If the moment of inertia of a cross section about a centroidal axis is known, the parallel axis theorem is used to calculate the moment of inertia about a parallel axis:
AA-SB-001: Analysis And Design Of Composite And Metallic Flight Vehicle Structures
Third Edition
- Table of Contents
- Revision History and Copyright Notice
- 1. SCOPE
- 2. REFERENCES
- 3. INTRODUCTION
- 4. MATERIALS
- 4.1. Composite Materials
- 4.1.1 Introduction
- 4.1.2. Basic Composite Material Primer
- 4.1.3. Fundamental Behavior of Carbon Fiber Epoxy Resin Composite Laminates
- 4.1.4. Environmental Conditions Considered
- 4.1.5. Manufacturing Effects Considered
- 4.1.6. Strength of Laminates
- 4.1.7. General Composite Laminate Analysis Approach
- 4.1.8. General Laminate Design Guidelines
- 4.2. Metallic Materials
- 4.3. Other Common Aircraft Materials
- 4.4. Corrosion
- 5. LOADS
- 6. SECTION PROPERTIES
- 7. STIFFNESS
- 8. BEAM ANALYSIS
- 9. TORSION
- 10. PLATE STRENGTH ANALYSIS
- 11. PRESSURE VESSELS
- 12. JOINTS
- 12.1. Adhesive Joints
- 12.2. Mechanically Fastened Joints
- 12.2.1. Introduction
- 12.2.2. Mechanical Joint Strength
- 12.2.3. Mechanical Joints in Metal Panels
- 12.2.4. Mechanical Joints in Composite Panels
- 12.2.5. Mechanical Joints, Examination of the Fastener
- 12.2.6. Potted Inserts in Cored Laminates
- 12.2.7. Fastener Interaction of Shear Load and Tension Load Effects
- 12.2.8. Mechanical Joints – Tension Clip Installations
- 12.2.9. Mechanical Joints – Lugs
- 12.2.10. Mechanical Joints – Lugs – Additional checks
- 12.2.11. Other Mechanical Connections
- 12.3. General Treatment of Contact Stresses
- 12.4. Strength of Brazed Joints
- 12.5. Strength of Welded Joints
- 13. COMBINED STRESSES
- 14. ULTIMATE STRENGTH OF METALLIC ELEMENTS
- 15. LOCAL STABILITY – ISOTROPIC MATERIALS
- 15.1. Introduction
- 15.2. General Buckling Expression
- 15.2.1. Introduction
- 15.2.2. Buckle Wavelength
- 15.2.3. Web Shear Buckling (Rectangular)
- 15.2.4. Panel Compression Buckling (Rectangular)
- 15.2.5. Interaction of Shear and Compression Buckling (Rectangular)
- 15.2.6. Flange Compression Buckling
- 15.2.7. Bending Buckling
- 15.2.8. Buckling of Triangular Panels
- 15.2.9. Reduction Factors Due to Cladding
- 15.2.10. Panel and Flange Buckling Summary
- 15.2.11. Inter-Rivet Buckling
- 15.3. Column Buckling
- 15.4. Buckling – Specific Cases
- 15.5. Crippling
- 16. LOCAL STABILITY – COMPOSITE MATERIALS
- 17. RESERVED
- 18. RESERVED
- 19. FINITE ELEMENT MODELLING
- 20. NOMENCLATURE
- 21. NUMERICAL METHODS
- 22. AIRCRAFT SPECIFIC DESIGN FEATURES AND DESIGN METHODS
- 22.1. Introduction
- 22.2. 06 Dimensions and Areas
- 22.3. 07 Lifting and Shoring
- 22.4. 08 Levelling and Weighing
- 22.5. 09 Towing and Taxiing
- 22.6. 25 Equipment and Furnishings (Interiors)
- 22.7. 27 Flight Controls
- 22.8. 28 Fuel
- 22.9. 29 Hydraulic Power
- 22.10. 32 Landing Gear
- 22.11. 52 Doors
- 22.12. 53 Fuselage
- 22.13. 54 Nacelles & Pylons
- 22.14. 55 Empennage/Stabilizers
- 22.15. 56 Windows
- 22.16. 57 Wings
- 22.17. 71 Powerplant
- 23. FIXED WING AIRCRAFT PERFORMANCE
- 24. OTHER AIRCRAFT TYPES: DESIGN AND ANALYSIS
- 25. CERTIFICATION
- 26. MICROSOFT EXCEL AS A REPORT WRITING TOOL
- 27. COMMON AIRCRAFT HARDWARE
6.1.4. Parallel Axis Theorem
6.1.4. Parallel Axis Theorem
If the moment of inertia of a cross section about a centroidal axis is known, the parallel axis theorem is used to calculate the moment of inertia about a parallel axis: