Abstract:
A mixed material of liquid crystals and resin is dropped on at least one substrate in an amount greater than the amount needed to cover a display area for the LCD panel. The substrate is adhered to another substrate, and excess material is removed to the outside of a display area. The phase-separation of the liquid crystals and resin is carried out by irradiating light while pressure is added to at least one substrate, so that a liquid crystal display panel applied to a liquid crystal display device or a light shutter can be manufactured without applying a complex vacuum device.
Abstract:
A process for producing high-density thin type optical disk substrates having good replicability and birefringence sufficient for practical use. In filling the resin into the cavity, the stress on the resin is reduced by controlling the relation of the cavity width and the injection compression force to reduce birefringence. Further, the mirror surface of the mold is maintained at a certain temperature to facilitate the resin flow and a good replicability and reduction of birefringence is achieved by terminating the resin filling and starting the compression process at the time at which the pressure of the resin filling is at a minimum.
Abstract:
An optical disk substrate which includes a plurality of sectors, tracks alternately formed into lands and grooves in a direction intersecting at right angles with a tracing direction during recording or reproducing of information, a first pit row having address information and formed at a specific position of the track of a predetermined one land or groove, and a second pit row having address information and formed in a different track neighboring the track formed with the first pit row in the tracing direction, and formed at a position deviated longer than a length of the pit row from the specific position. By the above arrangement, the address information can be read without interference, with reduction of waiting time for reading.
Abstract:
An aircraft has an airframe including a fuselage having major structural members made of a composite material. The airframe also includes a sweepforward main wing mounted on top of the fuselage and a T or cruciform tail on the fuselage. The aircraft has no canard. The aircraft has a pair of main landing gear units attached to the fuselage below the main wing, the main landing gear units having short strut assemblies which allow the crew and passengers to get on and off the aircraft easily. The sweepforward main wing allows a wide and comfortable cabin space to be created in the fuselage.
Abstract:
An improved gas generator apparatus having a compressor, a combustor, and a turbine having a turbine rotor coupled by a rotor shaft to the compressor rotor of the compressor. The combustor is spiral shaped and positioned between the compressor and turbine which allows the direction of flow of air or working gas to remain substantially unchanged from the compressor to the turbine, while maintaining a compact configuration. In operation, air drawn into the compressor is swirled circumferentially and pressurized by the compressor, and then delivered into a combustion chamber while it is being swirled. Air is expanded in the combustion chamber as it is swirled in and along the spirally shaped expansion chamber tube and then flows as a working gas into the turbine in which the gas drives the turbine rotor while the gas is still being swirled in the same direction. The air or working gas, therefore, maintains a swirling flow in one direction from the compressor to the turbine. In one embodiment, the scrolls for the compressor and turbine a compactly located in a normally empty space surrounding the shroud for the rotors of the compressor and turbine. In another embodiment, the separate compressor shroud is eliminated by providing a casing surrounding the spiral combustion expansion tube for receiving compressed air directly into that casing.
Abstract:
Disclosed is an optical information recording medium which comprises an active layer which undergoes phase change upon irradiation with light and protective layers formed on both the sides of the active layer, wherein the thermal capacity of the active layer which is a heat source is decreased, a reflection layer of high thermal conductivity is provided on the protective layer to cause increase of the coefficient of lines expansion of the protective layer with increase in distance from the active layer or the thickness of each layer is specified to make nearly the constant maximum temperature by irradiated light against a change in the thickness of the active layer.
Abstract:
A contrarotating propeller type propulsion system having first and second output rotary cylinders which are carried individually on an outside support cylinder fixedly secured to a first support structure, the first output rotary cylinder being borne on the outer peripheral surface of the first support cylinder through bearings and the second output rotary cylinder borne on the inner peripheral surface of the first support cylinder through bearings. The first and second output rotary cylinders serve to support the first and second contrarotating propellers, respectively. The first and second output rotary cylinders are supported on the first support cylinder at two axially spaced points. The driving shaft is borne on a second support cylinder fixedly secured to the support structure and surrounded by the first support cylinder. The gear reduction mechanism for causing the counter rotation of the propellers is provided within a case that is cooled and lubricated by oil flowing therethrough and also is cooled by an annular air passage around the entire exterior of the case.
Abstract:
A carbon material is provided which comprises spherical crystal amorphous carbon having a void diameter in the crystallite of 30 .ANG. or below, and there is also provided a process of the production of a carbon material, in which a thermosetting resin that will be converted to amorphous carbon after using for the carbonization is molded, the molded thermosetting resin is preliminarily heated at a temperature of 1,000.degree. to 1,900.degree. C., and an isostatic pressure of 1,000 atmospheres or over is applied to the preliminarily heated body at a temperature of 2,050.degree. C. or over.
Abstract:
A valve operating mechanism for an internal combustion engine having a valve disposed in an intake port or an exhaust port of a combustion chamber and being openable by a rotatable cam and cam follower in synchronism with the engine crankshaft rotation. The valve is normally urged toward the closed position by a spring means encircling the valve. Various embodiments are disclosed for varying the resilient force urging the valve toward the closed position during different engine operating conditions, such as, increasing the resilient valve closing force during high-speed operation for ensuring proper valve operation and decreasing the resilient valve closing force during low-speed operation for reducing friction in the valve operating mechanism. The valve operating mechanism includes means for switching between actuation by a low-speed cam or a high-speed cam. One form of the spring means includes a mechanism for increasing the spring force on the high-speed cam follower only during high-speed operation. Another form of the spring means includes a valve spring having a non-uniform rate of compression for imposing a higher rate of increase of spring force as the valve is opened a larger amount at high-speed.
Abstract:
Valve operating apparatus is disclosed in which intake or exhaust valves for an internal combustion engine are operated by rocker arms driven by cams and have a hydraulically operated coupling mechanism for selectively connecting or disconnecting adjacent rocker arms to vary the operation timing of the valves under different engine operating conditions. The fluid circuit for operating the coupling mechanism contains a valve which is energized to a closed position during low-speed engine operation and de-energized to an open position during high-speed engine operation.