AA-SB-001: Analysis And Design Of Composite And Metallic Flight Vehicle Structures

Third Edition

2. REFERENCES

Reference: Abbott, Richard. Analysis and Design of Composite and Metallic Flight Vehicle Structures 3 Edition, 2019

The following documents form a part of this document to the extent referenced herein:

AC20-107B. (2009). Composite Aircraft Structure. Federal Aviation Administration.

AC43.13-1B, A. C. (1998). Acceptable Methods, Techniques and Practices – Aircraft Inspection and Repair. Oklahoma City.

AC43-4A, A. C. (1991). Corrosion Control for Aircraft. Federal Aviation Administration, William J White.

AFFDL-TR-69-42. (1986). Stress Analysis Manual. Airforce Flight Dynamics Laboratory, Wright Patterson.

AFWAL-TR-85-3069. (1985). Buckling of Laminated Composite Plates and Shell Panels. Arthur W Leissa.

AFWL-TR-86-3035. (1986). Design Guide for Bolted Joints in Composite Structures. Wright Patterson Flight Dynamic Laboratory.

AGARD-AG-278. (1985). Aircraft Corrosion: Causes and Case Histories. W. Wallace, D, W, Hoeppner, P. V. Kandachar.

AGARD-CP-590. (1996). Conference Proceedings 590: Bolted/Bonded Joints in Polymeric Composites. Advisory Group for Aerospace Research and Development.

ARC-CP-1380. (1977). The Strength of Bolted Joints in Multi-Directional CFRP Laminates. London: Aeronautical Research Council.

ARC-CP-235. (1956). The Buckling under Longitudinal Compression of a Simply Supported Panel that changes in Thickness across the Width. London: E. C. Capey.

ARC-RM-2652. (1953). Investigation of Skin Buckling. Bristol: D. J. Farrar.

ARC-RM-2778. (1953). The Elastic Stability of Sandwich Plates. London: ARC.

DOT/FAA/AR-01/33. (2001). Investigation of Thick Bondline Adhesive Joints. J. S. Tomblin, C. Yang, P. Harter.

DOT/FAA/AR-01/57. (2001). Investigation of Adhesive Behavior for Aircraft Applications. Washington: Yang, Tomblin.

DOT/FAA/AR-02/121. (2003). Guidelines for Analysis, Testing, and Nondestructive Inspection of Impact Damaged Composite Sandwich Structures. Federal Aviation Administration.

DOT/FAA/AR-10/6. (2011). Determining the Fatigue Life of Composite Aircraft Structures Using Life and Load-Enhancement Factors. Washington: John Tomblin & Waruna Seneviratne.

DOT/FAA/AR-99/49. (1999). Review of Damage Tolerance for Composite Sandwich Airframe Structures. Wichita: J. Tomblin, T. Lacy, B. Smith, S. Hooper, A. Vizzini and S. Lee.

ECSS-E-HB-32-22A. (2011). Insert Design Handbook. European Cooperation for Space Standardization.

ECSS-Q-ST-70-36C. (2009). Material Selection for Controlling Stress Corrosion Cracking. ECSS.

ESA-PSS-03-1202. (1987). Insert Design Handbook. European Space Research and Technology Center.

FAA-ACE100-2001-006. (2001). Static Strength Substantiation of Composite Airplane Structure; Policy Statement. Federal Aviation Administration.

FAA-H-8083-25A. (2008). Pilot’s Handbook of Aeronautical Knowledge. Oklahoma City: Federal Aviation Administration.

FAA-H-8083-30. (2008). Aviation Maintenance Technician Handbook. Oklahoma City: Federal Aviation Administration.

FAA-H-8083-31. (2012). Aircraft Maintenance handbook Volume 1. Oklahoma City: Federal Aviation Administration, Flight Standards Service.

FAA-PS-ACE100-2004-10030. (2005). Substantiation of Secondary Composite Structures. Federal Aviation Administration.

FAA-PS-ACE100-2005-10038. (2005). Bonded Joints and Structures – Technical Issues and Certification Considerations. Federal Aviation Administration.

FPL-070. (1964). Buckling Coefficients for Simpy Supported and Clamped Rectangular Sandwich Panels Under Edgewise Compression. Madison, Wisconsin: US Forest Service.

L.J. Hart-Smith. (1992). NASA-N92-32588 A New Approach to Fibrous Composite Laminate Strength Prediction. NASA.

MIL-HDBK-17A. (1973). Plastics for Aerospace Vehicles, Part II Transparent Glazing Materials. Wright-Patterson Airforce Base, Ohio: Richard S. Hassard.

MIL-HDBK-17F Vol 3. (2002). Polymer Matrix Composites Volume 3: Materials Usage Design and Analysis. Department of Defense.

MIL-HDBK-23A. (1968). Structural Sandwich Composites. Department of Defense.

MIL-HDBK-310. (1997). Global Climatic Data for Developing Military Products. Department of Defense.

Mil-HNDBK-17F-Vol1. (2002). Polymer Matrix Composites Volume 1: Guidelines for Characterization of Structural Materials.

MIL-HNDBK-5H. (1998). Metallic Materials and Elements for Aerospace Vehicle Structures. Department of Defense.

MIL-P-5425D. (1967). Military Specification, Plastic Sheet, Acylic, Heat Resistant. Department of Defense.

MIL-PRF-25690B. (1960). Performance Specification, Plastic, Sheeets and Formed Parts, Modified Acrylic Base, Monollithic, Crack Propagation Resistant. Lakehurst, NJ: Department of Defense.

MIL-S-8879C. (1991). Screw Threads, Controlled Radius Root with Increased Minor Diameter, General Specification For. Department of Defense.

MIL-STD-210C. (1987). Climatic Information to Determine Design and Test Requirements for Military Systems and Equipment. Department of Defense.

MIL-STD-889C. (2016). Standard Practice – Dissimilar Metals. Patuxent River, Maryland: US Department of Defense.

MSFC-SPEC-3679. (2012). MSFC Technical Standard – Process Specification – Welding Aerospace Hardware. Alabama: George C. Marshall Space Flight Center.

MSFC-SPEC-522B. (1987). Design Criteria for Controlling Stress Corrosion Cracking. George C Marshall Space Flight Center: NASA.

NACA-Report-1027. (n.d.). Buckling of Thin-Walled Cylinders Under Axial Compression and Internal Pressure. Hsu Lo, Harold Crate and Edward Schwartz.

NACA-Report-733. (n.d.). Critical Compressive Stress for Flat Rectangular Plates Supported aLng All Edges and Elastically Restrained Against Rotation Along the Unloaded Edges. Lundquist and Stowell.

NACA-Report-734. (n.d.). Critical Compressive Stress for Outstanding Flanges. Lundquist and Stowell.

NACA-TN-1051. (1946). Preliminary Investigation of the Loads Carried by Individual Bolts in Bolted Joints. Washington: NACA.

NACA-TN-1222. (1947). Buckling Stresses of Simply Supported Rectangular Flat Plates in Shear. Washington: M Stein and J Neff.

NACA-TN-1223. (1947). Critical Combinations of Shear and Direct Stresses for Simply Supported Rectangular Flat Plates. Langley, Virginia: Batdorf, Stein.

NACA-TN-1261. (1947). Effect of Variables in Welding Technique on the Strength of Direct Current Metal Arc Welded Joints in Aircraft Steel. Washington: Voldrich, Armstrong.

NACA-TN-1323. (1947). Charts for the Minimum-Weight Design of Multi-web Wings in Bending. Langley, Virginia: Langley Memorial Aeronautical Laboratory.

NACA-TN-1344. (1947). Critical Stress of Thin-Walled Cylinders in Torsion. Washington: S. B. Batdorf, Manuel Stein, Murray Schildcrout.

NACA-TN-1345. (1947). Critical Combination of Torsion and Direct Axial Stress for Thin-Walled Cylinders. Washington: S. B. Batdorf, Manuel Stein, Murray Schildcrout.

NACA-TN-1990. (1949). Plastic Buckling of a Long Flate Plate Under Combined Shear and Longitudinal Compression. Langley, Virginia: Stowell.

NACA-TN-2163. (1950). Critical Stress of Plate Columns. Washington: John C. Houbolt, Elbridge Z Stowell.

NACA-TN-2536. (1951). Critical Combinations of Bending Shear and Transverse Compressive Stresses for Buckling of Infinitely Long Plates. Washington: Aldie E. Johnson, Kenneth P. Buchert.

NACA-TN-2661. (1952). A Summary of Diagonal Tension, Part 1, Methods of Analysis. Washington: Paul Kuhn, James P Peterson, L. Ross Levin.

NACA-TN-306. (1929). Curves Showing Column Strength of Steel and Duralumin. Washington: Orrin E. Ross.

NACA-TN-3184. (1954). Buckling of Long Square Tubes in Combined Compression and Torsion and Comparison with Flat Plate Buckling Theories. Langley, Virginia: Peters.

NACA-TN-3781. (1957). Handbook of Structural Stability. G. Gerard, H. Becker.

NACA-TN-3785. (1957). Handbook of Structural Stability Part V – Compressive Strength of Flat Stiffened Panels. Washington: George Gerard.

NACA-TN-578. (1936). Full Scale Wind Tunnel and Flight Tests of a Fairchild 22 Airplane Fitted with a Fowler Flap. Washington.

NACA-TN-733. (1940). Chart for Critical Compressive Stress of Flat Rectangular Plates. Washington: H. N. Hill.

NACA-TN-862. (1942). An Investigation of the Effectiveness of Stiffeners on Shear Resistant Plate Girder Webs. Washington: R L Moore.

NACA-TN-888. (1943). Torsion of Flanged Members with Cross Sections Retrained Against Warping. Washington: H. N. Hill.

NACA-TN-902. (1943). Description of Stress-Strain Curves by Three Parameters. Washington: Walter Ramberg, William Osgood.

NACA-TN-927. (1944). Determination of Stress-Strain Relations from “Offset” Yield Strength Values. Washington: H N Hill.

NACA-TN-930. (1944). Tensile Tests of Round-Head, Flat-Head and Brazier-Head Rivers. Washington: Schuette, Bartone, Mandel.

NACA-WR-3K13. (1943). Critical Stress for an Infinitely Long Flat Plate With Elastically Restrained Edges Under Combined Shear and Direct Stress. Langley, Virginia: Stowell, Schwarz.

NACA-WR-L-323. (1942). The Strength and Stiffness of Shear Webs with Holes having 45deg Flanges. Langley: Paul Kuhn.

NASA 20090013076. (2009). Evaluation of Margins of Safety in Brazed Joints. Yury Flom, Len Wang, Mollie Powell, Mathew Soffa, Monica Rommel.

NASA 20120008193. (2012). Failure Assessment of Brazed Structures. Yuri Flom.

NASA 20120008328. (2012). Failure Assessment of Brazed Structures Using Failure Assessment Diagram. Yuri Flom.

NASA Conference Publication 3087, Part 2. (1990). Eighth DoD/NASA/FAA Conference on Fibrous Composites- in Structural Design. NASA.

NASA CR-1457. (1969). Manual For Structural Stability Analysis Of Sandwich Plates And Shells. R. T. Sullins, G. W. Smith, and E. E. Spier.

NASA CR-2330. (1974). Elastic Stability of Laminated Flat and Curved, Long Rectangular Plates Subjected to In-Plane Loads. A. Viswanathan, M. Tamekuni & L. L. Baker.

NASA TM X-73305. (1975). Astronautic Structures Manual Volume 1. NASA.

NASA TM X-73306. (1975). Astronautic Structures Manual Volume II. NASA.

NASA TM X-73307. (1975). Astronautic Structures Manual Volume III. NASA.

NASA/CR-1999-208994. (1999). Facesheet Wrinkling in Sandwich Structures. National Aeronautics and Space Administration.

NASA/CR-2001-210661. (2001). A Study of Failure Criteria of Fibrous Composite Materials. F. Paris.

NASA/TM-2006-241323. (2006). Experimental Observations for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined With Fasteners. F. P. Thomas.

NASA/TP-2011-216460. (2011). Comparison of Open-Hole Compression Strength and Compression After Impact Strength on Carbon Fiber/Epoxy Laminates for the Ares I Composite Interstage. A.J. Hodge, A.T. Nettles and J.R. Jackson.

NASA-CR-112236. (1973). Adhesive Bonded Single-Lap Joints. Hampton, Virginia: Hart-Smith.

NASA-CR-123772. (1972). Materials Data Handbook, Aluminum Alloy 6061. Alabama: R. F Muraca, J.S. Whittick.

NASA-CR-132548. (n.d.). Shear Buckling of Square Perforated Plates. Ithica: Gross kurth, White, Gallagher, Thomas.

NASA-CR-2064. (1972). Integration of NASA Sponsored Studies on Aluminum Welding. Cambridge, Massachusetts: NASA.

NASA-CR-2218-1. (1974). Analysis and Design of Advanced Composite Bonded Joints. L. J. Hart-Smith.

NASA-CR-3767. (1984). Durability and Damage Tolerance of Large Composite Primary Aircraft Structure (LCPAS). J. E. McCarty, W. G. Roeseler.

NASA-CR-4608. (1994). Strength Evaluation of Socket Joints. L.C. Rash.

NASA-CR-4746. (1996). High Lift System on Subsonic Airliners. Seattle: NASA Ames Research Center.

NASA-CR-4750. (1997). Handbook of Analytical Methods for Textile Composites. Langley: Brian N Cox, Gerry Flannagan.

NASA-NAS1-19347. (1997). A Summary and Review of Composite Laminate Design Guidelines. J. A. Bailie, R. P. Ley, A. Pasricha.

NASA-RP-1228. (1990). Fastener Design Manual. Lewis Research Center, Cleveland, Ohio.

NASA-RP-1351. (1994). Basic Mechanics of Laminated Composite Plates. A. T. Nettles.

NASA-STD-5006. (1999). General Fusion Welding Requirements for Aerospace Materials Used in Flight Hardware. NASA.

NASA-STD-5020. (2012). Requirements for Threaded Fastening Systems in Space Flight Hardware. Washington DC: NASA.

NASA-TM-1998-206542. (1998). Mechanical and Thermal Buckling of Rectangular plates with Cutouts. Dryden Flight Center: William L. Ko.

NASA-TM-2012-217454. (2012). Aerospace Threaded Fastener Strength in Combined Shear and Tension Loading. B.E. Steeve and R.J. Wingate: Marshall Space Flight Center, Huntsville, Alabama.

NASA-TM-87603. (1985). Failure Mechanisms of Laminates Transversely Loaded by Bolt Push Through. Langley Research Center, Langley, Virginia.

NASA-TN-D-7855. (1975). Analysis of Bonded Joints. Hampton, Virginia: Srinivas.

NASA-TN-D-7996. (1975). Numerical Analysis and Parametric Studies of the Buckling of Composite Orthotropic Compression and Shear Panels. J. M. Housner, M. Stein.

NASA-TP-2528. (1986). An Approximate Buckling Analysis for Rectangular Orthotropic Plates With Centrally Located Cutouts. Michael P. Nemeth, Manuel Stein & Eric R. Johnson.

NASA-TP-2935. (1989). Weld Stresses Beyond Elastic Limit. Alabama: V. Verderaime.

NASA-TP-3024. (1990). Buckling and Post Buckling of Compression Loaded Isotropic Plates with Cutouts. Langley, Virginia: Michael P. Nemeth.

NAVWEPS-REPORT-7827. (1962). Handbook of Equations for Mass and Area Properties of Various Geometrical Shapes. China Lake, California: U.S. Naval Ordnance Test Station.

OTS-PB-151074 DMIC Report 118. (1959). Welding of High Strength Steels for Missile Applications. Columbus, Ohio: Mishler, Monroe, Rieppel.

PS-ACE100-2001-006. (2001). Static Strength Substantiation of Composite Airplane Structure. Federal Aviation Administration.

(2013). Pull-through Failure of Composite Joints. Department of Mechanical Engineering, McGill University, Montreal: Zao Chen.

US Forest Service Report No . 1845. (1955). Stresses Induced in a Sandwich Panel by Load Applied at an Insert. Madison: United States Department of Agriculture.

2. REFERENCES

Reference: Abbott, Richard. Analysis and Design of Composite and Metallic Flight Vehicle Structures 3 Edition, 2019

The following documents form a part of this document to the extent referenced herein:

AC20-107B. (2009). Composite Aircraft Structure. Federal Aviation Administration.

AC43.13-1B, A. C. (1998). Acceptable Methods, Techniques and Practices – Aircraft Inspection and Repair. Oklahoma City.

AC43-4A, A. C. (1991). Corrosion Control for Aircraft. Federal Aviation Administration, William J White.

AFFDL-TR-69-42. (1986). Stress Analysis Manual. Airforce Flight Dynamics Laboratory, Wright Patterson.

AFWAL-TR-85-3069. (1985). Buckling of Laminated Composite Plates and Shell Panels. Arthur W Leissa.

AFWL-TR-86-3035. (1986). Design Guide for Bolted Joints in Composite Structures. Wright Patterson Flight Dynamic Laboratory.

AGARD-AG-278. (1985). Aircraft Corrosion: Causes and Case Histories. W. Wallace, D, W, Hoeppner, P. V. Kandachar.

AGARD-CP-590. (1996). Conference Proceedings 590: Bolted/Bonded Joints in Polymeric Composites. Advisory Group for Aerospace Research and Development.

ARC-CP-1380. (1977). The Strength of Bolted Joints in Multi-Directional CFRP Laminates. London: Aeronautical Research Council.

ARC-CP-235. (1956). The Buckling under Longitudinal Compression of a Simply Supported Panel that changes in Thickness across the Width. London: E. C. Capey.

ARC-RM-2652. (1953). Investigation of Skin Buckling. Bristol: D. J. Farrar.

ARC-RM-2778. (1953). The Elastic Stability of Sandwich Plates. London: ARC.

DOT/FAA/AR-01/33. (2001). Investigation of Thick Bondline Adhesive Joints. J. S. Tomblin, C. Yang, P. Harter.

DOT/FAA/AR-01/57. (2001). Investigation of Adhesive Behavior for Aircraft Applications. Washington: Yang, Tomblin.

DOT/FAA/AR-02/121. (2003). Guidelines for Analysis, Testing, and Nondestructive Inspection of Impact Damaged Composite Sandwich Structures. Federal Aviation Administration.

DOT/FAA/AR-10/6. (2011). Determining the Fatigue Life of Composite Aircraft Structures Using Life and Load-Enhancement Factors. Washington: John Tomblin & Waruna Seneviratne.

DOT/FAA/AR-99/49. (1999). Review of Damage Tolerance for Composite Sandwich Airframe Structures. Wichita: J. Tomblin, T. Lacy, B. Smith, S. Hooper, A. Vizzini and S. Lee.

ECSS-E-HB-32-22A. (2011). Insert Design Handbook. European Cooperation for Space Standardization.

ECSS-Q-ST-70-36C. (2009). Material Selection for Controlling Stress Corrosion Cracking. ECSS.

ESA-PSS-03-1202. (1987). Insert Design Handbook. European Space Research and Technology Center.

FAA-ACE100-2001-006. (2001). Static Strength Substantiation of Composite Airplane Structure; Policy Statement. Federal Aviation Administration.

FAA-H-8083-25A. (2008). Pilot’s Handbook of Aeronautical Knowledge. Oklahoma City: Federal Aviation Administration.

FAA-H-8083-30. (2008). Aviation Maintenance Technician Handbook. Oklahoma City: Federal Aviation Administration.

FAA-H-8083-31. (2012). Aircraft Maintenance handbook Volume 1. Oklahoma City: Federal Aviation Administration, Flight Standards Service.

FAA-PS-ACE100-2004-10030. (2005). Substantiation of Secondary Composite Structures. Federal Aviation Administration.

FAA-PS-ACE100-2005-10038. (2005). Bonded Joints and Structures – Technical Issues and Certification Considerations. Federal Aviation Administration.

FPL-070. (1964). Buckling Coefficients for Simpy Supported and Clamped Rectangular Sandwich Panels Under Edgewise Compression. Madison, Wisconsin: US Forest Service.

L.J. Hart-Smith. (1992). NASA-N92-32588 A New Approach to Fibrous Composite Laminate Strength Prediction. NASA.

MIL-HDBK-17A. (1973). Plastics for Aerospace Vehicles, Part II Transparent Glazing Materials. Wright-Patterson Airforce Base, Ohio: Richard S. Hassard.

MIL-HDBK-17F Vol 3. (2002). Polymer Matrix Composites Volume 3: Materials Usage Design and Analysis. Department of Defense.

MIL-HDBK-23A. (1968). Structural Sandwich Composites. Department of Defense.

MIL-HDBK-310. (1997). Global Climatic Data for Developing Military Products. Department of Defense.

Mil-HNDBK-17F-Vol1. (2002). Polymer Matrix Composites Volume 1: Guidelines for Characterization of Structural Materials.

MIL-HNDBK-5H. (1998). Metallic Materials and Elements for Aerospace Vehicle Structures. Department of Defense.

MIL-P-5425D. (1967). Military Specification, Plastic Sheet, Acylic, Heat Resistant. Department of Defense.

MIL-PRF-25690B. (1960). Performance Specification, Plastic, Sheeets and Formed Parts, Modified Acrylic Base, Monollithic, Crack Propagation Resistant. Lakehurst, NJ: Department of Defense.

MIL-S-8879C. (1991). Screw Threads, Controlled Radius Root with Increased Minor Diameter, General Specification For. Department of Defense.

MIL-STD-210C. (1987). Climatic Information to Determine Design and Test Requirements for Military Systems and Equipment. Department of Defense.

MIL-STD-889C. (2016). Standard Practice – Dissimilar Metals. Patuxent River, Maryland: US Department of Defense.

MSFC-SPEC-3679. (2012). MSFC Technical Standard – Process Specification – Welding Aerospace Hardware. Alabama: George C. Marshall Space Flight Center.

MSFC-SPEC-522B. (1987). Design Criteria for Controlling Stress Corrosion Cracking. George C Marshall Space Flight Center: NASA.

NACA-Report-1027. (n.d.). Buckling of Thin-Walled Cylinders Under Axial Compression and Internal Pressure. Hsu Lo, Harold Crate and Edward Schwartz.

NACA-Report-733. (n.d.). Critical Compressive Stress for Flat Rectangular Plates Supported aLng All Edges and Elastically Restrained Against Rotation Along the Unloaded Edges. Lundquist and Stowell.

NACA-Report-734. (n.d.). Critical Compressive Stress for Outstanding Flanges. Lundquist and Stowell.

NACA-TN-1051. (1946). Preliminary Investigation of the Loads Carried by Individual Bolts in Bolted Joints. Washington: NACA.

NACA-TN-1222. (1947). Buckling Stresses of Simply Supported Rectangular Flat Plates in Shear. Washington: M Stein and J Neff.

NACA-TN-1223. (1947). Critical Combinations of Shear and Direct Stresses for Simply Supported Rectangular Flat Plates. Langley, Virginia: Batdorf, Stein.

NACA-TN-1261. (1947). Effect of Variables in Welding Technique on the Strength of Direct Current Metal Arc Welded Joints in Aircraft Steel. Washington: Voldrich, Armstrong.

NACA-TN-1323. (1947). Charts for the Minimum-Weight Design of Multi-web Wings in Bending. Langley, Virginia: Langley Memorial Aeronautical Laboratory.

NACA-TN-1344. (1947). Critical Stress of Thin-Walled Cylinders in Torsion. Washington: S. B. Batdorf, Manuel Stein, Murray Schildcrout.

NACA-TN-1345. (1947). Critical Combination of Torsion and Direct Axial Stress for Thin-Walled Cylinders. Washington: S. B. Batdorf, Manuel Stein, Murray Schildcrout.

NACA-TN-1990. (1949). Plastic Buckling of a Long Flate Plate Under Combined Shear and Longitudinal Compression. Langley, Virginia: Stowell.

NACA-TN-2163. (1950). Critical Stress of Plate Columns. Washington: John C. Houbolt, Elbridge Z Stowell.

NACA-TN-2536. (1951). Critical Combinations of Bending Shear and Transverse Compressive Stresses for Buckling of Infinitely Long Plates. Washington: Aldie E. Johnson, Kenneth P. Buchert.

NACA-TN-2661. (1952). A Summary of Diagonal Tension, Part 1, Methods of Analysis. Washington: Paul Kuhn, James P Peterson, L. Ross Levin.

NACA-TN-306. (1929). Curves Showing Column Strength of Steel and Duralumin. Washington: Orrin E. Ross.

NACA-TN-3184. (1954). Buckling of Long Square Tubes in Combined Compression and Torsion and Comparison with Flat Plate Buckling Theories. Langley, Virginia: Peters.

NACA-TN-3781. (1957). Handbook of Structural Stability. G. Gerard, H. Becker.

NACA-TN-3785. (1957). Handbook of Structural Stability Part V – Compressive Strength of Flat Stiffened Panels. Washington: George Gerard.

NACA-TN-578. (1936). Full Scale Wind Tunnel and Flight Tests of a Fairchild 22 Airplane Fitted with a Fowler Flap. Washington.

NACA-TN-733. (1940). Chart for Critical Compressive Stress of Flat Rectangular Plates. Washington: H. N. Hill.

NACA-TN-862. (1942). An Investigation of the Effectiveness of Stiffeners on Shear Resistant Plate Girder Webs. Washington: R L Moore.

NACA-TN-888. (1943). Torsion of Flanged Members with Cross Sections Retrained Against Warping. Washington: H. N. Hill.

NACA-TN-902. (1943). Description of Stress-Strain Curves by Three Parameters. Washington: Walter Ramberg, William Osgood.

NACA-TN-927. (1944). Determination of Stress-Strain Relations from “Offset” Yield Strength Values. Washington: H N Hill.

NACA-TN-930. (1944). Tensile Tests of Round-Head, Flat-Head and Brazier-Head Rivers. Washington: Schuette, Bartone, Mandel.

NACA-WR-3K13. (1943). Critical Stress for an Infinitely Long Flat Plate With Elastically Restrained Edges Under Combined Shear and Direct Stress. Langley, Virginia: Stowell, Schwarz.

NACA-WR-L-323. (1942). The Strength and Stiffness of Shear Webs with Holes having 45deg Flanges. Langley: Paul Kuhn.

NASA 20090013076. (2009). Evaluation of Margins of Safety in Brazed Joints. Yury Flom, Len Wang, Mollie Powell, Mathew Soffa, Monica Rommel.

NASA 20120008193. (2012). Failure Assessment of Brazed Structures. Yuri Flom.

NASA 20120008328. (2012). Failure Assessment of Brazed Structures Using Failure Assessment Diagram. Yuri Flom.

NASA Conference Publication 3087, Part 2. (1990). Eighth DoD/NASA/FAA Conference on Fibrous Composites- in Structural Design. NASA.

NASA CR-1457. (1969). Manual For Structural Stability Analysis Of Sandwich Plates And Shells. R. T. Sullins, G. W. Smith, and E. E. Spier.

NASA CR-2330. (1974). Elastic Stability of Laminated Flat and Curved, Long Rectangular Plates Subjected to In-Plane Loads. A. Viswanathan, M. Tamekuni & L. L. Baker.

NASA TM X-73305. (1975). Astronautic Structures Manual Volume 1. NASA.

NASA TM X-73306. (1975). Astronautic Structures Manual Volume II. NASA.

NASA TM X-73307. (1975). Astronautic Structures Manual Volume III. NASA.

NASA/CR-1999-208994. (1999). Facesheet Wrinkling in Sandwich Structures. National Aeronautics and Space Administration.

NASA/CR-2001-210661. (2001). A Study of Failure Criteria of Fibrous Composite Materials. F. Paris.

NASA/TM-2006-241323. (2006). Experimental Observations for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined With Fasteners. F. P. Thomas.

NASA/TP-2011-216460. (2011). Comparison of Open-Hole Compression Strength and Compression After Impact Strength on Carbon Fiber/Epoxy Laminates for the Ares I Composite Interstage. A.J. Hodge, A.T. Nettles and J.R. Jackson.

NASA-CR-112236. (1973). Adhesive Bonded Single-Lap Joints. Hampton, Virginia: Hart-Smith.

NASA-CR-123772. (1972). Materials Data Handbook, Aluminum Alloy 6061. Alabama: R. F Muraca, J.S. Whittick.

NASA-CR-132548. (n.d.). Shear Buckling of Square Perforated Plates. Ithica: Gross kurth, White, Gallagher, Thomas.

NASA-CR-2064. (1972). Integration of NASA Sponsored Studies on Aluminum Welding. Cambridge, Massachusetts: NASA.

NASA-CR-2218-1. (1974). Analysis and Design of Advanced Composite Bonded Joints. L. J. Hart-Smith.

NASA-CR-3767. (1984). Durability and Damage Tolerance of Large Composite Primary Aircraft Structure (LCPAS). J. E. McCarty, W. G. Roeseler.

NASA-CR-4608. (1994). Strength Evaluation of Socket Joints. L.C. Rash.

NASA-CR-4746. (1996). High Lift System on Subsonic Airliners. Seattle: NASA Ames Research Center.

NASA-CR-4750. (1997). Handbook of Analytical Methods for Textile Composites. Langley: Brian N Cox, Gerry Flannagan.

NASA-NAS1-19347. (1997). A Summary and Review of Composite Laminate Design Guidelines. J. A. Bailie, R. P. Ley, A. Pasricha.

NASA-RP-1228. (1990). Fastener Design Manual. Lewis Research Center, Cleveland, Ohio.

NASA-RP-1351. (1994). Basic Mechanics of Laminated Composite Plates. A. T. Nettles.

NASA-STD-5006. (1999). General Fusion Welding Requirements for Aerospace Materials Used in Flight Hardware. NASA.

NASA-STD-5020. (2012). Requirements for Threaded Fastening Systems in Space Flight Hardware. Washington DC: NASA.

NASA-TM-1998-206542. (1998). Mechanical and Thermal Buckling of Rectangular plates with Cutouts. Dryden Flight Center: William L. Ko.

NASA-TM-2012-217454. (2012). Aerospace Threaded Fastener Strength in Combined Shear and Tension Loading. B.E. Steeve and R.J. Wingate: Marshall Space Flight Center, Huntsville, Alabama.

NASA-TM-87603. (1985). Failure Mechanisms of Laminates Transversely Loaded by Bolt Push Through. Langley Research Center, Langley, Virginia.

NASA-TN-D-7855. (1975). Analysis of Bonded Joints. Hampton, Virginia: Srinivas.

NASA-TN-D-7996. (1975). Numerical Analysis and Parametric Studies of the Buckling of Composite Orthotropic Compression and Shear Panels. J. M. Housner, M. Stein.

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