This book addresses anti-fatigue manufacturing, analysis and test verification technologies for typical aircraft structures, including fastening holes, shot peening plates, different types of joints and wing boxes. Offering concrete solutions to practical problems in aircraft engineering, it will benefit researchers and engineers in the fields of Aerospace Technology and Astronautics.

This legendary, still-relevant reference text on aircraft stress analysis discusses basic structural theory and the application of the elementary principles of mechanics to the analysis of aircraft structures. 1950 edition.

Many of the aircraft that form the backbone of the U.S. Air Force operational fleet are 25 years old or older. A few of these will be replaced with new aircraft, but many are expected to remain in service an additional 25 years or more. This book provides a strategy to address the technical needs and priorities associated with the Air Force's aging airframe structures. It includes a detailed summary of the structural status of the aging force, identification of key technical issues, recommendations for near-term engineering and management actions, and prioritized near-term and long-term research recommendations.

Results of test programs conducted to obtain structural performance information essential to the design of long-life composite aircraft structure are presented. Static, fatigue, and fracture tests were conducted on T300/5208 and T300/5209 graphite/epoxy laminate specimens which were representative of full-scale strength-designed laminates. Results showed that static tensile and compressive strength are significantly degraded by discontinuities and impact damage. Laminates with representative fiber damage are relatively insensitive to cyclic tensile loadings; however, cyclic compressive loading results in finite fatigue lives. Impact damage which caused barely visible fiber failure was found to reduce fatigue performance below that defined for an open hole. The graphite/epoxy laminates tested were found to be fracture sensitive. Laminate stacking sequence was found to have a significant influence on fracture strength and failure mode.

Aircraft Sustainment and Repair is a one-stop-shop for practitioners and researchers in the field of aircraft sustainment, adhesively bonded aircraft joints, bonded composites repairs, and the application of cold spray to military and civil aircraft. Outlining the state-of-the-art in aircraft sustainment, this book covers the use of quantitative fractography to determine the in-service crack length versus flight hours curve, the effect of intergranular cracking on structural integrity and the structural significance of corrosion. The book additionally illustrates the potential of composite repairs and SPD applications to metallic airframes. Covers corrosion damage assessment and management in aircraft structures Includes a key chapter on U.S. developments in the emerging field of supersonic particle deposition (SPD) Shows how to design and assess the potential benefits of both bonded composite repairs and SPD repairs to metallic aircraft structures to meet the damage tolerance requirements inherent in FAA ac 20-107b and the U.S. Joint Services