Buckling Analysis of Stiffened Panels Under Fuselage Bending
International Journal of Engineering & Technology, 2018 The utmost important characteristics in aircraft design were the structure load and safety. One of the main part of an aircraft is Fuselage. Depending on mass scattering of fuselage, the inertia forces will change along the length of the fuselage. Fuselage tends to bend down about axis wing due to Inertia force scattering.
Neela Rajan.R.R +3 more
openaire +2 more sources
Conformal Reconfigurable Intelligent Surfaces: A Cylindrical Geometry Perspective
Advanced Electronic Materials, EarlyView.Cylindrical reconfigurable intelligent surfaces are explored for low‐complexity beam steering using one‐bit meta‐atoms. A multi‐level modeling approach, including optimization‐based synthesis, demonstrates that even minimal hardware can support directive scattering.
Filippo Pepe +4 more
wiley +1 more source
Fatigue Crack Nucleation and Growth in Recrystallized Annealed Ti‐6Al‐4V Combat Aircraft Structures
Fatigue &Fracture of Engineering Materials &Structures, EarlyView.ABSTRACT In the Swiss Air Force (SAF) F/A‐18C/D Hornet fleet, recrystallized annealed Ti‐6Al‐4V was selected for the wing carry through bulkheads to meet their demanding operational usage profile requirements that included increased airframe strength and toughness.
I. Field +5 more
wiley +1 more source
Failure Analysis of Large-Scale Composite Fuselage Panels Under Combined Loads
AerospaceThe fuselage serves as the primary component of commercial aircraft. The strength reliability of fuselage panels is therefore crucial for commercial aircraft.
Fei Yuan +5 more
doaj +1 more source
Approximate Stability Analysis of Omega‐Stringer Stiffened Composite Panels
PAMM, Volume 26, Issue 1, March 2026.ABSTRACT Thin‐walled composite structures are widely used in weight‐critical applications such as aircraft and spacecraft. However, ensuring the stability of such structures under various load cases remains a key challenge in their design and optimization.
Cherine El Yaakoubi‐Mesbah +1 more
wiley +1 more source
Study on Unscheduled Direct Maintenance Cost of Civil Aircraft Structure
Hangkong gongcheng jinzhan, 2019 To solve the problem of the unscheduled direct maintenance cost of civil aircraft structure is difficult to predict in the design phase. The elements and influence factors of DMC are introduced, and the prediction flow, model and adjustment model are ...
Liu Yu +4 more
doaj +1 more source
Active Sidewall Panels with Virtual Microphones for Aircraft Interior Noise Reduction
Applied Sciences, 2020 This work deals with the reduction of aircraft interior noise using active sidewall panels (linings). Research work done in the past showed that considerable reductions of the sound pressure level (SPL) in the cabin are possible using structural ...
Malte Misol
doaj +1 more source
Aerodynamic Interference between Oscillating Lifting Surfaces and Fuselage. Part 6: A Panel Method for Non-Lifting Bodies Oscillating in Subsonic Flow [PDF]
INCAS Bulletin, 2017 In the sixth part of this series, we continue our study started in the previous article, i.e., we present the basis of the method for calculating the unsteady airforces on oscillating non-lifting bodies. The method proposed here is a panel one.
Valentin Adrian Jean BUTOESCU
doaj +1 more source
Sensitivity Analysis of the Elastic Properties of Graphene/Fiber‐Reinforced Nanocomposites
Polymer Composites, Volume 47, Issue 4, Page 3854-3865, 20 February 2026.The formation of graphene/fiber‐reinforced nanocomposites. ABSTRACT This study offers a detailed sensitivity analysis of the elastic behavior of graphene/fiber‐reinforced nanocomposites using a multiscale micromechanical modeling framework. It focuses on key elastic properties, which are the longitudinal modulus (E11), transverse modulus (E22), in ...
Ranganai Tawanda Moyo +2 more
wiley +1 more source
RESEARCH ON TEST METHOD OF FUSELAGE PANEL SUBJECTED TO SHEAR LOAD
Jixie qiangdu, 2017 The test method of fuselage panel subjected to shear load is an important technique for aircraft structure strength research. A new shear test method is proposed based on the property of aircraft fuselage panel subjected to shear load.
ZANG WeiFeng +3 more
doaj