{"title":"Similarity Conditions for Sandwich Shell-Like Configurations","authors":"G. Simitses, G. Song, V. Birman, Y. Frostig","doi":"10.1115/imece1999-0135","DOIUrl":"https://doi.org/10.1115/imece1999-0135","url":null,"abstract":"\u0000 There is renewed interest in the use of sandwich construction, especially for future large transport aircraft. The design and manufacture of these aircraft will require extensive experimental evaluation, which consists of the verification of the design before going to production. This step, the experimental verification, requires the production and testing of large components and prototypes, which is very expensive and time consuming. Use of similitude theory to establish similarity among structural systems can reduce the time and expense by testing small-scale models and use their data to predict the behavior of large prototypes.\u0000 This paper deals with the derivation of similarity conditions (scaling laws) for shell-like sandwich configurations. These conditions are needed to (a) design the small-scale models and (b) predict the behavior of the large prototype by employing the test data of the small-scale model and the scaling laws. The basis of the derivation of the scaling laws is that both systems are analytically governed by the same equations. Through the use of scale factors (prototype/model parameters) one can find the conditions under which the two systems of governing equations become identical.\u0000 Both the symbolic code “MAPLE” and the long hand manipulation of equations were used in the derivation of the similarity conditions. Details of the use of the symbolic code are not given, herein.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"4 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120908263","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"On Crack Extension in TSD Specimen With Foam Core","authors":"Xiaoming Li, L. Carlsson","doi":"10.1115/imece1999-0131","DOIUrl":"https://doi.org/10.1115/imece1999-0131","url":null,"abstract":"\u0000 The Tilted Sandwich Debond (TSD) specimen has recently been introduced for characterization of debond fracture of sandwich structure. A precracked sandwich is attached to an incline, and debonding is achieved by loading the partially debonded top face until further crack propagation occurs. In this paper we present numerical finite element analysis of stress intensity factors for several configurations of the TSD specimen, viz. crack in a homogeneous specimen, crack located at the face/core interface, and crack located slightly below the face/core interface. The tendency for crack kinking is examined over a range of tilt angles. The stress intensity factors and mode mixty displayed very little dependency on the tilt angle, but the results were shown to depend on the exact crack configuration.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124536739","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"Design of a Frangible Laminated Composite Launch Tube Closure","authors":"W. T. Wang, J. H. Wu, T. Kam","doi":"10.1115/imece1999-0141","DOIUrl":"https://doi.org/10.1115/imece1999-0141","url":null,"abstract":"\u0000 The concepts of designing a laminated composite frangible launch tube closure are elaborated. The frangible closure is a convex shell structure of which the external failure pressure is much higher than the internal failure pressure. The frangible closure is designed in such a way that when subjected to an internal impulsive pressure of magnitude greater than certain value, the closure will be broken into several pieces in accordance with a predetermined failure pattern. A number of frangible closures of different sizes are fabricated and subjected to burst strength tests. The failure modes and the effects of some specific design variables on the burst strength of the closure are studied using the experimental results. Basically, the frangible closure can achieve the design objectives.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"62 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121548492","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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