Results 171 to 180 of about 48,655 (212)
Adaptive morphing of wing and tail for stable, resilient, and energy-efficient flight of avian-inspired drones. [PDF]
Npj RobotJeger SL +3 more
europepmc +1 more source
A bionic bird jumping grasping structure design based on stm32 development board control. [PDF]
Sci RepZhang C, Shao W, Hao Y.
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Fiber-Reinforced Polymer Laminates in Aviation and Structural Engineering: A Synthetic Comparison of Performance Requirements, Design Principles, and Defect Assessment Procedures. [PDF]
Materials (Basel)Janeikaitė J +2 more
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Thermoplastic Fuselage: Impact Projection for Thermoplastic Fuselage Panel
2023Extracts from life cycle assessment (LCA) results and environmental impact projections for are thermoplastic fuselage demonstrator are presented.
Nioac de Salles, Ana Claudia +4 more
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Fuselage Aerodynamic Prediction Methods
33rd AIAA Applied Aerodynamics Conference, 2015Abstract A reliable estimation of the aerodynamics of the fuselage of an airplane is crucial in order to carry out a well-designed aircraft. About 30% of an aircraft zero-lift drag source is due to the fuselage. Its aerodynamic instability is impacting wing and horizontal tail design, as well as aircraft directional stability characteristics.
NICOLOSI, FABRIZIO +4 more
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CFRP fuselage structures - postbuckling permitted
Air & Space Europe, 2001CFRP (carbon fibre reinforced plastics) fuselage structures are expected to be realized with future generations of aircraft. Going into the postbuckling regime with these structures requires improved, fast and reliable procedures for analysis and design of stiffened fibre composite panels.
Zimmermann, R., Rolfes, R.
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Fuselage Configuration Studies
SAE Technical Paper Series, 1967<div class="htmlview paragraph">Because of the rapid growth of air travel, both cargo and passenger, the payload capacity required for future transport aircraft is too great to be accommodated by fuselages of conventional configuration (that is, single-deck, single-aisle, up to 6 seats abreast).
J. Morris, D. M. Ashford
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Aircraft Engineering and Aerospace Technology, 1931
IT has been found by model tests that the lift of a combination of an aeroplane body and a wing is not in general equal to the sum of the lifts of the two components when tested separately. This difference is broadly referred to as an interference effect. It is dependent on a number of factors which can be generalised into three groups:—
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IT has been found by model tests that the lift of a combination of an aeroplane body and a wing is not in general equal to the sum of the lifts of the two components when tested separately. This difference is broadly referred to as an interference effect. It is dependent on a number of factors which can be generalised into three groups:—
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2017
The EC135 helicopter fuselage represents a realistic and challenging test-case with a range of complex flow physics, such as 3D separation and an unsteady vortical wake. Whilst developing new turbulence models naturally begins with simple test-cases, the potential impact of any new approach for industry cannot truly be measured until they are assessed ...
N. Ashton, M. Fuchs, C. Mockett, B. Duda
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The EC135 helicopter fuselage represents a realistic and challenging test-case with a range of complex flow physics, such as 3D separation and an unsteady vortical wake. Whilst developing new turbulence models naturally begins with simple test-cases, the potential impact of any new approach for industry cannot truly be measured until they are assessed ...
N. Ashton, M. Fuchs, C. Mockett, B. Duda
openaire +1 more source