56 research outputs found
The ship-surgeon in the navy of the Order of St. John in Malta
Full text linkBy the time the Knights came to Malta in 1530, they had evolved into a highly efficient naval force. In this article the author describes the training provided to the surgical students of the Order of St. John. It describes in detail the day to day tasks performed when on board of the galleys and describes also the dangers the surgical teams encountered whilst sailing.peer-reviewe
Pengaruh Matakuliah Kewirausahaan Syariah Terhadap Minat Berwirausaha Mahasiswa FAI UMSU
No full textTujuandari penelitian ini adalah untuk mengetahui pengaruh dari
matakuliah kewirausahaan syariah terhadap minat berwirausaha mahasiswa untuk
berwirausaha. Adapun populasi dalam penelitian ini adalah adalah seluruh
mahasiswa semester enam dari Program Studi Bisnis & Manajemen Syariah dan
Program Studi Perbankan Syariah Fakultas Agama Islam (FAI) Universitas
Muhammadiyah Sumatera Utara (UMSU) yang berjumlah 204 orang mahasiswa.
Sedangkan sampel diambil dengan penentuan jumlah atau ukuran sampel
menggunakan cara rumusan Slovin sebanyak 67 orang mahasiswa. Teknik analisa
data menggunakan uji kualitas data, uji rebilitas data, uji regresi sederhana, uji
hipotesis, uji parsial t hitung (uji t).
Hasil penelitian ini menunjukkan bahwa berdasarkan hasil penelitian maka
dapat diambil kesimpulan bahwa Matakuliah Kewirausahaan Syariah
berpengaruh signifikan terhadap Minat berwirausaha mahasiswa hal ini
didasarkan pada hasil Uji t 7.253 > 1.996 nilai dengan sig 0,000 < 0,05
menunjukkan H0 ditolak dan Ha diterima. Berdasarkan uji Determinasi Nilai R
Square 0,447 atau 44,7% menunjukkan sekitar 44,7% variabel Minat
Berwirausaha mahasiswa (Y) dipengaruhi oleh Matakuliah Kewirausahaan
Syariah (X). Sementara sisanya sebesar 55,3% dipengaruhi oleh variabel yang
tidak diteliti dalam penelitian ini. Maka penulis menarik kesimpulan dalam
penelitian ini variabel Matakuliah Kewirausahaan syariah mempunyai pengaruh
positif dan signifikan sebesar 0,447 atau 44,7% terhadap Minat Berwirausaha
pada FAI UMSU
ANALISIS KINERJA ISLAMIC HUMAN RESOURCES BERDASARKAN METODE MASLAHAH SCORECARD (STUDI KASUS PADA PT. INALUM)
Full text linkThis study discusses the effectiveness of performance based on the Maslahah Scorecard measurement method and reveals the influence of aspects of Maqasid Al-Syariah on the performance of Muslim employees of PT. INALUM. The population in this study were Muslim employees who worked at PT. INALUM which amounted to 1622 employees with a total sample of 94 people responded and then in determining and selecting a sample of researchers using the Convenience Sampling technique. ased on the approach of this study using the Mix Method method. Based on the results of the study it can be concluded that aspects of Maqasid Al-Sharia have a positive and significant effect of 80.8% on performance while the remaining 19.2% is influenced by variables outside of this study and based on statistical calculations that the performance of Muslim employees PT. INALUM has a performance with an effective category with a performance score of 89.9%
Base di statua da Rodi con citazione di Aristofane
Full text linkThe statue base, found in Rhodes and belonging to the second/first century BC, preserves verses 454-9 of Aristophanes’ Frogs headed by the name of the author in the genitive: it is the only known epigraphic example of a classical text introduced by its author’s name. The inscribed text is also significant for the textual tradition of the Frogs, since it confirms the reading of some ancient medieval manuscripts. The inscription was found near the ancient gymnasium, where a library has recently been identified: it suggests that the text belonged to an educational context. At the same time, the religious aspect is evident both in the inscribed verses and in the comparison with a dedication from the Rhodian Peraea made by gymnasiarchs to Helios. Hence, the inscription contributes to our knowledge of the cultural, educational and religious environment of the late Hellenistic age Rhodes
The Residual Strength Failure Sequence in Fibre Metal Laminates
No full textThe concept of damage tolerance is a key aspect in ensuring and maintaining safety of an airframe structure over its design life. Developments in materials and structural design have both contributed to improvements in the damage tolerance of modern aircraft structures. Indeed, new developments in metal alloys, composite materials, and hybrid materials such as the Fibre Metal Laminates (FMLs) have all resulted in structures less sensitive to damage and capable to withstand more severe loading conditions. Among other materials, FMLs represent a clear example of damage tolerant hybrid materials, made by bonding thin metal sheets together with fibres embedded in epoxy. Exploiting the damage tolerance capability of FMLs is strictly related to the ability to firstly understand the occurring failure mechanisms, and secondly to be able to accurately describe those mechanisms. In this light, the present dissertation describes the investigation on the residual strength failure sequence in FMLs, and presents the development of an accurate analytical prediction method. The failure sequence is studied in particular for standard Glare laminates, which are relevant laminates for applications in aircraft pressurized fuselages. The developed analytical method has been implemented into two numerical models, considering both through-the-thickness crack and fatigue crack configurations. The developed models are validated against a large number of experimental data, which are also presented in this thesis. The main concept in this dissertation is that the crack growth process in the metallic layers of an FML can be described with the Crack Tip Opening Angle concept (CTOA). This approach includes the contribution of the fibre layers (e.g. fibre failure and fibre bridging) and the associated quasi-static delamination growth. An introduction to FMLs and to all various Glare grades, lay-ups, and manufacturing processes is provided in chapter 2. Some current and future applications for aircraft structures are also discussed in that chapter. A qualitative description of the principal failure mechanisms occurring during the residual strength failure sequence is presented in chapter 3. Based on experimental observations, the metal crack growth mechanisms, permanent plastic deformation, fibre failure and static delamination growth are discussed. All these mechanisms are related to each other, and all contribute to the residual strength of the laminate. The development of the prediction models aimed to be a step forward with respect to previous relevant prediction models available in literature. Therefore, both empirical and analytical prediction models available in literature are presented and discussed in chapter 4. A critical evaluation of those models has pointed out their limitations in applicability and versatility towards a “generic FML” concept. From this chapter, some guidelines have been defined to address the subsequent model development. Two types of experimental activities were carried out. The first type consisted in experiments to gain understanding of the deformation behaviour of both metallic and fibre layers. Extensive use of Digital Image Correlation technique enabled to observe and measure the deformation field of both metal and fibre layers, and their interaction. Further insight into the fibre bridging mechanism and into the metal-fibre interaction was obtained. These experimental activities are discussed in chapter 5. The second type of experimental activities aimed to generate input data for the prediction model, and to validate the CTOA approach. These are discussed in chapter 6. A large amount of experimental CTOA tests were conducted on several FML grades to evaluate the CTOA as failure criterion for FML. This included the investigation of the effect of metal sheet thickness, crack length-to-panel width ratio and the effect of bridging fibres. Static delamination growth tests were conducted to obtain the critical Strain Energy Release Rate. This parameter was subsequently used as input in the prediction model to define the critical condition for the delamination growth. Furthermore, in the same chapter, it is also discussed the complex interaction between static delamination growth and plastic deformation of the metallic layers. The core aspect of the present thesis concerns the modelling of the residual strength failure sequence, which is presented in chapter 7. Two models are described: one for the through-the-thickness crack and one for the fatigue crack. Both models are based on the same method, which uses the CTOA as crack growth driving parameter. The method is based on the idea that crack extension in the metallic layers occurs when the calculated CTOA reaches the critical value obtained from CTOA experiments on metal laminates containing the same metal layers used in the FML. The calculated CTOA is a function of the contribution due to the far-field stress in the aluminium layers, and the contribution of the fibres. The fibre can contribute either in terms of crack opening contribution (broken fibres) or crack closing contribution (bridging fibres present in the fatigue crack configuration). Plastic deformation ahead and behind the metal crack tip is accounted and implemented into the calculation. In addition, in the case of fatigue crack configurations, the bridging stress is calculated by solving the deformation compatibility equation, accounting for the plastic zone ahead of the crack tip and fibre failure in the bridging area. The bridging stress is subsequently used to calculate the quasi-static delamination growth occurring at the fibre-metal interface using the Strain Energy Release Rate approach. The model for through-the-thickness crack showed a very good agreement with the experimental data, while the model for fatigue crack configuration showed sufficient agreement with experimental data. The modelling of the fatigue crack configuration presents higher degree of complexity, which required a number of simplifications and assumptions, making the model less robust than the one for through-the-thickness crack. Chapter 8 summarises the conclusions of the investigations. It can be concluded that with the proposed models, the mechanisms related to the residual strength failure sequence are fully described and characterized. The model for through-the-thickness crack is robust and validated, and can be extended to other material and geometrical configurations. The model for fatigue crack is not robust enough, but further improvements are possible.Mechanics, Aerospace Structures & MaterialsAerospace Engineerin
PEMA - LiCF3SO3 polymer electrolytes: Assessment of conductivity and transport properties
No full textEffect of temperature on the transport property of PVdF-HFP-MPII-PC/DME gel polymer electrolytes
No full textEngineering turbulence modelling, simulation and measurements; preface special issue
No full textMulti-Scale PhysicsApplied Science
Laminate and airplane provided with such a laminate
No full textAerospace Materials & ManufacturingAerospace Engineerin
- …
