Articles liés à Optimization of A Simple Aircraft Wing
- ÉditeurLAP LAMBERT Academic Publishing
- Date d'édition2019
- ISBN 10 6139458048
- ISBN 13 9786139458042
- ReliureBroché
- Langueanglais
- Nombre de pages72
- Coordonnées du fabricantnon disponible
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Optimization of A Simple Aircraft Wing
Edité par
LAP LAMBERT Academic Publishing, 2019
ISBN 10 : 6139458048
ISBN 13 : 9786139458042
Ancien ou d'occasion
Couverture souple
Vendeur : Buchpark, Trebbin, Allemagne
Évaluation du vendeur 5 sur 5 étoiles
Etat : Sehr gut. Zustand: Sehr gut | Seiten: 72 | Sprache: Englisch | Produktart: Bücher. N° de réf. du vendeur 34239028/2
Quantité disponible : 2 disponible(s)
Image d'archives
Optimization of A Simple Aircraft Wing
Edité par
LAP LAMBERT Academic Publishing, 2019
ISBN 10 : 6139458048
ISBN 13 : 9786139458042
Ancien ou d'occasion
Couverture souple
Vendeur : Buchpark, Trebbin, Allemagne
Évaluation du vendeur 5 sur 5 étoiles
Etat : Hervorragend. Zustand: Hervorragend | Seiten: 72 | Sprache: Englisch | Produktart: Bücher. N° de réf. du vendeur 34239028/1
Quantité disponible : 1 disponible(s)
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Optimization of A Simple Aircraft Wing
Edité par
LAP LAMBERT Academic Publishing, 2019
ISBN 10 : 6139458048
ISBN 13 : 9786139458042
Neuf
Couverture souple
Vendeur : moluna, Greven, Allemagne
Évaluation du vendeur 5 sur 5 étoiles
Etat : New. Dieser Artikel ist ein Print on Demand Artikel und wird nach Ihrer Bestellung fuer Sie gedruckt. Autor/Autorin: Srinivasa Rao DokkuDokku Srinivasa Rao(Ph.D),M.Tech(CAD/CAM),B.E(Mech),D.M.E,M.I.E(India),ISHRAE(India).Pursuing Ph.D from Andhra University,Completed M.Tech (CAD/CAM) from GITAM,B.E(Mech) from M.V.S.R.Engg.College affiliated to Osma. N° de réf. du vendeur 385859400
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Optimization of A Simple Aircraft Wing
Edité par
LAP LAMBERT Academic Publishing Mrz 2019, 2019
ISBN 10 : 6139458048
ISBN 13 : 9786139458042
Neuf
Taschenbuch
Vendeur : BuchWeltWeit Ludwig Meier e.K., Bergisch Gladbach, Allemagne
Évaluation du vendeur 5 sur 5 étoiles
Taschenbuch. Etat : Neu. This item is printed on demand - it takes 3-4 days longer - Neuware -In this parametric study the aircraft wing model was designed to a light weight, comfortable model which is also cost effective than the some of the existing models around the world. On testing the wing by applying uniformly distributed load, the Equivalent Stresses and the Total Deformations are calculated.The design of experiments was generated using central composite design method and subsequent optimization is carried out using screening method. Duly considered Aluminium material has the values of weight as 1050kg, 25985384.62 equivalent stresses. Now these values are optimized by 10% to the originally obtained values. The optimized values are, weight of leg is 948.2 kg, equivalent stresses are 2.8163E+07 and deformation is 0.81606m.Optimization problem was investigated in this paper. It is noticed that even though the basic geometry and the same sets of design variables are used, problem has radicaldifference with respect to design sensitivity. Optimized Problem possesses high sensitivity with respect to sizing design variables. Generally, it is not possible to determine beforehand which subset of design variables will be dominant in terms of sensitivity. 72 pp. Englisch. N° de réf. du vendeur 9786139458042
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Optimization of A Simple Aircraft Wing
Edité par
LAP LAMBERT Academic Publishing, 2019
ISBN 10 : 6139458048
ISBN 13 : 9786139458042
Neuf
Taschenbuch
Vendeur : AHA-BUCH GmbH, Einbeck, Allemagne
Évaluation du vendeur 5 sur 5 étoiles
Taschenbuch. Etat : Neu. nach der Bestellung gedruckt Neuware - Printed after ordering - In this parametric study the aircraft wing model was designed to a light weight, comfortable model which is also cost effective than the some of the existing models around the world. On testing the wing by applying uniformly distributed load, the Equivalent Stresses and the Total Deformations are calculated.The design of experiments was generated using central composite design method and subsequent optimization is carried out using screening method. Duly considered Aluminium material has the values of weight as 1050kg, 25985384.62 equivalent stresses. Now these values are optimized by 10% to the originally obtained values. The optimized values are, weight of leg is 948.2 kg, equivalent stresses are 2.8163E+07 and deformation is 0.81606m.Optimization problem was investigated in this paper. It is noticed that even though the basic geometry and the same sets of design variables are used, problem has radicaldifference with respect to design sensitivity. Optimized Problem possesses high sensitivity with respect to sizing design variables. Generally, it is not possible to determine beforehand which subset of design variables will be dominant in terms of sensitivity. N° de réf. du vendeur 9786139458042
Quantité disponible : 1 disponible(s)
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Optimization of A Simple Aircraft Wing
Edité par
LAP LAMBERT Academic Publishing Mär 2019, 2019
ISBN 10 : 6139458048
ISBN 13 : 9786139458042
Neuf
Taschenbuch
Vendeur : buchversandmimpf2000, Emtmannsberg, BAYE, Allemagne
Évaluation du vendeur 5 sur 5 étoiles
Taschenbuch. Etat : Neu. Neuware -In this parametric study the aircraft wing model was designed to a light weight, comfortable model which is also cost effective than the some of the existing models around the world. On testing the wing by applying uniformly distributed load, the Equivalent Stresses and the Total Deformations are calculated.The design of experiments was generated using central composite design method and subsequent optimization is carried out using screening method. Duly considered Aluminium material has the values of weight as 1050kg, 25985384.62 equivalent stresses. Now these values are optimized by 10% to the originally obtained values. The optimized values are, weight of leg is 948.2 kg, equivalent stresses are 2.8163E+07 and deformation is 0.81606m.Optimization problem was investigated in this paper. It is noticed that even though the basic geometry and the same sets of design variables are used, problem has radicaldifference with respect to design sensitivity. Optimized Problem possesses high sensitivity with respect to sizing design variables. Generally, it is not possible to determine beforehand which subset of design variables will be dominant in terms of sensitivity.Books on Demand GmbH, Überseering 33, 22297 Hamburg 72 pp. Englisch. N° de réf. du vendeur 9786139458042
Quantité disponible : 2 disponible(s)