Municipal solid wastes in Tripoli are the residues from the daily consumption of population and made of food residues, yard residues, plastic bags, papers, textile, leather, rubber, wood, tin/aluminum cans, iron, glass, sand/dirt etc. One strategy of Municipal solid waste management is refuse derived fuel (RDF) It is designed to divert combustible fractions from municipal solid wastes (MSW) to produce fuel and then to be used as substitution or supplementary energy. In this regard, RDF utilization can be considered as CDM and conforms to Kyoto Protocol. In this study Dulong formula is used to calculate higher heating value and lower Heating Value of Refuse derived fuel (RDF).The results of HHV and LHV are obtained. The higher heating value, HHV=8.530628MJ/Kg, and the lower heating value, 8.00MJ/Kg respectively for Tripoli Municipal Solid Waste based on data obtained from Sidi Assayeh landfill in 2015.

Abstract Rapid Prototyping of embedded hardware/software systems is important, because it shortens the path from specification to the final product. Prototypes play a major role in decision making, concept and design validation, feature and limit exploration, as well as design verification in every phase of the product development cycle, including product planning, requirement engineering, and product development. Rapid prototyping of embedded systems can emulate different kind of processes, through the mathematical modelling that represent their dynamic characteristics. This make easier to emulate different control strategies, which can interact with the real signals of the embedded process, making a better approach of the real response than a simple simulation. This paper presents the results of the emulation of the dynamic behaviour in the study case to work, in order to validate control strategies like PID and Fuzzy, using the concepts of rapid prototyping and hardware-in-the-loop (HIL). To achieve this objective, two embedded systems were employed, the first one to emulate the dynamics of the process, and the second one to implement the control strategy. Both systems were interconnected using the Controller Area Network protocol (CAN). The principal contribution of this work is the methodological development in the application of the control strategies through HIL 

Abstract The characteristics of non-minimum phase and static unstable of a tail controlled tactical missile are presented firstly. Then, in order to eliminate the static error, a cascade PI compensator was introduced to the classic two loop autopilot. Due to the slow tracking for command acceleration, the longitudinal three-loop autopilot design is driven based on LTI model of missile plant to stabilize the non-minimum phase static unstably missile airframe. The focus is to explain the performance and the control effect at different values of velocity and stability derivative (𝑀𝜶) of two algorithms on missile plant. The analysis is executed by establishing a standard algorithm in virtue of MATLAB/Simulink for autopilot design. The simulation results indicated that three-loop topology gives better tracking than two-loop with a cascade PI compensator at different value of stability derivative 𝑀𝜶. On the other hand, two-loop has a better response and less control effort at different velocities. fin angle and fin angle rate are less than the three loop for static unstable and stable missile. 

Combustion systems are the least amenable of all gas turbine components to analyze. Among the literature overview made, it was realized that even though significant steps have been made in improving the combustor design procedure via the use of computational fluid dynamics, much of the design process still relies upon empirically derived rules. These rules include the calculation procedure of the required airflow rate by each zone of the combustion chamber to attain a suitable gas temperature, high values of combustion efficiency, low concentrations of pollutant species together with the determination of liner geometry that matches the chamber required performance goals with the constraints imposed by the engine dimensions [1,2,3, and 4]. The main target of this research work is to identify the proper procedure to distribute a predetermined airflow rate in annular type combustor and to generalize an effective calculation method that formulate and solve the problems in as much simplified and accurate manner as possible. The combustor dimensions and airflow rates in each zone is found in reference [5] and shown in Figure 1. It is designed with central vaporizing unit to deliver 516.3 KW of power with a geometrical constraint of 142 mm & 140 mm overall length and casing diameter, respectively, while the airflow rate is 0.8 kg/sec and the fuel flow rate is 0.012 kg/sec [5, 6].

Abstract: In this Paper the Hardware-In-the-Loop Simulation (HILS) platform is used to design a flight Control system for Unmanned Aerial Vehicles (UAV). A flight Controllers are designed and validated for lateral and longitudinal axes motion using Matlab/Simulink offline simulations and the designed controllers are embedded To the HILS platform for Real time simulation. It is observed that the resulting controller successfully stabilizes the aircraft to achieve flight Trajectory

Using natural gas as a fuel for internal combustion engine (spark ignition) results in reduction of pollutant emission such as NOx, HC, CO and SOOT if compared with conventional hydrocarbon fuel in addition the high-octane number of natural gas allows an increase of compression ratio in spark ignition engine and consequently improves their efficiency.

In this paper an extension of the model presented by Ferguson [1], is applied using FORTRAN language. A comprehensive performance data is presented for equivalence ratios, compression ratios, and engine speed. The contributions were to develop and validate a computer code simulation for 4-stroke cycle SI engine by using different fuel and compare the results with previous experimental studies. The results of the computer code are in very good agreement with the experimental studies under various conditions.

Experiments showed that a compression ratio of 12:1 is a reasonable value for a compressed-natural-gas direct-injection engine to obtain a better thermal efficiency without a large penalty of emissions.

The main objective of the paper is to analyze the performance of axial flow compressors and to generate a systematic design approach which enables to design subsonic flow ones. In order to investigate the validity of this approach, the LP axial flow compressor of the RR Spey MK511 turbofan engine is taken as an example. The design calculations were based on thermodynamics, gas dynamics, fluid mechanics and empirical relations. The flow is assumed to be of two-dimensional compressible type with constant axial and rotor blade velocities with a free-vortex swirl distribution. Design calculations include

thermodynamic properties of the working fluid, number of compressor performance parameters such as, stage temperature rise and number, flow and blade angles (blade twist), velocity triangles and relative inlet Mach number at rotor blades tips as well as blades tip and hub diameters. A repeated calculation is made to determine these parameters along compressor stages. The variation of velocity whirl components, air and blade angles, deflection and degree of reaction from root to tip of the blades were also determined. The twist of the blades along the blade length is set according to the recommended values in order to obtain smooth blade twist profile.

The importance of flow measurement in the industry has grown in the past 50 year, not just because it was widespread use for accounting purposes, such as custody transfer of fluid from supplier to customers, but also because of its application in manufacturing processes [1,2, and 3], Examples of the industrial involvement in flow measurement includes food and beverage, oil and gas industry, medical, petrochemical, power generation and water distribution, etc. In the research laboratory, advanced flow measurements are providing new insights into a wide range of engineering flow problems in hydrodynamics such as wave impact loading on coastal defenses, beach erosion) combustion such as low Nox burners in IC engines, aerodynamics such as wind turbine optimization and performance prediction) to list but a few [4,5], The aim of this work is to generate an awareness and understanding of the range of contemporary flow measurement techniques available with the emphasis on devices and techniques with wide application in engineering. Focus is devoted to cheap meters with reasonable accuracy; the differential pressure flow meters that all infer the flow rate from a pressure drop across a restriction in the pipe. An orifice plate meter is designed to measure the required flow rate to cool a nuclear reactor at design point is 20 Kg/sec. Meter operation at off design conditions; 5 and 30 Kg/sec minimum and maximum flow rates with maximum allowable orifice pressure drop of 200 KPa were investigated and finalizes the design process.

The objectives of this study (baseline study, n = 20) were to implement Matlab procedures for quantifying selected static balance variables, establish baseline data of selected variables which characterize static balance activities in a population of healthy young adult males, and to examine any trial effects on these variables. The results indicated that the implementation of Matlab procedures for quantifying selected static balance variables was practical and enabled baseline data to be established for selected variables. There was no significant trial effect. Recommendations were made for suitable tests to be used in later studies. Specifically it was found that one foot-tiptoes tests either in static balance is too challenging for most participants in normal circumstances. A one foot-flat eyes open test was considered to be representative and challenging for static balance.

Abstract—this work reports on a high speed flexible automation system based on Cartesian multi-axis coordinate system linear step motor developed, in the target application as a multi-use robot system. The task of this work is to constructs an interactive multimedia page for study and researches the principle’s work of drive of direct action linear step motor, Development the mathematical model and implementation of a closed loop control, based MATLAB/SIMULINK, Study the static and dynamic characteristics of the motor movement which is restricted to the trajectories accessible through the given commands.