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This paper concentrates on explaining the design and engineering aspects of making a Go Kart for Students Kart Design. This report explains objectives, assumptions and calculations made in designing of Go Kart. The primary objective is to design a safe and functional vehicle based on rigid and torsion-free frame. Well mounted power train and to understand the finer aspects of vehicle design with the ulterior motive of fabricating prototype vehicle, while strictly adhering to the safe drive. The secondary objective is to enhance driver’s comfort and safety, and to increase the performance and the manoeuvrability of the vehicle. [ABSTRACT FROM AUTHOR]

The selected variants of strengthening the construction of a military vehicle subjected to the effects of the wave of pressure coming from an explosion have been analyzed in the article. The paper includes the validation process of a numerical model based on the results of experimental tests of a real object, carried out on the testing ground. As a result of the conducted numerical analyses, the characteristics of the selected impact factors in the explosive wave-vehicle-dummy scheme have been presented. In order to assess the influence of strengthening the construction, the selected biomechanical factors, such as the acceleration of the dummy’s head, and mechanical factors, such as the acceleration of the vehicle’s wall, have been chosen. [ABSTRACT FROM AUTHOR]

This article is devoted to an interplanetary movement and design restrictions of the solar sail spacecraft. Authors propose to use locally-optimal control laws to obtain the dynamic scheme of the interplanetary flight to Mercury and finite-element model of the solar sail for modeling the behavior of construction. Model of the spherical type solar sail spacecraft is designed by postgraduate students of Samara National Research University. The temperature of the solar sail surface should not exceed the maximum permissible values. [ABSTRACT FROM AUTHOR]

Currently, various countries are working to create a prospective manned reentry space vehicle of a new generation. The development of a new manned reentry space vehicle is conditioned by the necessity to increase the number of crew members, increase the carrying capacity, and improve the accuracy of landing at a given point on the earth's surface. The listed requirements for the appearance of the prospective reentry space ship and the increase in its dimensions lead to an increase in its cost, which entails the expediency of its reusability. This imposes additional conditions on the design of the spacecraft. The braking of the reentry vehicle is carried out by aerodynamic braking in the atmosphere upper layers, the parachutes usage and the use of a multi-jet braking system near the landing surface. With this braking method, the task is to effectively control the braking jet propulsion system at landing regimes [1]. [ABSTRACT FROM AUTHOR]

This research discusses about the manufacturing method of electric sports car's body. The contents of this study include literatures, research methods, and results. Focus of this research is on the technique of manufacturing electric sports car's body by spraying the body frame that has been coated with elastic fabric. Two types of fabrics will be used in this study namely lycra and oscar. Mold ring is used as a body frame and the elastic fabric to form the surface is then sprayed by resin to make it harder. After the elastic fabric hardened then fiberglass will be added to strengthen the material. Then tensile test and stress analysis are perfomed to find out the strength and suitability of material. From the test obtained that oscar fabric specimen has better strength than lycra fabric specimen with tensile stress 5 [49] Kg/mm2 [MPa], 2.26% elongation, and von misses 5.147e+007 N/m2 while lycra fabric with 4 [39] Kg/mm2 [MPa] for tensile stress, 2.24% elongation, and von misses 4.083e+007 N/m². According to the experiment it can be conluded that this method only needs the cost around IDR 902,500.00 with easier and even faster for a car body manufacturing process. [ABSTRACT FROM AUTHOR]

Fuel vehicles have at least 3 (three) disadvantages: low efficiency, generating exhaust emissions, and using non-renewable energy. So in some developed countries, electric vehicles began to operate as an alternative solution, because it is very efficient and without emissions. However, electric vehicles have constraints in charging the battery that takes a very long time. Therefore, the technology needed to reduce fuel consumption without reducing the performance of the vehicle. Appropriate technology to overcome this is a hybrid drive system, a combination of power sources on fuel and electric motors, which is currently applied to four-wheeled vehicles. As for motorcycles, hybrid technology has not been much. The design of a motorcycle with a propulsion system in the form of multi-mode hybrid is possible through the configuration of 3 types of power source that is one unit of fuel and two units of BLDC electric motor. Both BLDC electric motors can operate as traction motors and electric generators to charge the battery. To enable the multi-mode hybrid system to function, the planetary gear will be the connecting force of the fuel engine, electric motor # 1 and electric motor # 2. Hybrid multi-mode pattern designed is electric mode will be operated when the work cycle of the vehicle is in low to medium rotation, if the rotation of the vehicle reaches the mid-rotation until high speed then hybrid mode (parallel, parallel and series, and series) will be operated. [ABSTRACT FROM AUTHOR]

GESITS is an Indonesia electric scooter with design and manufacture in Institute of Technology Sepuluh Nopember (ITS) Surabaya, Indonesia. It is the first electric scooter in Indonesia that developed by a group of Indonesian engineers and business people that banded together to deliver the product to the market. One of the key to the successful implementation of e-scooter is the water resistance performance test of the escooter. In order to accomplish the protection, it is important to conduct the water ingress test based on Standard IPX5. In this paper explains the water resistance performance test for GESITS and then discuss some results. In accordance with the test procedure to evaluate IPX5 protection against ingress of water, the water resistance shall be carried out by spraying with a stream of fresh water the enclosure from all practicable directions with a standard test nozzle. The results showed that after finished the test and analyzing both the battery compartment and the controller compartment, it was determined that GESITS passes Ingress Protection and meets the engineering requirements. No water was observed inside the compartment during the visual inspection performed after the IPX5 exposure. Thus the degree of protection against water corresponds to IPX5 for GESITS. A visual inspection conducted upon completion of the exposure period also found no visible evidence of damage or degradation. It can be concluded that the result comply with the requirements since there wasn't any water that entered the enclosure. [ABSTRACT FROM AUTHOR]

Along with the steady evolution of the automotive industry, the concern for developing crash-safety technologies has always been one of the major concerns within the design of a vehicle. The understanding of the response of materials to impact is a traditional but ongoing subject of investigation worldwide, powered by the challenges imposed by novel and progressively complex materials such as fiber reinforced composite plastics, with the intrinsic failure mechanisms characteristic of the combination among each matrix and reinforcement selected. Acknowledging the current importance of numerical simulations in this study, the present work aims at providing a brief summary of basic notions for which regards impact explicit numerical simulations on composite materials, particularly considering two-dimensional ‘shell’ finite elements. [ABSTRACT FROM AUTHOR]

In order to maintain the operational continuity of air defense systems, unmanned autonomous or remotely controlled unmanned aerial vehicle (UAV) plays a great role as a target for the anti-aircraft weapons. The aerial vehicle must comply with the requirements of high speed, remotely controlled tracking and navigational aids, operational sustainability and sufficient loiter time. It can also be used for aerial reconnaissance, ground surveillance and other intelligence operations. This paper aims to develop a complete tail design of an unmanned aerial vehicle using Systems Engineering approach. The design fulfils the requirements of longitudinal and directional trim, stability and control provided by the horizontal and vertical tail. Tail control surfaces are designed to provide sufficient control of the aircraft in critical conditions. Design parameters obtained from wing design are utilized in the tail design process as required. Through chronological calculations and successive iterations, optimum values of 26 tail design parameters are determined. [ABSTRACT FROM AUTHOR]

Following the UN Climate Change Conference 2009 in Copenhagen, Denmark, Malaysia seriously committed on "Go Green" campaign with the aim to reduce 40% GHG emission by the year 2020. Therefore, the National Green Technology Policy has been legalised in 2009 with transportation as one of its focused sectors, which include hybrid (HEVs), electric vehicles (EVs) and fuel cell vehicles with the purpose of to keep up with the worst scenario. While the number of registered cars has been increasing by 1 million yearly, the amount has doubled in the last two decades. Consequently, CO2 emission in Malaysia reaches up to 97.1% and will continue to increase mainly due to the activities in the transportation sector. Nevertheless, Malaysia is now moving towards on green car which battery-based EVs. This type of transportation mainly needs power performance optimization, which is controlled by the Batteries Management System (BMS). BMS is an essential module which leads to reliable power management, optimal power performance and safe vehicle that lead back for power optimization in EVs. Thus, this paper proposes power performance optimization for various setups of lithium-ion cathode with graphene anode using MATLAB/SIMULINK software for better management performance and extended EVs driving range. [ABSTRACT FROM AUTHOR]

Impact damage is one of the major concerns that should be taken into account with the new aircraft and spacecraft structures which employ ever-growing use of composite materials. Considering the thermal loads encountered at different altitudes, both low and high temperatures can affect the properties and impact behavior of composite materials. This study aims to investigate the effect of temperature and impactor diameter on the impact behavior and damage development in balanced and symmetrical CFRP laminates which were manufactured by employing vacuum bagging process with autoclave cure. Instrumented drop-weight impact testing system is used to perform the low velocity impact tests in a range of temperatures ranged from 60 down to -50 °C. Impact tests for each temperature level were conducted using three different hemispherical impactor diameters varying from 10 to 20 mm. Energy profile method is employed to determine the impact threshold energies for damage evolution. The level of impact damage is determined from the dent depth on the impacted face and delamination damage detected using ultrasonic C-Scan technique. Test results reveal that the threshold of penetration energy, main failure force and delamination area increase with impactor diameter at all temperature levels. No clear influence of temperature on the critical force thresholds could be derived. However, penetration threshold energy decreased as the temperature was lowered. Drop in the penetration threshold was more obvious with quite low temperatures. Delamination damage area increased while the temperature decreased from +60 °C to -50 °C. [ABSTRACT FROM AUTHOR]

The developed method of iterative optimization of interplanetary missions with the low thrust, using sequence of movement specified mathematical models and design shape spacecraft, is realized. The new articular analytical decision describing planar movement of spacecraft with solar electric propulsion is described, allowing to construct initial approach in the iterative scheme of optimization. Developed a method of modelling and optimization of interplanetary missions ballistic schemes, based on a combination of Pontryagin's maximum principle formalism conditions of transversality and methods of the mathematical programming, allowing to consider restrictions characteristic for concrete interplanetary missions. Recommendations for choice design-ballistic parameters of the interplanetary missions spacecraft, received taking into account features nuclear and solar power plant for missions on delivery of a payload to orbits of Mars, expeditions the Earth-Mars-Earth are received. [ABSTRACT FROM AUTHOR]

Flight mechanics with a low-thrust is a new chapter of mechanics of space flight, considered plurality of all problems trajectory optimization and movement control laws and the design parameters of spacecraft. Thus tasks associated with taking into account the additional factors in mathematical models of the motion of spacecraft becomes increasingly important, as well as additional restrictions on the possibilities of the thrust vector control. The complication of the mathematical models of controlled motion leads to difficulties in solving optimization problems. Author proposed methods of finding approximate optimal control and evaluating their optimality based on analytical solutions. These methods are based on the principle of extending the class of admissible states and controls and sufficient conditions for the absolute minimum. Developed procedures of the estimation enabling to determine how close to the optimal founded solution, and indicate ways to improve them. Authors describes procedures of estimate for approximately optimal control laws for space flight mechanics problems, in particular for optimization flight low-thrust between the circular non-coplanar orbits, optimization the control angle and trajectory movement of the spacecraft during interorbital flights, optimization flights with low-thrust between arbitrary elliptical orbits Earth satellites. [ABSTRACT FROM AUTHOR]

In this paper discussed camouflage design helmet for armored vehicles with comparing head measurement of Indonesian anthropometric. Design process conduct with considering of design aspects involves function, materials, operational, technology, user, and appearance (camouflage). As an application of Indonesian National Army that qualifies factors needs: safety, comfort, practical and service. MIL-H-44099A Military Specification : Helmet, Ground Troops And Parachutists is minimum limitation standard of military helmet production. Head measurement for product design process guide is presented. Model simulation and helmet measurement using the design for ego and design for more types ergonomics concept. Appearance shape concept is engaging camouflage towards background and environment to deceive enemy viewpoint. Helmet prototype has tested ergonomically to an Indonesian National Army soldier and stated that the helmet size is a comfort and fitted on the head when in use. [ABSTRACT FROM AUTHOR]

The thermal comfort in passenger cabins needs an automotive air-conditioning system. The electric vehicle air conditioner system is driven by an electric compressor which includes a compressor and an electric motor. Almost airconditioning system uses CFC-12, CFC-22 and HFC-134a as refrigerant. However, CFC-12 and CFC-22 will damage the ozone layer. The extreme huge global warming potentials (GWP) values of CFC-12, CFC-22, and HFC-134a represent the serious greenhouse effect of Earth. This article shows new experimental measurements and analysis by using a mixture of HC-134 to replace HFC-134a. The result is a refrigerating effect, the coefficient of performance and energy factor increase along with cooling capacity, both for HFC-134a and HC-134. The refrigerating effect of HC-134 is almost twice higher than HFC-134a. The coefficient of performance value of HC-134 is also 36.42% greater than HFC-134a. Then, the energy factor value of HC-134 is 3.78% greater than HFC-134a. [ABSTRACT FROM AUTHOR]

In this study, range extender engine designed should be able to meet the power needs of a power generator of hybrid electrical vehicle that has a minimum of 18 kW. Using this baseline model, the following range extenders will be compared between conventional SI piston engine (Baseline, BsL), engine capacity 1998 cm3, and efficiency-oriented SI piston with engine capacity 999 cm3 and 499 cm3 with 86 mm bore and stroke square gasoline engine in the performance, emission prediction of range extender engine, standard of charge by using engine and vehicle simulation software tools. In AVL Boost simulation software, range extender engine simulated from 1000 to 6000 rpm engine loads. The highest peak engine power brake reached up to 38 kW at 4500 rpm. On the other hand the highest torque achieved in 100 Nm at 3500 rpm. After that using AVL cruise simulation software, the model of range extended electric vehicle in series configuration with main components such as internal combustion engine, generator, electric motor, battery and the arthemis model rural road cycle was used to simulate the vehicle model. The simulation results show that engine with engine capacity 999 cm3 reported the economical performances of the engine and the emission and the control of engine cycle parameters. [ABSTRACT FROM AUTHOR]

Vehicle dynamics plant phenomena during acceleration, deceleration and curve turning in uncertainty ground road is very complexity and nonlinearity model. No integrated chassis control by various systems have been proposed to control vehicle behavior by distributing front-rear and left-right braking/ABS & driving/TCS forces, adjusting rear-wheel steering angle/4WS. ABS and TCS can reduce the slip and skid factor that improve the braking and driving performance but cannot eliminate the vehicle sideslip (VSS). In other side four wheel steering (4WS) have good performance in reducing of vehicle sideslip to improve maneuver ability but fail in decreasing of stopping distance (SD) and increasing driving performance (DP). In this research, to solve the previous problem, author purpose an integrated ABS-TCS-4WS control using mamdani-fuzzy logic. Input and output variable are described. Steering maneuver, slope of the road, vehicle mass (number of passenger) are the input variables, while error of wheel slip factor, error of skid factor and error of vehicle sideslip are output variables. In this research, parameter for reference, wheel slip and skid factor are setup to 20% and vehicle sideslip to be zero degree. 22 rules was setup to produce the best mamdani fuzzy in adapting the nonlinearity of the vehicle dynamics. Result of the research shown, that error of wheel slip factor was 3.2%, error of skid factor was 2.8% and error of vehicle side slip was 4.2 degree. [ABSTRACT FROM AUTHOR]

In space, environmental torques exerts continuously on a satellite and may influence and affect the satellite's attitude dynamics. The relative strength of the various torques will depend on both spacecraft environment and the structure of the spacecraft itself. RazakSAT is the world first remote sensing satellite launched into Near Equatorial Orbit (NEqO). Hence, the objective of this paper is to study the properties and behaviour of disturbance torque that perturb RazakSAT's attitude during orbiting in NEqO in sun tracking mode using in-flight attitude data. The results show that the environmental torques exerted on RazakSAT during sun tracking mode is periodic and the magnitude of the torques vary from 10-4 to 10-7. Understanding the behaviour of disturbance torque can be utilized in spacecraft design to improve the satellite's performance for future mission. [ABSTRACT FROM AUTHOR]

An Unmanned Aerial Vehicle was designed, analyzed and fabricated to meet design requirements and perform the entire mission for an international aircraft design competition. The goal was to have a balanced design possessing, good demonstrated flight handling qualities, practical and affordable manufacturing requirements while providing a high vehicle performance. The UAV had to complete total three missions named ferry flight (1st mission), maximum load mission (2nd mission) and emergency medical mission (3rd mission). The requirement of ferry flight mission was to fly as many as laps as possible within 4 minutes. The maximum load mission consists of flying 3 laps while carrying two wooden blocks which simulate cargo. The requirement of emergency medical mission was complete 3 laps as soon as possible while carrying two attendances and two patients. A careful analysis revealed lowest rated aircraft cost (RAC) as the primary design objective. So, the challenge was to build an aircraft with minimum RAC that can fly fast, fly with maximum payload, and fly fast with all the possible configurations. The aircraft design was reached by first generating numerous design concepts capable of completing the mission requirements. In conceptual design phase, Figure of Merit (FOM) analysis was carried out to select initial aircraft configuration, propulsion, empennage and landing gear. After completion of the conceptual design, preliminary design was carried out. The preliminary design iterations had a low wing loading, high lift coefficient, and a high thrust to weight ratio. To make the aircraft capable of Rough Field Taxi; springs were added in the landing gears for absorbing shock. An airfoil shaped fuselage was designed to allowed sufficient space for payload and generate less drag to make the aircraft fly fast. The final design was a high wing monoplane with conventional tail, single tractor propulsion system and a tail dragger landing gear. Payload was stored in undercarriage box for maximum load mission and emergency medical mission. The aircraft structure, weights 5.6 lb., constructed by balsa wood, depron and covering film was the only feasible match for the given requirements set by the competition organizers. The defined final aircraft was capable of: Completing 3 laps within 4 minutes at the first mission; flying 3 laps with 4 internal payloads at the second mission; flying 3 laps with all possible payload configurations at the third mission. [ABSTRACT FROM AUTHOR]

Today, the interior noise perceived by occupants is becoming an important factor driving design standards for the design of most of interior assemblies in an automotive vehicles. BSR(Buzz, Squeak and Rattle) is a major contributor towards the perceived noise of annoyance to vehicle occupants. One method of minimizing the possibility of squeak and rattle is by making use of the judicious selection of mating materials pairs. In this paper, the BSR test system was designed and built. Also described is a test instrument that has been developed for such material pair compatibility studies. [ABSTRACT FROM AUTHOR]

Long endurance flight, on the order of days, is a leading flight performance characteristic for Unmanned Aerial Vehicles (UAVs). Liquid hydrogen (LH2) is well suited to providing multi-day flight times with a specific energy 2.8 times that of conventional kerosene based fuels. However, no such system of LH2 storage, delivery, and use is currently available for commercial UAVs. In this paper, we develop a light weight LH2 dewar for integration and testing in the proton exchange membrane (PEM) fuel cell powered, student designed and constructed, Genii UAV. The fuel tank design is general for scaling to suit various UAV platforms. A cylindrical vacuum-jacketed design with removable end caps was chosen to incorporate various fuel level gauging, pressurizing, and slosh mitigation systems. Heat and mechanical loadings were modeled to compare with experimental results. Mass performance of the fuel tank is characterized by the fraction of liquid hydrogen to full tank mass, and the insulation performance was characterized by effective thermal conductivity and boil-off rate. [ABSTRACT FROM AUTHOR]

Realistic duty cycles are critical for design and assessment of hybrid propulsion systems, in particular, plug-in hybrid electric vehicles. The analysis of the PHEV impact requires a large amount of data about daily missions for ensuring realism in predicted temporal loads on the grid. This paper presents two approaches for the reduction of the computational effort while assessing the large scale PHEV impact on the grid, namely 1) "response surface modelling" approach; and 2) "daily driving schedule modelling" approach. The response surface modelling approach replaces the time-consuming vehicle simulations by response surfaces constructed off-line with the consideration of the real-world driving. The daily driving modelling approach establishes a correlation between departure and arrival times, and it predicts representative driving patterns with a significantly reduced number of simulation cases. In both cases, representative synthetic driving cycles are used to capture the naturalistic driving characteristics for a given trip length. The proposed approaches enable construction of 24-hour missions, assessments of charging requirements at the time of plugging-in, and temporal distributions of the load on the grid with high computational efficiency. [ABSTRACT FROM AUTHOR]

Metallic pressure tanks used in space missions are inherently vulnerable to hypervelocity impacts from micrometeoroids and orbital debris; thereby knowledge of impact damage and its effect on the tank integrity is crucial to a spacecraft risk assessment. This paper describes tests that have been performed to assess the effects of hypervelocity impact (HVI) damage on Titanium alloy (Ti-6Al-4V) pressure vessels burst pressure and characteristics. The tests consisted of a pair of HVI impact tests on water-filled Ti-6Al-4V tanks (water being used as a surrogate to the actual propellant) and subsequent burst tests as well as a burst test on an undamaged control tank. The tanks were placed behind Aluminum (Al) shields and then each was impacted with a 7 km/s projectile. The resulting impact debris plumes partially penetrated the Ti-6Al-4V tank surfaces resulting in a distribution of craters. During the burst tests, the tank that failed at a lower burst pressure did appear to have the failure initiating at a crater site with observed spall cracks. A fracture mechanics analysis showed that the tanks failure at the impact location may have been due to a spall crack that formed upon impact of a fragmentation on the Titanium surface. This result was corroborated with a finite element analysis from calculated Von-Mises and hoop stresses. [ABSTRACT FROM AUTHOR]

The most suitable method to compute aerodynamic forces of a spacecraft, at first stage of a design, relies on bridging formulae. There are two kinds of bridging formulae: global and local. The global formulae rely on knowledge of spacecraft aerodynamic force coefficients in continuum and in free molecular flow. The local formulae calculate the skin friction and pressure coefficients on the body surface; the global aerodynamic coefficients are then computed by integration. The aim of this work is to analyze the widely accepted local formulae by Potter and by Kotov. To this purpose, a simple body, like a sphere, has been preliminary considered and the results have been compared with those from the DSMC code DS2V. This comparison led to the corrections of the computation of the skin friction and pressure coefficients. These corrections have been applied to the Potter formula. On the other hand the original Kotov formula showed good results for the pressure coefficient at high altitudes. Therefore a merge of the corrected Potter formula and of the Kotov formula has been made. This methodology, called 'new' bridging formula, has been successfully applied to sphere. The 'new' formula has been also applied to EXPERT and ORION capsules, but it has to be pointed out that, in this application at low altitudes, a failure of the panel method starts to appear. Both local and global coefficients have been compared with the results by the DS2/3V codes. Finally, for these capsules, the global formula by Wilmoth has been also used by tuning the adjustable parameters. [ABSTRACT FROM AUTHOR]

In the development of aerospace technology the design of space vehicles is important in phase of reentry flight. The space vehicles reenter into the atmosphere with range of 6-8 km/s. The non-equilibrium flow with radiative heating from strongly shocked air ahead of the vehicles plays an important role on the heat flux to the wall surface structure as well as convective heating. The experimental data for re-entry analyses, however, have remained in classical level. Recent development of optical instruments enables us to have novel approach of diagnostics to the re-entry problems. We employ the CARS (Coherent Anti-Stokes Raman Spectroscopy) method for measurement of real gas temperatures of N2 with radiation of the strong shock wave. The CARS signal can be acquired even in the strong radiation area behind the strong shock waves. In addition, we try to use the CCD camera to obtain 2D images of total radiation simultaneously. The strong shock wave in front of the reentering space vehicles is experimentally realigned by free-piston, double-diaphragm shock tube with low density test gas. [ABSTRACT FROM AUTHOR]

Statistical BGK/DSMC and continuum N-S simulations of a typical vehicle reentry flow were performed taking into account local flow features. The local surface features were known to cause problems during the Apollo era Earth atmosphere reentry Ref. [1] and therefore require close attention as the shapes and design details of the new reentry vehicles tend to build on the Apollo reentry capsules. The TPS thermal response to the high energy reentry flow in cracks and compression pad areas is important to understand to predict the TPS degradation due to the chemical and thermal ablation. The TPS study presented in this article includes the stagnation area micro crack and compression pads which disturb the flow and cause local augmentation of heat flux, which in turn, results in higher recession rates. [ABSTRACT FROM AUTHOR]

This research presents a development of a design of experiment technique for quality improvement in automotive manufacturing industrial. The quality of interest is the colour shade, one of the key feature and exterior appearance for the vehicles. With low percentage of first time quality, the manufacturer has spent a lot of cost for repaired works as well as the longer production time. To permanently dissolve such problem, the precisely spraying condition should be optimized. Therefore, this work will apply the full factorial design, the multiple regression, the constrained response surface optimization methods or CRSOM, and Taguchi's method to investigate the significant factors and to determine the optimum factor level in order to improve the quality of paint shop. Firstly, 2κ full factorial was employed to study the effect of five factors including the paint flow rate at robot setting, the paint levelling agent, the paint pigment, the additive slow solvent, and non volatile solid at spraying of atomizing spraying machine. The response values of colour shade at 15 and 45 degrees were measured using spectrophotometer. Then the regression models of colour shade at both degrees were developed from the significant factors affecting each response. Consequently, both regression models were placed into the form of linear programming to maximize the colour shade subjected to 3 main factors including the pigment, the additive solvent and the flow rate. Finally, Taguchi's method was applied to determine the proper level of key variable factors to achieve the mean value target of colour shade. The factor of non volatile solid was found to be one more additional factor at this stage. Consequently, the proper level of all factors from both experiment design methods were used to set a confirmation experiment. It was found that the colour shades, both visual at 15 and 45 angel of measurement degrees of spectrophotometer, were nearly closed to the target and the defective at quality gate was also reduced from 0.35 WDPV to 0.10 WDPV. This reveals that the objective of this research is met and this procedure can be used as quality improvement guidance for paint shop of automotive vehicle. [ABSTRACT FROM AUTHOR]

We discuss the requirements for developing a lightweight laser-powered space engine with specific impulse range 200

At STAIF-2006, the author presented research into the Mach-Effect and its spin-off, the Mach-Lorentz Thruster (MLT); both of which were created by Woodward. Herein, these MLTs are assessed to see how they could impact the transportation industry if the MLT’s force output scales as predicted by Woodward. These MLT force scaling rules, which are that the MLT output force varies with the cube of the cap voltage and operating frequency but linearly with the B-field, provide a viable path to increasing the MLT’s current specific thrust of ∼1×10-5 Newton per Watt (N/W) up to ∼1.0 N/W, but to do so these MLTs have to overcome their already evident material and control technology issues. However, a preliminary MLT powered spacecraft design demonstrates the enhanced performance capabilities of such a vehicle assuming the availability of 100 Watt/kg electrical power supplies, while illuminating some of the MLT design difficulties as well. This 26.5 metric tonne MLT powered spacecraft points to new capabilities such as traveling from the surface of the Earth to the surface of the Moon using only electrical fuel cell and battery derived energy. Roundtrip times for such an Earth-Moon-Earth journey, carrying a crew of two with a 2-metric tonne payload both ways, could be under 12-hours without refueling; assuming 0.50-to-1.50 Earth-g’s continuous accelerations and decelerations for the various flight segments. If perfected, this MLT propulsion technology could also power land, sea and air vehicles back on Earth. © 2007 American Institute of Physics [ABSTRACT FROM AUTHOR]

With data analysis preparations for LISA underway, there has been renewed interest in studying solar, cosmic ray and environmental physics for, and using LISA. The motivation for these studies is two fold. The primary incentive is to predict and consequently minimize the impact of disturbances associated with these factors, to maximize LISA’s gravitational wave scientific yield. The second stimulus is the unique opportunity that is afforded by LISA’s long-baseline 3-spacecraft configuration for studies of solar, cosmic ray and environmental physics. Here we present an overview of recent progress in these studies. © 2006 American Institute of Physics [ABSTRACT FROM AUTHOR]

Aim of the LISA Test-flight Package on board the LISA Pathfinder mission is to provide in-flight demonstration of some of the LISA critical technologies in achieving the free-fall condition of a LISA-like test-mass in the bandwidth from 1 to 30mHz. Accordingly, owing to high inertial loads arising during the launch phase the test-mass needs to be firmly secured to the GRS, in order to avoid collision with the surrounding electrodes and housing parts. After the launch and orbit commissioning, the test-mass must be released to floating conditions, in compliance with strict requirements of initial position and velocity, due to the low force and torque authority made available by the capacitive actuation system. The Caging Mechanism Assembly is being designed by Alcatel Alenia Space Italia and it constitutes the GRS subsystem dedicated to cage and release the test-mass. The release phase to floating conditions has been identified as critical for the entire mission, therefore a ground-based verification of such a function has been deemed necessary. The verification approach adopted is to set both test-mass and release-dedicated plunger mock-ups in representative tribological conditions of the in-flight situation. An effort is being made to build a facility that enables to characterize the momentum transfer between the two suspended bodies and verify the compliance of the design of the release-dedicated mechanism subsystem of the Grabbing Positioning and Release Mechanism of the CMA. The proposed experiment and the facility status are here presented and discussed. © 2006 American Institute of Physics [ABSTRACT FROM AUTHOR]

Self-gravity noise due to sciencecraft distortion and motion is expected to be a significant contributor to the LISA acceleration noise budget. To minimize these effects, the gravitational field at each proof mass must be kept as small, flat, and constant as possible. Most likely it will not be possible to directly verify that the LISA sciencecraft meets these requirements by measurements; they must be verified by models. The LISA Integrated Modeling team developed a new self-gravity tool that calculates the gravitational forces, moments, and gradients on the proof masses and creates a color coded map of the component contributions to the self-gravity field. The color mapping provides an easily recognized and intuitive interface for determining the self-gravity hot-spots of a spacecraft design. Self-gravity color maps can be generated as true representations of the steady-state, or as an approximation of the variability through computation of the difference values across multiple physical states. We present here an overview of the tool and the latest self-gravity results calculated using a recent design of LISA. © 2006 American Institute of Physics [ABSTRACT FROM AUTHOR]

The baseline concept of LISA had been developed within an industrial investigation by Astrium/EADS and is being reviewed since 2005 in an ongoing formulation phase. One of the most important key technology development issues remains the demonstration of the interferometric readout of the main science measurement. This includes the hardware development of an appropriate Phase Measurement System (PMS). We present the status of our work concerning the design and implementation of a LISA-like PMS with particular emphasis on the hardware development based on Field Programmable Gate Arrays (FPGA’s) as main technology platform and we report on our first results demonstrating the performance of the PMS with synthetic signals. © 2006 American Institute of Physics [ABSTRACT FROM AUTHOR]

In this paper, a double line pier on a high-speed railway in China is taken as an example. the size of each location is drawn up firstly. The design of pre-stressed steel beam for its crossbeam is carried out, and the configuration of ordinary reinforcement is carried out for concrete piers. Combined with bridge structure analysis software Midas Civil and BSAS, the frame pier is modeled and calculated. The results show that the beam and pier column section size reasonable design of pre-stressed steel beam with 17-7Ф5 high strength low relaxation steel strand, can meet the requirements of high speed railway carrying capacity; the main reinforcement of pier shaft with HRB400 diameter is 28mm, ring arranged around the pier, can satisfy the eccentric compression strength, stiffness and stability requirements, also meet the requirements of seismic design. [ABSTRACT FROM AUTHOR]