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A driving simulator capable of duplicating the critical sensations incurred during a spin, or when a driver is engaged in drift cornering, was constructed by Mitsubishi Heavy Industries, Ltd., and Hiromichi Nozaki of Kogakuin University. Specifically, the simulator allows independent movement along three degrees of freedom and is capable of exhibiting extreme yaw and lateral acceleration behaviors. Utilizing this simulator, the control characteristics of drift cornering have become better understood. For example, after a J-turn behavior experiment involving yaw angle velocity at the moment when the drivers attention transitions to resuming straight ahead driving, it is now understood that there are major changes in driver behavior in circumstances when simulator motions are turned off, when only lateral acceleration motion is applied, when only yaw motion is applied, and when combined motions (yaw + lateral acceleration) are applied.

The Advanced ECS is under development for the purpose of saving fuel, improving safety, and cabin comfort. In FY2006 study, basic components (i.e. MDC, OBNOGS, desiccant units, and CO2 removers) have been improved and their performances evaluated including resistance to environmental condition (i.e. vibration). In addition, the suitable system configuration for a 90-seats aircraft has been considered to evaluate the feasibility of the system. In this paper, we show the results of the evaluated performances based on prototype components, and the analytical study of a revised system configuration.

Nowadays, space crafts such as a space shuttle take the O2 gas for crew respiration from the earth. However, for long periods of stay in space and far missions such as to the moon, it is not possible to carry sufficient amounts of oxygen. Therefore, there is need to establish other methods of supplying the extra O2 required by the crew under such circumstances. The CO2 reduction system is one method to generate O2 in space.

The Japanese Experimental Module (JEM) Pressurized Module (PM) is a facility where astronauts conduct experiments or control the total JEM facility. Inside the PM, the air composition, temperature and humidity are controlled so as to be comfortable for astronauts' activity all the time. The verification of the on-orbit performance of the functions constituting a manned space system is one of the critical points. Computational Fluid Dynamics (CFD) simulation technology is utilized to characterize and investigate the airflow in the JEM for various operating conditions. The development of a successful CFD model for International Space Station (ISS) operation is useful because there are always off-nominal and other contingency operations, which might occur and could be analyzed using an existing CFD model. This paper also presents the cabin ventilation test data obtained from the JEM flight module.

In order to design a well-balanced truck frame, optimization of not only the stiffness of the entire body and stress of each member, but also the internal force of each member is necessary, including the effect of a rear body mounted on the frame. This paper proposes a new parameter, “torsional stiffness share rate,” that directly correlates the contribution of member torsional stiffness to frame torsional stiffness with the internal force of the members as to torsion of the truck frame. The merits of the torsional stiffness share rate are shown in comparison with the strain energy share rate and the stiffness contribution rate. The results of experimental and FEM analyses of the torsional stiffness share rate are also presented.

Mud adhesion to the rear surfaces of trucks, vans and buses causes troublesome results such as aesthetic degradation, hindered rear view and laborious washing. To raise the product value of trucks and buses, it is important to develop effective measures for suppressing such mud adhesion. In this research the authors first clarified the mechanism of mud adhesion through flow visualization tests. Then, wind tunnel tests were performed to predict the effects of various countermeasures, and prospective ones were put under actual driving tests to verify their effects. The following measures were found effective in suppressing mud adhesion. (1) Aerodynamic improvement by attaching corner vanes to the upper and side edges of the rear surface. (2) Blocking road splash with a slanted plate under the truck and close to the base.

Wet multiple plate clutches consist of friction plates, on which a friction material is bonded, and mating plates that are plain metal plates. Since the frequency and the range of load in the field of forklift trucks vary widely and are more severe than those for passenger cars, the wet multiple plate clutches on forklift trucks are often damaged. Damaged clutches that were returned from the field typically had 3 types of symptoms: 1.Only the friction material was damaged, 2.Only the mating plates were deformed, 3.Both symptoms were observed. It was clear that the cause of these symptoms depended on the difference of the operating application and the strength criteria of each part. This showed that a design guide for wet multiple plate clutches considering the strength balance between the two parts according to the work application was required. The relevant flow chart of this design process was proposed.

Some research and development studies concerning Mitsubishi DC2 diesel engines are described. The engines are of 90-deg V type newly designed, for trucks or buses of more than 14 tons (30,900 lb) gross weight, after exhaustive fundamental researches and many years' experience. The series covers 6-, 8-, and 12-cyl engines of the water-cooled, precombustion-chamber type with a 130-mm (5.12 in.) bore and a 125-mm (4.92 in.) stroke. The engines are capable of developing a maximum output of 200-400 ps (197.5 ∼ 395 hp) and combine high reliability with compact and light-weight construction. Naturally the use of common parts among these engines in series facilitates their parts' supply and maintenance. In addition to the naturally aspirated engines, turbocharged 8- and 12- cyl engines are available.

In closed environments such as space stations, it is necessary to eliminate CO2 produced by the metabolisms of crew members, for their life support, and to regenerate the air by supplying O2 to make up for the deficiency. If humans are to be in space only a short time, it is in general advantageous to adsorb CO2 with lithium hydroxide, and to supply O2 from tanks. But when the stay in space is long, it is essential to establish a highly reliable and energy-efficient system to recover CO2 in high concentrations and regenerate O2 from this recovered CO2 Fig. 1 shows the system presently conceived, which is roughly divided into the following processes: A process that removes and concentrates CO2 from the air; a CO2 reduction process that separates carbon from CO2 and obtains water; and a water electrolysis process that decomposes water electrically and recovers O2.

Water is one of the most valuable items in the closed environment such as the space station. It will be used for human habitation and various experiments. However, it will be not supplied from the earth. Therefore, water reclamation is one of the most indispensable technologies in the space station. The water treatment processes used to be combinations of the membrane separation technologies of pre-filter (PF), ultra-filtration (UF) and reverse osmosis (RO) which has been developed for the salt-to-fresh distillation technology. One the other hand, more efficient hydrophobic membranes have been developed recentry. Using these new water treatment technology of hydrophobic membranes, the membrane distillation (MD), combined with the conventional water treatment process in now being investigated for water reclamation. The MD is expected to be most important process of the water reclamation system integrated into the space station in the future.

One of the important feature in the Environment Control and Life Support System required to support long duration mission at the Space Station is an oxygen supply for the human metabolism. The recovery of oxygen from the concentrated carbon dioxide through chemical methods will give significant advantage to the Space Station by reducing the supply requirement of the consumables, such as oxygen bottles. Oxygen recovery plants using the Bosch reaction and the Sabatier reaction are experimentally developed and tested. The Bosch reaction has been considered to produce carbon and water directly from carbon dioxide by the hydrogenization process. But it seems to proceed through two steps with carbon monoxide as the intermediate product. Also the total production rate is relatively low and the carbon deposited is less solid. The Sabatier reaction requires two steps to achieve carbon and water, with methane as the intermediate product.

Improvement of an air revitalization technology of ECLSS (Environment Control and Life Support System) is one of the key elements in development and operation of future human space systems. The paper summarizes a trace-contaminant control system which employs “thermal storage / combustion” method for reduction of cabin and equipment-generated off-gases. For comparison, the International Space Station will be equipped with a trace-contaminant system utilizing “oxidization” method with catalyst substances. Preliminary functions of the processor were also evaluated to determine the designing parameters for a space system hardware. The results indicate the capability of processor under large volumes and high concentration of trace gases, and its systematic feasibility.

A fundamental study was performed to develop a high efficiency solar heat receiver for a solar energy experiment mission on the Japan experiment module - exposed facility of the international space station. It is composed of a solar heat absorber, thermal energy storage and heat pipes. This system is aimed to transport solar thermal energy to a bottoming system with an efficiency of 80 %. Thermal analysis of each component was performed to assess its design approach. One ground testing model of the solar receiver was designed and fabricated in 1998, and then would be experimentally evaluated in 1999 at a test vacuum chamber of National Aerospace Laboratory.