Abstract: Disclosed is an X-ray reflecting device and an X-ray reflecting element constituting the X-ray reflecting device capable of facilitating a reduction in weight and being prepared in a relatively simple manner. The X-ray reflecting element of the present invention comprises a body made of a solid silicon, and a plurality of slits formed in the body in such a manner as to penetrate from a front surface to a back surface of the body. Each of the slits has a wall surface serving as an X-ray reflecting surface.

Abstract: It is possible to obtain a wide-band feeder circuit a lower conductive plate provided substantially in parallel to an upper conductive plate, a short-circuit portion provided in a concave manner at a central portion of the lower conductive plate, and a countersunk portion provided in a convex manner at a central portion of a short-circuit plate forming a bottom of the short-circuit portion. It is also possible to obtain an antenna including such a wide-band feeder circuit.

Abstract: Air conditioning equipment that ensures sufficient noise reduction in the low frequency range of a few hundred hertz or below. The air conditioning equipment is characterized by including a heat exchanger for exchanging heat between air and refrigerant of a refrigeration cycle, a fan that supplies air to the heat exchanger, an air duct in which the fan is installed and through which acoustic waves are propagated, and a plurality of small holes that blows a jet into the air duct and sucks a jet from the air duct by a pressure difference between the blow side and the suction side of the fan.

Abstract: A main swirler of a triple annular configuration that is partitioned by a pre-filmer and a separator is installed in an inlet port of a main air flow channel. The vicinity of the inner wall of the main air flow channel provided with a main fuel injection port is bulged radially outward from the innermost surface (innermost surface of a small swirler) of a main swirler. Further, a distance from the main fuel injection port and the pre-filmer is set such that an effective opening area between the pre-filmer and “the inner wall of the main air flow channel provided with the main fuel injection port” is equal to an effective opening area of the small swirler. The swirling directions of the swirlers of the main swirler are “clockwise”-“counter-clockwise”-“clockwise” respectively along the radial outward direction when the swirling direction of the innermost swirler is taken as “clockwise”.

Abstract: To provide a compact and high performance gyroscope. A gyroscope (10) comprises an outer frame (11); an inner frame (12) positioned inside the outer frame and supported to be movable in one reciprocating direction; a plurality of proof masses (15) positioned inside the inner frame and supported to be movable in the direction orthogonal to the one reciprocating direction; a plurality of outer support suspensions (13) which connect the outer frame and the inner frame; a plurality of inner support suspensions (14) which connect the inner frame and each of the proof masses; actuators (16) for accelerating each of the proof masses; and detectors (17) for detecting displacement of the inner frame against the outer frame. The actuators oscillate the plurality of proof masses in-phase, and wherein Coriolis forces induced on each of the proof masses are summed up in the inner frame.

Abstract: Disclosed is an X-ray reflecting device and an X-ray reflecting element constituting the X-ray reflecting device capable of facilitating a reduction in weight and being prepared in a relatively simple manner. The X-ray reflecting element of the present invention comprises a body made of a solid silicon, and a plurality of slits formed in the body in such a manner as to penetrate from a front surface to a back surface of the body. Each of the slits has a wall surface serving as an X-ray reflecting surface.

Abstract: An ultrahigh altitude sun-synchronous orbit satellite system having one or plural satellites orbiting the sun such that the satellites revolve around the earth in a substantially circular or elliptic motion at an altitude of several million kilometers from the earth, beyond the sphere of earth gravity influence. The satellites are placed on an orbital plane relative to both the sun and the earth and keep a distance and geometry between the satellites, sun and earth substantially constant. The satellite system performs any one of the services of space observation, global observation, and satellite communication. The satellites orbit the sun with both inclination and eccentricity distinct from those of the revolution of the earth and revolve around the earth with a sun synchronous property in which the local solar time is kept constant at a point on the surface of the earth directly beneath the satellite.

Abstract: The calibration tool of the present invention is a transparent camera calibration tool in which a plurality of indicator points is spatially distributed and fixed, wherein the indicator points are formed as intersecting points of thin wires extended to the frame by varying the position of the thin wires in the thickness direction and the indicator points are formed as groups of intersecting points of thin wires rendered by extending a plurality of parallel thin wire groups in different directions. The indicator groups are arranged in at least two sets in a non-coplanar relationship and embodied by distributing distinguishable minute particles in a transparent raw material or by marks or similar in the surface of the raw material. Further, a plurality of cameras arranged separately from one another are calibrated in the same coordinate system by using the transparent camera calibration tool, plate tools that are added thereto, and light beams.

Abstract: Main arrays (MA1-MAm) of solar cells (2) are provided so as to correspond to shunt circuits (SM1-SMm), respectively. Charge arrays (CA1-CAn) are provided so as to correspond to shunt circuits (SC1-SCn) and charging circuits (CH1-CHn), respectively. Each shut circuit operates independently from other shunt circuits, and each charging circuit operates independently from other charging circuits.

Abstract: To provide an aircraft wing which has both high bending flexibility in the wing chord direction and high capacity to maintain the wing shape in the wing span direction, and to which morphing aircraft technology can be applied in the high-speed regime where aerodynamic forces are high. The wing is formed by arranging a plurality of CFRP rods having maximum anisotropic stiffness in the axial direction, so as to be parallel to the wing span direction, and filling the gaps between the CFRP rods with an elastic material.

Abstract: It is an object of the present invention to provide a device for generating analysis object data that allows the simple setting of an intrusion detection policy, and more specifically, to allow policy setting that performs pattern matching with a plurality of signatures summarized as a single intrusion detection policy, and to allow policy setting that performs pattern matching of the context of an attack and response to this attack.

Abstract: In a blade vortex interaction (BVI) noise reduction system for a helicopter a rotor blade, a tab is movable via an actuator from a first position, wherein the tab is within the blade, to a second position, wherein the tab extends outwardly from a trailing edge of the rotor blade. The actuator is operated so that the tab advances and retreats in response to rotating timing of the rotor blade, to reduce the BVI noise of the rotor blade.

Abstract: A method of controlling a redundant manipulator for assigning one or more redundant joints from a plurality of joints and obtaining the solution to an inverse kinematics problem at high-speed. The joints are arbitrarily classified into redundant joints and non-redundant joints, and an initial value is set for the joint angle of the classified redundant joint as a parameter. Then based on an evaluating function or a constraint condition defined by the joint angle of the redundant joint provided as a parameter and the joint angle of the non-redundant joint, which is determined by the inverse kinematics calculation according to the change of the parameter, an optimum solution of a set of joint angles is determined, and until the optimum solution covers the target range of the hand position, the procedure to determine the optimum solution is repeated with relaxing the constraint conditions.

Abstract: In a schlieren optical system, a laser beam is passed through the jet flow and the ambient around the jet flow, and a high speed sampling is performed using a high speed photo sensor while displacing measurement points. The value obtained by sampling represents a result of the optical path caused curved by a density gradient generated in an arc-shape from the center of the jet flow. The value is subjected to a high speed discrete Fourier transform and decomposed into frequency components which constitute the noise. Thereafter, Abel inversion is performed on data belonging to a particular frequency to obtain a density gradient in the radial direction from the center of the jet flow. The obtained density gradient is visualized in a graph display, so that the position of the sound source and the state of the jet flow can be accurately grasped.

Abstract: In a method for injecting a plurality of spacecraft into different circum-earth or interplanetary orbits individually in a single launch, a plurality of spacecraft coupled to an assist module are injected into an interplanetary orbit having a periodicity synchronous with the earth's revolution period. Then, in a maneuver allowing the assist module to re-counter with and pass near to the earth (Earth swing-by), the assist module appropriately performs an orbital change maneuver and a separation maneuver for each of the spacecraft in a sequential order. Through these maneuvers, a closest-approach point to the earth is changed for each of the spacecraft so as to drastically change a subsequent orbital element for each of the spacecraft. The assist module takes a sufficient time to determine a target orbit for each of the spacecraft with a high degree of accuracy until a half month to several days before a closest-approach time in the Earth swing-by.

Abstract: A method is disclosed for designing an orbit of a spacecraft which allows the spacecraft to take a small-radius halo orbit near a Lagrange point while avoiding the prohibited zone where the spacecraft may be shadowed or might be prevented from making communication. The method makes it possible to have a closed orbit although being similar to a Lissajous orbit, under a restricted condition where a propulsion force magnitude applied to a spacecraft is fixed, and where it rotates at a constant angular velocity, based on the equation of motion close to a Lagrange point. The method also provide a theory for guiding/controlling the orbit of a spacecraft, that is, the embodiment of the above orbit design method.

Abstract: An ultrasonic test method for detecting a defective portion more precisely in a noncontact reflection way, and ultrasonic test instrument used for the method. An ultrasonic wave is transmitted from a transmitter (20 (21)) provided on one side of an object under test, and the reflected wave is received by a receiver (30 (31)) provided on the same side. The ultrasonic wave is transmitted/received through an air layer between the transmitter and the object (100) under test and between the receiver and the object (100). The relative positions of the transmitter (20), the receiver (30), and the object (100) are so determined that the air propagation time ta of the air path (RA) between the transmitter and the receiver is longer than the propagation time tb of the reflected wave in the reflection path (RB). The propagation of the ultrasonic wave through the solid body between the transmitter and the receiver is blocked.

Abstract: To provide a simple structured and low cost pintle injector capable of uniformly atomizing and mixing fuel and oxidizer, and further improving the combustion efficiency of the combustion reaction in the combustion chamber. A pintle injector part having a first propellant channel forms a first injector flow path as a regenerative cooling path along the pintle external wall that projects into a combustion chamber, and high temperature fuel gas is injected from the first pintle injector port. On the other hand, an axial injector part is located upstream of the first pintle injector port, and injects comparatively low temperature liquid or gas fuel from an axial injector port via a third propellant channel and a third injector flow path. Oxidizer is injected from a second pintle injector port via a second propellant channel and a second injector flow path, and is atomized and mixed while being impinged on either by the high temperature fuel gas and the comparatively low temperature liquid or gas fuel.

Abstract: An optical element of the present invention exhibits at least one of an upconversion emission characteristic and a light amplifying characteristic when irradiated with an excitation light. The optical element includes a bulk glass that contains titanium oxide as a main component, and the glass further contains a rare earth element. As the rare earth element, at least one element of Er and Yb, or a combination of Yb and Tm preferably is used, for example.

Abstract: A pressure tight large-scaled membrane structure comprising a bag body having a plurality of gores attached to each other along an attachment line, and a plurality of first ropes attached over a predetermined range of the bag body in such a manner as to be orthogonal to the attachment line of the gores, whereby a cylindrical shaped portion is formed. The cylindrical shaped portion has a substantially circular cross-sectional area that is a maximum substantially circular cross-section of the bag body and the plurality of first ropes each having approximately the same length as a circumference of the substantially circular-cross section having a maximum area with respect to the bag body.