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Deformation analysis of wing structures /
The elementary theories of bending and torsion often do not describe the stresses in aircraft shell structures with adequate accuracy; more refined stress theories have therefore have developed over a period of years. Theories of this nature are applied to the problem of calculating the deflections,...
| Clasificación: | Libro Electrónico |
|---|---|
| Autor principal: | |
| Autor Corporativo: | |
| Formato: | Documento de Gobierno Electrónico eBook |
| Idioma: | Inglés |
| Publicado: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1947.
|
| Colección: | Technical note (United States. National Advisory Committee for Aeronautics) ;
no. 1361. |
| Temas: | |
| Acceso en línea: | Texto completo |
MARC
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| 100 | 1 | |a Kuhn, Paul, |e author. | |
| 245 | 1 | 0 | |a Deformation analysis of wing structures / |c by Paul Kuhn. |
| 264 | 1 | |a Washington, D.C. : |b National Advisory Committee for Aeronautics, |c 1947. | |
| 300 | |a 1 online resource (34 pages, 9 unnumbered pages) : |b illustrations | ||
| 336 | |a text |b txt |2 rdacontent | ||
| 337 | |a computer |b c |2 rdamedia | ||
| 338 | |a online resource |b cr |2 rdacarrier | ||
| 490 | 1 | |a National Advisory Committee for Aeronautics technical note ; |v number 1361 | |
| 500 | |a "Langley Memorial Aeronautical Laboratory." | ||
| 500 | |a Date of issue: July 1947. | ||
| 500 | |a Report no. NACA TN No. 1361. | ||
| 504 | |a Includes bibliographical references (page 34) | ||
| 520 | 3 | |a The elementary theories of bending and torsion often do not describe the stresses in aircraft shell structures with adequate accuracy; more refined stress theories have therefore have developed over a period of years. Theories of this nature are applied to the problem of calculating the deflections, particularly of wings. Bending as well as torsional deflections are discussed for wings without or with cut-outs. Whenever convenient, the formulas are given in such a form that they yield corrections to be added to the deflections calculated by means of the elementary theories. Examples show that the deflection corrections usually are quite small; very simple approximation formulas are therefore adequate for design purposes when conventional structures uder a reasonably uniform loading are being considered. | |
| 588 | 0 | |a Print version record. | |
| 590 | |a Knovel |b ACADEMIC - Aerospace & Radar Technology | ||
| 650 | 0 | |a Deformations (Mechanics) | |
| 650 | 0 | |a Airplanes |x Wings. | |
| 650 | 0 | |a Strains and stresses. | |
| 650 | 0 | |a Mathematics |v Formulae. | |
| 650 | 6 | |a Déformations (Mécanique) | |
| 650 | 6 | |a Avions |x Ailes. | |
| 650 | 6 | |a Contraintes (Mécanique) | |
| 650 | 6 | |a Mathématiques |v Formules. | |
| 650 | 7 | |a deformation. |2 aat | |
| 650 | 7 | |a stress. |2 aat | |
| 650 | 7 | |a strain. |2 aat | |
| 650 | 7 | |a formulas (algorithms) |2 aat | |
| 650 | 7 | |a Airplanes |x Wings |2 fast | |
| 650 | 7 | |a Deformations (Mechanics) |2 fast | |
| 650 | 7 | |a Mathematics |2 fast | |
| 650 | 7 | |a Strains and stresses |2 fast | |
| 655 | 7 | |a Mathematical formulae |2 fast | |
| 710 | 1 | |a United States. |b National Advisory Committee for Aeronautics, |e issuing body. | |
| 710 | 2 | |a Langley Aeronautical Laboratory. | |
| 730 | 0 | |a Technical Report Archive & Image Library (TRAIL) | |
| 776 | 0 | 8 | |i Print version: |a Kuhn, Paul. |t Deformation analysis of wing structures |w (OCoLC)652863425 |
| 830 | 0 | |a Technical note (United States. National Advisory Committee for Aeronautics) ; |v no. 1361. | |
| 856 | 4 | 0 | |u https://appknovel.uam.elogim.com/kn/resources/kpDAWSNAC1/toc |z Texto completo |
| 994 | |a 92 |b IZTAP | ||