| Japan Aerospace Exploration Agency Patent applications |
| Patent application number | Title | Published |
|---|
| 20120092645 | MULTI-LIDAR SYSTEM - An object of the present invention is to provide a method enabling measurement in a wider range than a conventional LIDAR system and capable of measuring airflow information, which is used to reduce shaking of an airframe when an aircraft collides with turbulence, in a shorter period, and a device having corresponding functions. A multi-LIDAR system according to the present invention includes at least two optical remote airflow measurement devices of a Doppler LIDAR system employing laser light that are provided in a fixed relative position relationship, has functions for emitting lasers of identical wavelengths from the respective devices and receiving scattered light by the respective devices, thereby improving redundancy with respect to defects, and improves a detectability by increasing an integration amount of respective measurement signals. | 04-19-2012 |
| 20110241955 | ANTENNA AND MANUFACTURING METHOD THEREFOR - Provided is an antenna capable of establishing electrical conductivity between a flange-like short-circuit section of a power supply section and a thin metal plate even in a harsh temperature environment in a space environment. Under a state in which an apical portion of a power supply section is inserted from an outer side of a face plate into a hole for the power supply section of a thin metal plate, a dielectric plate, and a metal plate, a plurality of screws are inserted from the outer side of a flange-like short-circuit section through a plurality of insertion holes of the flange-like short-circuit section, the thin metal plate, and the dielectric plate, and the plurality of screws are threadingly inserted into a plurality of tapped holes of the metal plate so that electrical conductivity between the flange-like short-circuit section and the thin metal plate is established through direct contact. | 10-06-2011 |
| 20110214410 | PROPELLANT TANK AND VAPOR JET EMITTING DEVICE INCLUDING SAME - A propellant tank for storing a liquid propellant A and supplying vapor produced by evaporation of part of the liquid propellant A to an external location comprises a tank body for storing the liquid propellant A, a mesh member arranged inside the tank body to cover a liquid surface of the liquid propellant A to divide an interior of the tank body into a liquid propellant storing area LA and a gas storing area GA by utilizing surface tension of the liquid propellant, and a heater arranged to a gas storing area GA side of the tank body to keep the gas storing area GA at higher temperature than temperature in the liquid propellant storing area LA. The tank body has a propellant inlet open into the liquid propellant storing area LA and a gas outlet open into the gas storing area GA. | 09-08-2011 |
| 20110214408 | LIQUID PROPELLANT TANK AND VAPOR JET EMITTING DEVICE INCLUDING SAME - A liquid propellant tank for storing a liquid propellant A and supplying vapor produced by evaporation of part of the liquid propellant A to an external location comprises a tank body for storing the liquid propellant A, and a plurality of holder plates arranged inside the tank body, around an axis L of the tank body. The holder plates cause the liquid propellant A to adhere to them by surface tension, thereby establishing, inside the tank body, a liquid propellant holding area LA in which the liquid propellant A is held and a gas accumulation area GA in which vapor produced by evaporation of part of the liquid propellant A accumulates. The tank body has a propellant inlet open into the liquid propellant holding area LA and a gas outlet open into the gas accumulation area GA. | 09-08-2011 |
| 20110167870 | TITANIUM-CONTAINING OXIDE GLASS AND METHOD FOR PRODUCTION THEREOF - A titanium-containing oxide glass having a bulky form and substantially having a chemical composition represented by the formula: (M | 07-14-2011 |
| 20110165809 | SOLUBLE TERMINALLY MODIFIED IMIDE OLIGOMER USING 2-PHENYL-4, 4'-DIAMINODIPHENYL ETHER, VARNISH, CURED PRODUCT THEREOF, IMIDE PREPREG THEREOF, AND FIBER-REINFORCED LAMINATE HAVING EXCELLENT HEAT RESISTANCE - A novel terminally modified imide oligomer having excellent solubility in organic solvents, excellent solution storage stability, and excellent molding properties such as low melt viscosity. Also, a varnish obtained by dissolving the terminally modified imide oligomer in an organic solvent; a cure product obtained by using the terminally modified imide oligomer and having excellent thermal and mechanical characteristics such as heat resistance, elastic modulus, tensile strength at break and tensile elongation at break; a prepreg; and a fiber-reinforced laminate. The soluble terminally modified imide oligomer is represented by general formula (1). In the formula, R | 07-07-2011 |
| 20110111947 | DIELECTRIC CERAMIC COMPOSITION AND ELECTRONIC COMPONENT - The disclosed is a dielectric ceramic composition in which dielectric particles | 05-12-2011 |
| 20110110018 | HEXAGONAL TYPE BARIUM TITANATE POWDER, PRODUCING METHOD THEREOF, DIELECTRIC CERAMIC COMPOSITION AND ELECTRONIC COMPONENT - Dielectric ceramic composition includes a hexagonal type barium titanate as a main component shown by a generic formula (Ba | 05-12-2011 |
| 20110086455 | GYROSCOPE - To provide a compact and high performance gyroscope. | 04-14-2011 |
| 20110059838 | DIELECTRIC CERAMIC COMPOSITION - Dielectric ceramic composition comprising a barium titanate including barium titanate having hexagonal structure as a main component, and an element “M”, an effective ionic radius of the “M” is within ±20% with respect to an effective ionic radius of 12-coordinated Ba | 03-10-2011 |
| 20110027102 | COOLING STRUCTURE OF TURBINE AIRFOIL - A cooling structure of a turbine airfoil cools a turbine airfoil ( | 02-03-2011 |
| 20110006970 | WIDE-BAND FEEDER CIRCUIT AND ANTENNA HAVING THE SAME - 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. | 01-13-2011 |
| 20100308135 | STAGING FUEL NOZZLE - 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”. | 12-09-2010 |
| 20100244565 | POWER SUPPLY CONTROLLER - Main arrays (MA | 09-30-2010 |
| 20100162819 | ACOUSTIC MEASUREMENT DEVICE AND ACOUSTIC MEASUREMENT METHOD - 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. | 07-01-2010 |
| 20100022379 | OPTICAL ELEMENT, TITANIUM-CONTAINING OXIDE GLASS USED FOR THE OPTICAL ELEMENT, AND LIGHT EMITTING METHOD AND LIGHT AMPLIFYING METHOD USING THE TITANIUM-CONTAINING OXIDE GLASS - 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. | 01-28-2010 |
| 20100012772 | PRESSURE TIGHT LARGE-SCALED MEMBRANE STRUCTURE - 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. | 01-21-2010 |
| 20100006697 | LOW NOISE AIRCRAFT - A low noise aircraft which can reduce engine noise on the ground sharply at the time of take-off and landing by utilizing a well-known mechanism. By utilizing a thrust deflection means constituted of a well-known mechanism for making the direction of thrust variable, exhaust direction of an engine is deflected to the upper side (upward) of the course direction (flight direction) of the aircraft so that the maximum propagation direction of the engine jet exhaust noise is kept away from the ground, thus reducing the engine noise level on the ground at the time of aircraft take-off and landing. In particular, when the thrust deflection type exhaust nozzle ( | 01-14-2010 |
| 20100003514 | Titanium-Containing Oxide Glass and Method for Production Thereof - A titanium-containing oxide glass having a bulky form and substantially having a chemical composition represented by the formula: (M1) | 01-07-2010 |
| 20090226297 | HIGH BYPASS-RATIO TURBOFAN JET ENGINE - To provide a turbofan jet engine which is capable of increasing the bypass ratio without increasing the fan diameter, and of reducing air resistance acting on the engine, a front fan duct that discharges air compressed by a front fan to the atmosphere and an aft fan duct that introduces air into an aft fan are disposed such as to change cross-sectional shapes thereof by rotating around a core engine in a counterclockwise direction, so that the cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately posterior to the front fan and a cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately anterior to the aft fan are inverted. | 09-10-2009 |
| 20090218449 | ATTITUDE CONTROL DATA CREATING METHOD, AND ATTITUDE CONTROL SYSTEM APPLYING THE METHOD - In order to control an attitude of a movable object having a flexible member ( | 09-03-2009 |
| 20090115661 | POSITIONAL INFORMATION PROVIDING SYSTEM, POSITIONAL INFORMATION PROVIDING APPARATUS AND TRANSMITTER - Positional information is provided at a place out of reach of radio wave. The process executed by a positional information providing apparatus includes the steps of: obtaining a received positioning signal (S | 05-07-2009 |
| 20090106633 | METHOD AND APPARATUS FOR CORRECTING AND DETECTING MULTIPLE SPOTTY-BYTE ERRORS WITHIN A BYTE OCCURRED IN A LIMITED NUMBER OF BYTES - An apparatus for correcting and detecting multiple spotty-byte errors within a byte occurred in a limited number of bytes and which has a function capable of controlling multiple spotty-byte errors within a byte occurred in the limited number of bytes, is provided. | 04-23-2009 |
| 20090007541 | THRUSTER USING NITROUS OXIDE - A thruster is provided that makes it possible to reduce and eventually eliminate the toxicity of storable liquid propellant and improve the low-temperature environment adaptability of propulsion system using the storable liquid propellant. The thruster produces thrust by using catalytic decomposition gas obtained by catalytically decomposing nitrous oxide with a nitrous oxide decomposition catalyst. | 01-08-2009 |
| 20080257525 | THERMAL CONTROL APPARATUS - Disclosed is a thermal control apparatus which comprises a base plate associated with a target object in a heat-exchangeable manner therebetween, at least one heat-exchange paddle attached to the base plate in such a manner as to be selectively deployed and retracted, paddle drive means provided at an end of the base plate and adapted to drive a deployment movement and a retraction movement of the heat-exchange paddle so as to change an angle of the heat-exchange paddle, and a heat transport element provided to connect the base plate and the heat-exchange paddle. | 10-23-2008 |
| 20080223017 | HALL-TYPE ELECTRIC PROPULSION - The present invention provides a hall-type electric propulsion that exhibits both overheating protection and operational stability, thereby simultaneously solving the problem of waste heat, which worsens with micronization, and the problem of discharge current oscillation. First, the magnetic flux distribution in ionization/acceleration channel is formed to optimize ion velocity vector, whereupon a propellant flow passage (propellant conduit) is disposed in a magnetic pole of the propulsion, or more specifically in the vicinity of the acceleration channel, and then propellant is passed through the flow passage. Thus, the magnetic pole, which is overheated by the generated plasma, can be cooled, and at the same time the propellant can be heated. Furthermore, the heated propellant is choked immediately before being introduced into the ionization/acceleration channel by a throat region provided immediately before the ionization/acceleration channel, and as a result the sonic speed of neutral species (propellant) is increased. | 09-18-2008 |
| 20080213926 | METHOD FOR EVALUATING A SEMICONDUCTOR SUBSTRATE - A method for evaluating a semiconductor substrate is provided that can evaluate even a thin semiconductor substrate or a substrate with untreated surfaces, can evaluate a large quantity of semiconductor substrates for solar cells in a short time and can be used as in-line inspection in a production process of solar cells or the like. The method for evaluating a semiconductor substrate comprises a step of immersing a semiconductor substrate in an etching solution filled in a container, a step of irradiating the substrate being immersed in the etching solution with light via the etching solution to cause the substrate to emit photoluminescence, and a step of observing the emitted photoluminescence. | 09-04-2008 |
