Keywords : beam


TAIL PLANE DESIGN FOR SATISFYING LONGITUDINAL HANDLING QUALITIES

Yahya A. Faraj; Farag M. Mohammed; Mohammed A. Ahmed; Mohammed A. Ahmed; Waleed M. Abid; Ahmed N. Uwayed; Ghalib R. Ibrahim; Khaldon F. Breithe; Khalel I. Aziz; Arz Y. R; Hamdi E. A. Zangana; Akram Shaker Mahmood; Arz Yahya Rzayeg; Ahmed T. Al; Ejbari; Khaleel I. Aziz; Mazin Y.A; Riyah N. K; Nidaa Ezzy; Khamis N. Sayle; Nidaa Ezzy; xxxxx xxxxx; xxxxx xxxxxxx; xxxxx xxxxxx; zzzzzz zzzzzz

Anbar Journal of Engineering Sciences, 2008, Volume 1, Issue 2, Pages 1-14
DOI: 10.37649/aengs.2008.14201

The Cooper-Harper rating of aircraft handling qualities has been adopted as a standard for measuring the performance of aircraft. In the present work, the tail plane design for satisfying longitudinal handling qualities has been investigated with different tail design for two flight conditions based on the Shomber and Gertsen method. Tail plane design is considered as the tail/wing area ratio. Parameters most affecting on the aircraft stability derivative is the tail/wing area ratio. The longitudinal handling qualities criteria were introduced in the mathematical contributions of stability derivative. This design technique has been applied to the Paris Jet; MS 760 Morane-Sualnier aircraft. The results show that when the tail/wing area ratio increases the aircraft stability derivative increases, the damping ratio and the natural frequency increases and the aircraft stability is improved. Three regions of flight conditions had been presented which are satisfactory, acceptable and unacceptable. The optimum tail/wing area ratio satisfying the longitudinal handling qualities and stability is (0.025

Keywords

Longitudinal Handling
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Stability
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Tail Design

ANALYSIS OF MULTI-LAYER COMPOSITE SIMPLY SUPPORTED BEAM UNDER BLAST LOADING

Ahmed T. Al; Ejbari; Khaleel I. Aziz; xxxxx xxxxx; nnnnnn nnnnnn

Anbar Journal of Engineering Sciences, 2008, Volume 1, Issue 2, Pages 98-117
DOI: 10.37649/aengs.2008.14220

In this study an attempt is made to derive governing equations satisfying equilibrium and compatibility, for multi-layer composite simply supported beam under blast loading , for linear material and shear connector behavior in which the slip (horizontal displacement) and uplift force (vertical displacement) are taken into consideration. The analysis is based on an approach presented by Roberts, which takes into consideration horizontal and vertical displacements in interfaces. The model consists of a simply supported beam with three layers having a cross-sectional area ,different dimensions and material properties. The analysis led to a set of six differential equations containing derivatives of the fourth and third order. The blast loading was considered as a function of time. Explosions have different effects including blast, penetrations and fragmentation. The blast is the main effect which hits the structure in short duration. Multi –layer composite construction is the best type of constructions to resist the blast loading ; according to this , multi-layer composite construction is used for air-craft and marine industries. Analysis of composite beam under blast load , taking in consideration vertical and horizontal displacements, leads to six differential equations , the load is taken as a function of time.