Abstract: It is an object of the present invention to solve the problem of a drop in precision in conventional systems using a square pyramid type five-hole probe due to the drop in atmospheric pressure in high altitude ranges, and to provide a wide velocity range flight velocity vector measurement system that can prevent a drop in measurement precision. Furthermore, it is also an object of the present invention to provide a method for eliminating the effects of detection fluctuations caused by adhering water droplets, ice particles or dust in a wide velocity range flight velocity vector measurement system.

Abstract: A measuring body is provided in a fluid path between a pump and a fuel injection valve, a flow amount for which is measured. An inner space of the measuring body is divided into a first and a second fluid chambers by a partitioning wall, wherein the first and second fluid chambers are, respectively, operatively connected to the pump and the fuel injection valve. A movable member (float) is slidably inserted into a through-hole formed in the partitioning wall, so that both ends are respectively exposed to the first and second fluid chambers. When the fuel injection is carried out by the fuel injection valve, the fluid in the second fluid chamber is decreased corresponding to the amount of injected fluid, and thereby the float is moved in a direction from the first to the second fluid chamber. The amount of the injected fluid is measured by detecting the movement of the float.

Abstract: It is an object of the present invention to solve the problem of a drop in precision in conventional systems using a square pyramid type five-hole probe due to the drop in atmospheric pressure in high altitude ranges, and to provide a wide velocity range flight velocity vector measurement system that can prevent a drop in measurement precision. Furthermore, it is also an object of the present invention to provide a method for eliminating the effects of detection fluctuations caused by adhering water droplets, ice particles or dust in a wide velocity range flight velocity vector measurement system.

Abstract: A measuring body is provided in a fluid path between a pump and a fuel injection valve, a flow amount for which is measured. An inner space of the measuring body is divided into a first and a second fluid chambers by a partitioning wall, wherein the first and second fluid chambers are, respectively, operatively connected to the pump and the fuel injection valve. A movable member (float) is slidably inserted into a through-hole formed in the partitioning wall, so that both ends are respectively exposed to the first and second fluid chambers. When the fuel injection is carried out by the fuel injection valve, the fluid in the second fluid chamber is decreased corresponding to the amount of injected fluid, and thereby the float is moved in a direction from the first to the second fluid chamber. The amount of the injected fluid is measured by detecting the movement of the float.

Abstract: There is provided a method of generating no error in the output of a resonator fiber optic gyro even when the polarization dependency loss is present in a ring resonator of the resonator fiber optic gyro. The relationship between &Dgr;L and &Dgr;&bgr; is set to satisfy the formula &Dgr;&bgr;&Dgr;L=&pgr;+2n&pgr; [radian] (n: integer), or &Dgr;&bgr;&Dgr;L is close to the value obtained from the formula, where &Dgr;L is defined as the difference between the lengths L1 and L2 of two portions of a waveguide divided by a coupler and a polarization-rotating point in the ring resonator, and &Dgr;&bgr; is defined as the difference in propagation constant of two axes of polarization having the waveguide. &Dgr;L is set so that the error induced by the polarization fluctuation is minimized.

Abstract: A flight velocity detection system using a truncated pyramid-shape multi-e Pitot probe in which an extreme end portion has a truncated pyramid-shape, a cylindrical hole is provided at the apex thereof, a total pressure tube of a smaller diameter than that of the cylindrical hole is secured at a position by a predetermined length determined by a relationship with the diameter of the cylindrical hole from the extreme end of the cylindrical hole, and groups of pressure holes comprised of a plurality of pressure holes are arranged in each of the truncated pyramid surfaces of the truncated pyramid shape. Items of pressure information detected by the probe are input into a velocity vector processor to convert them into electric signals, and signals are processed using pressure coefficients of the holes of the probe with respect to the velocity vector stored in advance in the velocity vector processor to calculate flight velocity vector (V, .alpha., .beta.

Abstract: An apparatus for detecting double-feed of sheets of paper with a light-transmission sensor. The light-transmission sensor is composed of a light emitting source, such as an LED, and a light receiving sensor located on both sides of a paper transport path. Before the first sheet is fed, the gain of a variable gain amplifier, which amplifies an output of the light receiving sensor, is present at a predetermined value so that an output level of the amplifier may be appropriate. When the first sheet passes the light transmission sensor, an output level of the variable gain amplifier is measured and the level for a sheet is stored. Each time a sheet is fed in the sequential paper feeding operation, the output level of the amplifier is measured and compared with the stored data to detect double-feed of sheets. If the level is not appropriate, the intensity of the light emitting source is controlled in order to correct the level.

Abstract: Transferring device for a semiconductor wafer or like part includes a rotatable carrying arm rotatably for carrying a semiconductor wafer or part from its initial position and through a first angle. The rotatable carrying arm has a holding portion for a wafer or part, and a cam follower portion. A motor rotates the rotatable carrying arm through an angle slightly greater than the first angle slightly past a desired position for the wafer. Then, an eccentric cam returns the carrying arm through a second, incremental angle, for bringing the carrying arm, and, hence, the wafer held thereby, to the desired position.

Abstract: A positioning device for a table on which a semiconductor wafer is moved into an inspection position is described. It comprises a pneumatic stage supporting the table and movable both in the x and y directions, a moving device using wire which moves the stage in the x or y direction, and a fine resolution lifting device which moves or lifts the table vertically.

Abstract: A wafer basket station includes a semiconductor wafer basket containing therein a number of semiconductor wafers and an elevating device which raises and lowers the wafer basket to bring a desired wafer in its taken out height. A wafer detecting device is formed with a transmission type optical sensor disposed inclined so that the optical axis thereof passes a center of a semiconductor wafer at the desired height, but not to pass adjacent wafers of the semiconductor wafer.The elevating device of the wafer basket has an elevator which supports wafers to be worked and treated and is guided and driven vertically with respect to a base frame of the device. The elevator is provided with an opaque body. A photocoupler support plate is guided to move vertically and supported with respect to the base frame of the device. A spring means is energized in the departing direction away from the photocoupler support plate against the base frame.

Abstract: The rate-of-climb indicator of this invention can indicate the existence of wind shear.

Abstract: A turn-and-bank indicator can integrate with regard to time the displacement of a pointer of the turn-and-bank indicator, the pointer indicating the turning rate of the airplane. It includes a non-contact converter which outputs an electrical signal in proportion to the deflection of the pointer; an amplifier which amplifies the output of the non-contact converter; an integrator which integrates the output of the amplifier with respect to time; and a digital display unit which displays the output from the integrator at a close position with the pointer.

Abstract: An airspeed indicator for low-speed conveyances which comprises a thin cylindrical hood, a generator supported at the center within the hood and a propeller mounted on the driving shaft of the generator. An indicating means for indicating the magnitude of the airspeed on a scale plate with a pointer is also provided, the pointer being rotated in proportion to the current through an ammeter coupled to the output of the generator. Means for supporting the hood is further provided, the means holding the hood so that when the indicating means is mounted on the low-speed conveyance, the hood may be fixed to face the flight direction.

Abstract: A servo instrument, particularly a servo altimeter, with a minimum of display error. The instrument comprises a capsule assembly, a sector adapted for rotation corresponding to the displacement of the capsule assembly, a photosensor for producing an output showing its angular position relative to the sector, a support for rotating the photosensor while supporting it adjustably in a direction of tracing the sector, a cam adapted to make the amount of the adjustment of the photosensor variable by the position of the support, a motor, means for generating a signal showing the rotating positional angle of the motor, and an amplifier for amplifying the output of the photosensor and driving the motor so as to maintain the output of the photosensor constant.

Abstract: An image developing machine uses magnetic toner for developing a latent image on a light sensitive drum. The magnetic toner is fed onto a surface of a sleeve and applied onto the surface of the light sensitive drum at a developing station in a direction which is the reverse of the moving direction of the drum. Before being applied, the thickness of the toner on the sleeve is lessened twice by doctor blades so as to effectively avoid any occurrence of sticking between the toner particles or sticking thereof to the sleeve surface. Proper values have been found for the distance H between the drum surface and the sleeve surface and gaps L.sub.1 and L.sub.2 between leading ends of the doctor blades and the sleeve surface.

Abstract: A viscous damping device positioned between a gimbal shaft and a bearing sleeve supporting the gimbal shaft is provided for damping a gyro apparatus in a rotational direction. The viscous damping device comprises first and second rings fixed to an outer periphery of the gimbal shaft. A circular groove provided in the first ring is complementary with a circular protrusion of the second ring, so that damping liquid initially poured into the circular groove is made to fill an air gap between the outer peripheries of the rings and an inner wall of the bearing sleeve by inserting the circular protrusion into the circular groove.

Abstract: A turn rate indicator of an aircraft wherein the outer rotor of a Hall motor is used as a gyro rotor. A driving circuit for the gyro stator circuit is provided integrally with the gyro gimbal. The driving circuit is coupled to a connector affixed to the case of the turn rate indicator with fine connecting lines keeping a slack section between the driving circuit and the connector.

Abstract: A turn rate indicator for an aircraft includes magnetic substance pieces facing each other, one being rotatable integrally with a gimbal and the other being fixed to a body. Because of the attracting force generated between the magnetic substance pieces, a pointer of the indicator returns to its zero point smoothly and certainly.

Abstract: An aircraft instrument with an acceleration compensation device comprises at least a capsule, a rocking axle, a link mechanism to transmit displacements of a free end of the capsule to the rocking axle, a first gear integrally provided with the rocking axle, a second gear meshed with the first gear and being rotatable, and weights. The weights are provided on the first gear and the second gear each correspondingly, and rotative force of the weights caused by an acceleration force works on the rocking axle so as to cancel the rotative force of the rocking axle by the displacements, due to the acceleration, of the free end of the capsule.