Structural components of aircraft

Megson, T.H.G.

doi:10.1016/b978-0-08-096905-3.00050-4

Cited by 6 publications

(9 citation statements)

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“…In some texts, 1 the symbol J is reserved for the polar second moment of area which is not implied here. Furthermore, in some texts on thin shell theory, 11 where the product of the shell thickness and the second moment of length is used extensively, the symbol I is employed and the implied meaning must be discerned from the context.…”

Section: Centroid Of a Surface Of Revolutionmentioning

confidence: 99%

“…A similar result is obtained for the position of the centroid in the y -direction, where cosθ is replaced by sinθ in the integral to yield, Finally, the position of the centroid in the z -direction is, Noting that both the radial position r and the axial position z are not functions of θ gives, where the second integral is recognized as the product second moment of length of the generating plane figure relative to the r - and z -axes, J rz , 11 giving the final result, …”

Section: Centroid Of a Surface Of Revolutionmentioning

confidence: 99%

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Extensions to the theorems of Pappus to determine the centroids of solids and surfaces of revolution

Cloete

2023

International Journal of Mechanical Engineering Education

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Extensions to the first and second theorems of Pappus are presented, whereby the centroid of a surface or solid of revolution can be determined using only the geometric properties of the generating plane curve or figure and the arc of revolution. The derivations are well suited to first-year-level courses in mathematics and engineering. From a didactic perspective, the resulting formulas are simple to apply, especially since the required geometric properties are typically available in standard tables of plane sections or relatively routine to derive. Furthermore, the formulas provide a general scaffold for students to attempt problems involving axisymmetric bodies while also reinforcing and embedding their knowledge of the properties of the generating plane shapes. A selection of illustrative problems is discussed that are generally regarded to be challenging for introductory mechanics courses but for which the formulas derived in this article provide straightforward solutions.

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Section: Centroid Of a Surface Of Revolutionmentioning

confidence: 99%

Section: Centroid Of a Surface Of Revolutionmentioning

confidence: 99%

Extensions to the theorems of Pappus to determine the centroids of solids and surfaces of revolution

Cloete

2023

International Journal of Mechanical Engineering Education

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“…A complex structure can be idealized into simpler models that behave in a similar manner as the real structure. Megson (2007) proposes in ideal mechanical model based on a skin-boom combination. The conservative assumptions behind this model are that stringers and spars can be substituted by area concentrations, which will carry all direct stresses, while the skins will carry only shear stresses.…”

Section: Theoretical Backgroundmentioning

confidence: 99%

“…Finally, the shear loads acting on the skin panels and the boom’s normal loads are evaluated. More details on the calculation process can be consulted in Ricci (2019) and Megson (2007). The model also provides longitudinal and angular displacements at the wingtip position.…”

Section: Design Proceduresmentioning

confidence: 99%

Multiobjective optimization of the LASER aircraft wing’s composite structural design

Ricco

Coimbra

Gomes

2021

AEAT

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Purpose Aircraft wings, one of the most important parts of an aircraft, have seen changes in its topological and design arrangement of both the internal structures and external shape during the past decades. This study, a numerical, aims to minimize the weight of multilaminate composite aerospace structures using multiobjective optimization. Design/methodology/approach The methodology started with the determination of the requirements, both imposed by the certifying authority and those inherent to the light, aerobatic, simple, economic and robust (LASER) project. After defining the requirements, the loads that the aircraft would be subjected to during its operation were defined from the flight envelope considering finite element analysis. The design vector consists of material choice for each laminate of the structure (20 in total), ply number and lay-up sequence (respecting the manufacturing rules) and main spar position to obtain a lightweight and cheap structure, respecting the restrictions of stress, margins of safety, displacements and buckling. Findings The results obtained indicated a predominance of the use of carbon fiber. The predominant orientation found on the main spar flange was 0° with its location at 28% of the local chord, in the secondary and main web were ±45°, the skins also had the main orientation at ±45°. Originality/value The key innovations in this paper include the evaluation, development and optimization of a laminated composite structure applied to a LASER aircraft wings considering both structural performance and manufacturing costs in multiobjetive optimization. This paper is one of the most advanced investigations performed to composite LASER aircraft.

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“…The impact load was then estimated using Newton's second law of motion and the given deceleration. The idealized beam method, as laid out by Megson [35], was then applied and iterated until a minimum-weight configuration was reached.…”

Section: Wing Construction and Draining Testsmentioning

confidence: 99%

Design and demonstration of a seabird-inspired fixed-wing hybrid UAV-UUV system

et al. 2018

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This paper looks to the natural world for solutions to many of the challenges associated with the design of fixed-wing cross-domain vehicles. One example is the common murre, a seabird that flies from nesting locations to feeding areas, dives underwater to catch prey and returns. This hunting expedition provides an outline of a possible mission for a cross-domain vehicle. While the challenges of cross-domain vehicles are many, the focus of this paper was on buoyancy management and propulsion. Potential solutions to each challenge, inspired by multiple animals that cross between aerial and underwater domains, are investigated. From these solutions, three design concepts are considered, a quadrotor/fixed-wing hybrid, a vertical takeoff and landing (VTOL) tailsitter aircraft, and a waterjet-assisted takeoff vehicle. A comparison was made between the capability of each concept to complete two missions based on the common murres' hunting expedition. As a result of this comparison, the VTOL tailsitter design was selected for further study. In-depth design was conducted and a prototype vehicle was built. The completed vehicle prototype successfully conducted submerged operation as well as four air flights. Flights consisted of egress from water, flight in air, ingress into water in each flight, and water locomotion. A total of 11 min, 23 s of flight time was recorded as well as underwater swims down to 12 ft (3.7 m) below the surface.

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Structural components of aircraft

Cited by 6 publications

References 0 publications

Extensions to the theorems of Pappus to determine the centroids of solids and surfaces of revolution

Extensions to the theorems of Pappus to determine the centroids of solids and surfaces of revolution

Multiobjective optimization of the LASER aircraft wing’s composite structural design

Design and demonstration of a seabird-inspired fixed-wing hybrid UAV-UUV system

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