Penilaian kepatuhan syariat islam dalam merekabentuk tanah perkuburan islam berkonsepkan taman teknologi

Tanah Perkuburan Islam di Malaysia telah mencapai banyak pembaharuan. Antaranya pembinaan Raudhatul Sakinah iaitu tanah perkuburan dalam taman. Pada peringkat awal, dua tanah perkuburan telah dijadikan tapak pembinaan iaitu Tanah Perkuburan Islam KL-Karak dan Tanah Perkuburan Islam Bukit Kiara yang diuruskan oleh Jabatan Agama Islam Wilayah Persekutuan (JAWI). Lanjutan dari itu sekumpulan penyelidik dari UTHM melakukan penambahbaikan melalui usaha merekabentuk Tanah Perkuburan Islam Berkonsepkan Taman Teknologi menggunakan dengan aplikasi Geographical Information System (GIS) sebagai nilaitambah dalam dalam proses pembinaan tanah perkuburan Islam yang lebih sistematik. Lokasi kajian ini terletak di Tanah Perkuburan Islam, Parit Raja, Batu Pahat. Perkembangan ini memerlukan memerlukan satu garis panduan yang jelas agar usaha yang dilakukan berada dalam ruang lingkup kepatuhan syariat Islam. Justeru kertas kerja ini dihasilkan bagi menilai kepa rekabentuk tanah perkuburan Islam berkonsepkan taman teknologi ini adalah selari dengan ketetapan syariat Islam. Pendekatan kajian ini menggunakan kaedah temubual, permerhatian dan kajian perpustakaan. Hasil dari analisis kajian, terdapat tiga aspek yang perlu diambilkira semasa merekabentuk tanah perkuburan berkonsepkan taman teknologi iaitu tujuan mengkebumikan jenazah, tujuan menziarahi kubur dan bentuk binaan di atas tapak perkuburan. Dapatan daripada kajian ini akan menjadikan rekabentuk Tanah Perkuburan berkonsepkan Taman Teknologi menepati syariat Islam, diterima serta dimanafaatkan oleh seluruh masyarakat Islam di Malaysia

Time-Domain System Identification for Long-EZ Fixed-Wing Aircraft Based on Flight Test Data

System identification using flight test data based on time-domain method is an accurate way of getting a reliable mathematical aircraft model. This thesis provides a system identification procedure on a canard configured fixed-wing aircraft Long-EZ, which is the early and critical stage of providing accurate aircraft models for designing an effective autopilot in the future. Flight test designed for Long-EZ aircraft has been carried out by International Test Pilot School (ITPS Canada Ltd). The real flight test data recorded from the testbed has been utilized for the identification and verification of a linear transfer function model, a nonlinear neural network model, and a block-oriented model consisting of linear and nonlinear parts. The linear transfer function structure has been determined with aircraft’s physical dynamics, and the model parameters have been identified using MATLAB System Identification toolbox. The nonlinearity of the aircraft dynamics has been treated with a Multilayer Perceptron (MLP) neural network structure, which has been developed with a set of Python codes. Flight data has been utilized to train this MLP structure. The results demonstrate different predicting capabilities of the developed linear, nonlinear, and combined linear and nonlinear structure, which is also known as the neural network Wiener model. The developed Wiener model in general shows satisfactory predicting capability for the testbed Long-EZ aircraft

Online parameter estimation of a miniature unmanned helicopter using neural network techniques

The online aerodynamic parameter estimation of a miniature unmanned helicopter using Neural Network techniques has been presented. The simulation model for the miniature helicopter was developed using the MATLAB/ SIMULINK software tool. Three trim conditions were analyzed: hover flight, 10m/s forward flight and 20m/s forward flight. Radial Basis Function (RBF) online learning was achieved using a moving window algorithm which generated an input-output data set at each time step. RBF network online identification was achieved with good robustness to noise for all flight conditions. However, the presence of atmospheric turbulence and sensor noise had an adverse effect on network size and memory usage. The Delta Method (DM) and the Modified Delta Method (MDM) was investigated for the NN-based online estimation of aerodynamic parameters. An increasing number high confidence estimated parameters could be extracted using the MDM as the helicopter transitioned from hover to forward flight

Design, manufacturing and testing of parachute recovery system for aludra SR-10 unmanned aerial vehicle (UAV)

Unmanned Systems Technology (UST) Aludra SR-10 Unmanned Aerial Vehicle (UAV) was purposely designed for survey and mapping mission. This study focuses on the design, manufacturing and testing of Parachute Recovery System (PRS) on the Aludra SR-10 UAV. A design work of PRS involving in defining a suitable type of parachute design, parachute compartment, parachute deployment and activation mechanism system. This study was performed by simulation approach (using Computational Fluid Dynamic, CFD) and experimental approach (static drop test and flight test). The evaluation of aerodynamics characteristics using ANSYS software over two types of parachute models (annular and cruciform parachutes canopy) help to determine the most suitable type of parachute design for PRS. The static drop test with on board system (consisted of NI myRio, IMU and GPS) programme using LabVIEW software was performed to evaluate the feasibility of the parachute. Meanwhile, the flight test was conducted to investigate the performance and reliability of PRS at different deployment heights. A baseline annular parachute canopy with 2.41 m of the nominal diameter was selected as the main parachute, which produced highest drag coefficient (1.03). The findings also highlighted the significance of separation and recirculating flows behind studied geometries, which in turn was responsible in producing the drag. Through the static drop test, the selected parachute design provided a predicted terminal descent velocity of approximately 4 m/s with payload of 5kg. This parachute recovery system was able to reduce the impact force at fourth time lower compared to belly landing, from 139.77 N to 30.81 N. The pilot-chute was successful pulled main parachute to free stream and fully inflated in a short time, less than 3 seconds. Most of all, the parachute recovery was able to support and bring the aircraft to a soft and safe landing thus, confirmed its reliability. Interestingly, robust evidence in a prediction of the landing position area using PRS was achieved

Aeronautical engineering: A continuing bibliography with indexes (supplement 304)

This bibliography lists 453 reports, articles, and other documents introduced into the NASA scientific and technical information system in May 1994. Subject coverage includes: design, construction and testing of aircraft and aircraft engines; aircraft components, equipment, and systems; ground support systems; and theoretical and applied aspects of aerodynamics and general fluid dynamics

Techniques for effective virtual sensor development and implementation with application to air data systems

1noL'abstract è presente nell'allegato / the abstract is in the attachmentopen716. INGEGNERIA AEROSPAZIALEnoopenBrandl, Albert

Aeronautical engineering: A continuing bibliography with indexes (supplement 293)

This bibliography lists 476 reports, articles, and other documents introduced into the NASA scientific and technical information system in July, 1992. Subject coverage includes: design, construction and testing of aircraft and aircraft engines; aircraft components, equipment, and systems; ground support systems; and theoretical and applied aspects of aerodynamics and general fluid dynamics

Aeronautical engineering: A continuing bibliography with indexes (supplement 292)

This bibliography lists 675 reports, articles, and other documents recently introduced into the NASA scientific and technical information system database. Subject coverage includes the following: design, construction and testing of aircraft and aircraft engines; aircraft components, equipment, and systems; ground support systems; and theoretical and applied aspects of aerodynamics and general fluid dynamics

Aeronautical engineering: A continuing bibliography with indexes (supplement 295)

This bibliography lists 581 reports, articles, and other documents introduced into the NASA Scientific and Technical Information System in Sep. 1993. Subject coverage includes: design, construction and testing of aircraft and aircraft engines; aircraft components, equipment, and systems; ground support systems; and theoretical and applied aspects of aerodynamics and general fluid dynamics

Aeronautical engineering: A continuing bibliography with indexes (supplement 278)

This bibliography lists 414 reports, articles, and other documents introduced into the NASA scientific and technical information system in April 1992