress intensity factors

– Crack growth behaviour (e.g. FORMAN equation)

– Residual strength performance (e.g. FEDDERSEN concept, R-CURVE concept)

Example: The fatigue lifeN (in cycles) of a component made of 2024-T3 with a givenKt is to bedetermined for the applied stress amplitudeσa = 60 MPa and a stress ratioR = 0.1.

Solution: From the WEIBULL equation

log N = C3 ·

[

ln

(

C2 − C1

σa − C1

)]1/C4

the dataN follows using the dataC1, . . . ,C4 as:

Kt C1 C2 C3 C4 N- MPa MPa - - cycles

2.5 38 194 4.63 5.25 1830543.6 23 194 4.39 3.53 89687


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4.8 Chapter 70000: Vibrations


• Eigenmodes

• Eigenfrequencies

Example: The datai andαi for the calculation of the eigenfrequencies of a simple-clamped beamis to be determined.

Solution:i andαi follow from the diagram:

System Mode DataCase 1 x / l

i = 0 α0 = 1.8750.226

i = 0 α0 = 4.694

kl

0.499 0.132

i = 2 α0 = 7.8540.644 0.356 0.094

i = 3 α0 = 10.9960.721 0.5 0.277 0.073

i = 4 α0 = 14.137


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IASB CONTACTS

For general information concerning the use of the HSB pleasecontact the IASB via the:

• IASB ChairmanDr. Martin SchagerlAirbus Deutschland GmbHStructure Analysis Stress [email protected]

• IASB Deputy ChairmanRobert DilgerEADS Military Air SystemsFatigue & Damage Tolerance [email protected]

For technical information concerning the application of HSB sheets contact the IASB via the:

• Responsible Expert Chapter 00000Christoph HeineAirbus Deutschland GmbHStructure Analysis Stress [email protected]

• Responsible Expert Chapter 10000Günther VolkmannAirbus Deutschland GmbHMaterials & Processes [email protected]

• Responsible Expert Chapter 20000Arthur SpainkFokker AESPF/[email protected]

• Responsible Expert Chapter 30000Georg GüntherEADS Military Air [email protected]

• Responsible Expert Chapter 40000Prof. Dr. Ralf [email protected]

• Responsible Expert Chapter 50000Dr. Jürgen [email protected]

• Responsible Expert Chapter 60000Robert DilgerEADS Military Air SystemsFatigue & Damage Tolerance [email protected]

• Responsible Expert Chapter 70000Prof. Dr. Ralf [email protected]

Documents

002 Hsb Imagebroschuere 2008 Abstract 16072012 0