Paramotor Trike Design and Analysis

A paramotor trike refers to an ultralight aircraft that is attached to a paraglider. A trike with a rear-mounted engine provides thrust force, enabling the vehicle to take off. The main objective of this study is to develop the modelling simulation of a two-seater paramotor trike and analyze the stresses acting on the frame structure of the paramotor trike through static and drop test simulations. In this study, the paramotor trike conceptual design is developed using SolidWorks. The safety factor for the static test and drop test is satisfactory based on the deformation, strain, and stress results. Moreover, the paramotor trike that was developed achieved its lightweight goal of 99 kg with an ergonomic design and has a maximum takeoff weight of 246 kg

Analysis of Case Records of Foetal Deaths in Livestock in Serdang, Selangor

Cases of foetal death in the necropsy records of the Faculty of Veterinary Medicine and Animal Science, Universiti Pertanian Malaysia over a 5-year period (1977 -1981) were analysed. Of 119 foetal deaths, 49.0% were abortions, 41.0% stillbirths and 10.0% premature non-viable births. Most of the cases, particularly abortions, (96.5%) remained undiagnosed. There was a remarkable absence of foetal deaths due to infectious diseases

Design proposal of the energy installation system for vehicle’s wind turbine

New inventions is relating to the idea of mounting a wind turbine for power generating system in vehicles. This study will investigate on the existing energy conversion and storage systems used in standard vehicle’s power system.This study involves with a proposed design of a vehicle’s wind turbine system. The energy that has been generated by wind turbine will be stored in the 12 volt battery and will then, be distributed to the entire vehicle for the use of the vehicle components. The optimal design for energy conversion system is created based on the review of the existing energy conversion and storage systems which are used in vehicle’s power system. A simulation study using NI Multisim (National Instrument Software) is conducted on the energy conversion and storage system that. The objectives of this study are to convert a mechanical energy from the blade to electrical energy to generate 12V voltage and to store it in a 12 volt battery. The 12V battery voltage will then be supplied to a high voltage system, up to 200V voltage capacity. From the analysis that has been done, the energy from a turbine has the potential to generate power to car system. The wind energy is possible to integrate with other existing and renewable energy. At this stage, the energy gained does not replace the existing one but it can be considered as a new energy source in the future energy developmen

Comparative study of turbulent incompressible flow past naca airfoils

The flow past the airfoils is continuously investigated in various experimental and computational aerodynamic perspectives. In this paper, a comparative study on the aerodynamic characteristics of the turbulent incompressible flow past four NACA airfoils is emphasized. Particularly, we classify these characteristics based on the basic geometries, namely symmetric and asymmetric airfoils, as well as trailing edge angles. The results confirm the general aerodynamic theory and include finding on the effect of sharp trailing edge, which complement the available airfoil datasets for improving their designs and as reference cases

Design of power device sizing and integration for solar-powered aircraft application

The power device constitutes the PV cell, rechargeable battery, and maximum power point tracker. Solar aircraft lack proper power device sizing to provide adequate energy to sustain low and high altitude and long endurance flight. This paper conducts the power device sizing and integration for solar-powered aircraft applications (Unmanned Aerial Vehicle). The solar radiation model, the aerodynamic model, the energy and mass balance model, and the adopted aircraft configuration were used to determine the power device sizing, integration, and application. The input variables were aircraft mass 3 kg, wingspan 3.2 m, chord 0.3 m, aspect ratio 11.25, solar radiation 825 W/m2 , lift coefficient 0.913, total drag coefficient 0.047, day time 12 hour, night time 12 hours, respectively. The input variables were incorporated into the MS Excel program to determine the output variables. The output variables are; the power required 10.92 W, the total electrical power 19.47 W, the total electrical energy 465.5 Wh, the daily solar energy 578.33 Wh, the solar cell area 0.62 m, the number of PV cell 32, and the number of the Rechargeable battery 74 respectively. The power device was developed with the PV cell Maxeon Gen III for high efficiency, the rechargeable battery sulfur-lithium battery for high energy density, and the Maximum power point tracker neural network algorithm for smart and efficient response. The PD sizing was validated with three existing designs. The validation results show that 20% reduction of the required number of PV cells and RB and a 30% increase in flight durations

Experimental respiratory infection of goats with Mycoplasma arginini and Pasteurella haemolytica A2

Twenty-one healthy local goats of about eight months old were divided into four groups consisting of six animals in groups 1, 2 and 3 and three animals in group 4. Goats in groups 1 and 2 were inoculated intratracheally with Mycoplasma arginini. Goats in group 2 were inoculated again with Pasteurella haemolytica A2 six days later. Goats in group 3 were inoculated intratracheally with P. haemolytica A2 alone while goats in group 4 received intratracheal inoculation ofPBS. The goats were euthanised at day 1, 3 and 7 post inoculation with P. haemolytica. Four goats in group 1 and three goats in group 3 had small patches of mild pneumonic lesions. Goats in group 2 had severe lung lesions typical of pneumonic pasteurellosis at the anteroventral region of the lungs. None of the goats in group 4 had pulmonary lesions. P. haemolytica was reisolated from all goats in group 2 and from three goats in group 3 but M. arginini was not reisolated

Development of low liquid fuel Burnera

Recently, most of the gas turbine combustion research and development involves in lowering the emissions emitted from the combustor. Emission causes adverse affect to the world and mankind especially. Main concern of the present work is to reduce the NOx emission since the CO emission could be reduced through homogeneous mixing of fuel and air. Homogeneous mixing of fuel and air is also needed in order to reduce NOx emission. A liquid fuel burner system with radial air swirler vane angle of 30o, 40o, 50o and 60o has been investigated using 163mm inside diameter combustor. Orifice plates with three different sizes of 20mm, 25mm and 30mm were inserted at the back plate of swirler outlet. All tests were conducted using diesel as fuel. Fuel was injected at two different positions, i.e. at upstream and downstream of the swirler outlet using central fuel injector with single fuel nozzle pointing axially outwards. Experiment has been carried out to compare the three emissions NOx, CO and SO2. NOx reduction of about 53 percent was achieved for orifice plate of 20mm with downstream injection compared to orifice plate of 20mm with upstream injection. CO2 and SO2 was reduced about 26 percent and 56 percent respectively for the same configuration. This comparison was taken using swirler vane angle of 60o. The overall study shows that larger swirler vane angle produces lower emission results compared to the smaller ones. Smaller orifice plates produce better emission reduction. Meanwhile, downstream injection position significantly decreases the emission levels compared to upstream injection position. Combination of smallest orifice plate and largest swirler vane angle with downstream injection produce widest and shortest flame length

Stress Investigation of Aluminium Alloy and Composite Material for Unmanned Aerial Vehicle Application via Simulation Analysis

Composite material offers excellent properties such as lightweight, high strength to weight ratios, and excellent corrosion resistance. Universiti Tun Hussein Onn Malaysia successfully developed a Cargo Drone (C-Drone) using aluminium alloy as its structure. The future enhancement is looking at the potential of composite material for C-Drone application. Therefore, this research aims to study the stress properties of aluminium alloy and glass fibre composite for C-Drone application via simulation analysis. The scope of this study focuses on the landing gear part of the C-Drone. The drawing of C-Drone was analysed through SolidWorks software to obtain the result of the material reacting to stress, strain, and displacement. The result shows that glass fibre with brittle properties can withstand a high amount of stress, acceptable strain rate, acceptable deformation and reduced weight up to 10% compared to aluminium alloy. This research proves that composite material such as glass fibre reinforced plastic can become an alternative to the current aluminium alloy 6061-T6