Abstract: Provided is a road surface friction coefficient measuring method and device for measuring the friction coefficient of road surfaces such as roads and runways, and which can be used by being mounted on a general car. This device has a spindle 5 detachably connected to the wheel of a travelling wheel 3 of a car, a support arm 6 oscillatably connected to the spindle, and a measuring wheel supported rotatably by the support arm.

Abstract: A jet engine for supersonic aircraft which enables supersonic flight and high fuel efficiency to be achieved while suppressing noise at take-off. The engine comprises a front engine consisting of a turbofan engine, and a rear engine or engines consisting of a turbofan or turbojet engine disposed to the rear of said front engine, the rear engine(s) being coupled switchably by a tube to the bypass duct of the front engine, the air inlet(s) of the rear engine(s) being coupled to the bypass duct during supersonic flight, or during acceleration to supersonic speed, whereby the pressure and temperature of the bypass air from the front engine is raised by the rear engine(s), and the air inlet(s) of the rear engine(s) being separated from the bypass duct during take-off, in such a manner that the bypass air is discharged without the temperature or pressure thereof being raised further.

Abstract: In a rotary articulated robot having at least a plurality of offset rotary joints in which a drive arm and driven arm are driven in rotation about an offset rotary axis inclined with respect to the arm axis, a hollow rotary shaft that is driven in rotation by a motor is arranged rotatably, being inclined, at the leading end of the arm of either the drive arm or driven arm while a rotor member to which turning effort from the hollow shaft is transmitted is fixed at the base of the other arm, said hollow rotary shaft and said rotor member constituting a high reduction ratio transmission/torque increasing mechanism.

Abstract: An arithmetic processing method and system in a wide velocity range flight velocity vector measurement system using a square truncated pyramid-shape five-hole Pitot probe. Approximation equations that determine attack angle &agr; and sideslip angle &bgr; in the form of third-order equations concerning attack angle pressure coefficient C&agr; and sideslip angle pressure coefficient C&bgr;, which are known numbers, are expressed in the form of a polynomial equation concerning Mach number M, where the coefficients are obtained from a lookup table.

Abstract: The present invention relates to a network unauthorized access analysis method, a network unauthorized access analysis apparatus utilizing this method and a computer-readable recording medium having a network unauthorized access analysis program recorded thereon, and is capable of processing arbitrary data, performing arbitrary communication between networks, easily dealing with an increase in a number of protocols and coping with arbitrary protocols.

Abstract: Provided is a road surface friction coefficient measuring method and device for measuring the friction coefficient of road surfaces such as roads and runways, and which can be used by being mounted on a general car. This device has a spindle 5 detachably connected to the wheel of a travelling wheel 3 of a car, a support arm 6 oscillatably connected to the spindle, and a measuring wheel supported rotatably by the support arm.

Abstract: A flight velocity vector measuring system in a wide velocity region in which an attack angle pressure coefficient C&agr; of air current, a sideslip angle pressure coefficient C&bgr; and an air current angle pressure coefficient C&ggr; are obtained from five pressure information detected by a square truncated pyramid-shape probe. The aforementioned pressure coefficients, pressure calibration coefficients with respect to a Mach number M, an attack angle &agr; and a sideslip angle &bgr; every velocity region obtained by dividing the wide velocity region into a plurality of regions stored in advance in the calculation processor, and a Mach number M, an attack angle &agr; and a sideslip angle &bgr; of unknown quantity constitute a calculation processing expression comprising a polynomial approximation to call the pressure calibration coefficients in the velocity region, and flight velocity vectors (M, &agr;, &bgr;) are calculated by the polynomial approximation.

Abstract: A transportable three-dimensional calibration wind tunnel system is comprised of a small wind tunnel portion for creating a three-dimensional calibration air having a suitable wind velocity, and a two-axis rotational deformation device portion for causing said wind tunnel portion to effect a conical motion with a nozzle blow port being an apex to suitably change a flow angle. The two-axis rotational deformation device is comprised of a .beta.-angle rotational deformation device having a .beta.-angle deformation base supported to be rotated horizontally, and a .alpha.-angle rotational deformation device having a .alpha.-angle deformation base supported to be rotated vertically. A rotational axis of the .alpha.-angle deformation base, a rotational axis of the .beta.-angle deformation base and a center axis of the small wind tunnel portion are arranged so that they intersect at a point.

Abstract: A transportable three-dimensional calibration wind tunnel system consisting of a small wind tunnel portion for creating a three-dimensional airflow having a suitable wind velocity, and a two-axis rotational deformation device portion for causing the wind tunnel portion to effect a conical motion with a nozzle blow port being in close proximity to an apex to suitably change a flow angle. The two-axis rotational deformation device includes a .beta.-angle rotational deformation device having a .beta.-angle deformation base supported to be rotated horizontally, and an .alpha.-angle rotational deformation device having an .alpha.-angle deformation base supported to be rotated vertically. A rotational axis of the .alpha.-angle deformation base, a rotational axis of the .beta.-angle deformation base and a center axis of the small wind tunnel portion are arranged so that they intersect at a point.

Abstract: A transportable three-dimensional calibration wind tunnel system consists of a small wind tunnel portion for creating a three-dimensional airflow having a suitable wind velocity, and a two-axis rotational deformation device portion for causing the wind tunnel portion to effect a conical motion with a nozzle blow port being in close proximity to an apex to suitably change a flow angle. The two-axis rotational deformation device includes a .beta.-angle rotational deformation device having a .beta.-angle deformation base supported to be rotated horizontally, and an .alpha.-angle rotational deformation device having an .alpha.-angle deformation base supported to be rotated vertically. A rotational axis of the .alpha.-angle deformation base, a rotational axis of the .beta.-angle deformation base and a center axis of the small wind tunnel portion are arranged so that they intersect at a point.

Abstract: A mounting object comprises a combination of a mounting object body wherein engaging portions of fastener elements of a metallic heat-resistant two-dimensional fastener are projected outside from a mounting surface, and base portions are embedded and integrally molded, and a mating fastener element base object wherein mating fastener elements in detachably engagement with said fastener elements are projected and integrally molded. Said mounting object body is obtained as a heat-resistant material integral with a metallic two-dimensional fastener by covering and fixing part of the fastener elements of the metallic two-dimensional fastener with a carbon powder having a high melting temperature and covering bases thereof with a metallic powder, a ceramics powder or a mixed powder of them to mold and sinter it.

Abstract: A mounting object comprises a combination of a body wherein elements of a metallic heat-resistant two-dimensional fastener in a mounting surface, and their engaging portions projecting therefrom have their base portions embedded and integrally molded, and a mating base object wherein integrally molded mating fastener elements project for detachable engagement with said fastener elements. The mounting object body is formed as a heat-resistant material integral with a metallic two-dimensional fastener by covering and fixing part of the fastener elements of the metallic two-dimensional fastener with a carbon powder having a high melting temperature and covering bases thereof with a metallic powder, a ceramics powder, or a mixture thereof which is molded and sintered.

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: A plurality of eccentric rotors are rotatably fitted between a fixed base and an output shaft on which an object to be vibrationproofed is mounted, the output shaft being supported movably in 3 to 6 Degree-of-Freedom, magnet spring mechanisms are provided on fitted wall surfaces between the fixed base and the eccentric rotor, a composite vibrationproof adjusting spring is provided between the fixed base and the output shaft, the magnet spring mechanism responding to a fine displacement of the output shaft, and in a case where the output shaft is greatly displaced, the output shaft is braked so as to be restored to a predetermined position by the composite vibrationproof adjusting spring mechanism. The magnet spring mechanism produces a large braking force since a rotational angle is large and a rotational-angle speed is high due to eccentricity of eccentric rotors.

Abstract: The invention relates to a method and an apparatus for determining the size or the size distribution of fine particles. A single particle or a group of particles are shone by a parallel polarized beam of a single wave length and the scattered intensity on the plane of polarization of the incident beam is measured by a photodetecting array. For a single particle the size is determined from the peak scattering angle at which the profile of the product of the scattered intensity and the scattering angle has the peak. On the other hand, for a group of particles, the size distribution is determined from the angular variation of the scattered intensity or the profile of the product of the scattered intensity and the scattering angle measured on the plane of polarization of the incident beam.

Abstract: A docking and active damping device for space structures is provided, in a docking portion of one space structure to be docked, with a positioning device in which an output rotor can be moved and rotated within a two-dimensional plane by a composite rotation of one or more eccentric rotors capable of being independently driven and controlled by a direct drive motor and the output rotor, and a docking member having a docking ring and a latch mechanism are supported on the output rotor of the positioning device. A probe having a capture device capable of being protruded and driven in an axial direction by a linear motion is provided inwardly of the docking member, and the probe provides a 4-freedom movement according to a position of the passive side to capture and dock a drogue.

Abstract: The present invention relates to a method of producing a functionally grant material whose components and structure are continuously adjusted by the coating, plating and powder metallurgy techniques to change its function in turn and provide a method of producing a functionally gradient material superior in heat-resistance, corrosion-resistance and resistance to thermal fatigue by distributing a third component having a lower Young's modulus or formed of high-strength material sufficiently durable to the fracture strength among ceramics as a first component and metals or other ceramics as a second component to change the function.

Abstract: A superprecision positioning device includes an output shaft rotor, a plurality of eccentric shaft rotors including an inner eccentric shaft rotor and an outer eccentric shaft rotor, and a bearing base cylinder, electrically rotating and driving mechanism portions being provided between the eccentric shaft rotor and the output shaft rotor, and between the outer eccentric shaft rotor and the bearing base cylinder, respectively, whereby the eccentric shaft rotors and the output shaft rotor may be independently rotated and controlled. With this arrangement, movement in three degrees of freedom may be achieved by translational movement and rotation of the output shaft in a two-dimensional surface, and if an axially movable support shaft is inserted in the output shaft, an article being positioned may be moved with four degrees of freedom in total, providing superprecision positioning in units of 1/10 micron.

Abstract: In the cooling wall of a regenerative cooling rocket combustion chamber, the throat portion thereof in which the heat load is highest is formed of a porous material having a perspiring cooling action. The other portion in which the heat load is relatively low is designed to be cooled by conventional forced convection. By such a composite cooling system, a high cooling effect is provided and yet the pressure loss in the cooling passages is small and light weight and long life of the engine are attained concurrently.

Abstract: A method of producing rocket combustors wherein in forming an outer cylin by a powder metallurgical method on the outer side of a cylinder provided on its outer periphery with a cooling wall of channel construction having a plurality of grooves, a low-melting alloy is used as a filler to be filled into the grooves. It is also possible to form the outer cylinder after forming a Cu plating shell on the periphery of the inner cylinder filled with the low-melting alloy.