Japan Aerospace Exploration Agency Patent applications |
Patent application number | Title | Published |
20160118817 | CHARGE-DISCHARGE DEVICE WITH EQUALIZATION FUNCTION USING BOTH CONVERTOR AND MULTI-STAGE VOLTAGE DOUBLER RECTIFIER CIRCUIT - The disclosure describes a charge device capable of charging electricity storage cells while eliminating a voltage variation among the electricity storage cells without a need for at least a circuit section playing a role in voltage equalization among the electricity storage cells to be designed to have a large current capacity, and describes a charge-discharge device constructed by additionally equipping a discharging function with the charge device. Provided are a charge device and a charge-discharge device each of which comprises a convertor, an input circuit, and a multi-stage voltage doubler rectifier circuit. An element in the convertor configured to be applied with a rectangular waveform voltage is connected to the multi-stage voltage doubler rectifier circuit via the input circuit to thereby realize a voltage equalization function, and an output section of the convertor is connected to the multi-stage voltage doubler rectifier circuit to thereby realize a charging-discharging function. | 04-28-2016 |
20150082797 | FUEL INJECTION DEVICE - A fuel injection device for supplying a fuel to a compressed air includes: a pilot fuel injector; a main fuel injector located at an outer periphery of the pilot fuel injector; and an air injection unit located between an outlet end portion of the pilot fuel injector and the main fuel injector. The air injection unit includes: a partition wall plate separating the air injection unit from a combustion chamber; a flame stabilization plate provided at a downstream side of the partition wall plate; a first opening at a downstream side between the flame stabilization plate and the outlet end portion of the pilot fuel injector; and a second opening provided in the partition wall plate and through which the compressed air is supplied. The flame stabilization plate includes an inclined portion inclined in a radially outward and downstream direction with respect to an axis. | 03-26-2015 |
20150048177 | EXHAUST NOZZLE AND METHOD FOR CHANGING EXHAUST FLOW PATH - Provided is an exhaust nozzle and a method for changing an exhaust flowpath, whereby noise can be reduced by using a simple and light-weight mechanism without increasing the complexity and size of the structure of the exhaust nozzle, and furthermore, the efficiency during cruising at supersonic speeds can be improved. The rear end side of main nozzle pieces | 02-19-2015 |
20140257599 | ELECTRIC PROPULSION SYSTEM CONTROL APPARATUS - The present invention provides an electric propulsion system control apparatus that uses electric means alone so that effects pertaining to weight and cost are suppressed, is capable of accurate detection even when an airspeed has a binary relationship with a torque and a rotation speed of a propeller, and thereby exhibits improved detection precision and responsiveness. The electric propulsion system control apparatus drives a propulsion propeller to rotate, and is configured to estimate the airspeed from a data set stored in advance in relation to the airspeed and a propeller characteristic, and a plurality of torque and rotation speed estimation values detected under different driving conditions. | 09-11-2014 |
20140240147 | APPARATUS AND METHOD FOR SUPPORTING DISTRIBUTION FROM AIRCRAFT - When distribution material is distributed over a target site on a ground surface from an aircraft, a distribution supporting apparatus offers support information to a pilot dropping the distribution material to efficiently distribute the distribution material. The distribution supporting apparatus includes: an input section to which information items on at least an aircraft velocity, an aircraft altitude, and a wind velocity are input; a computation section configured to compute a location at which the distribution material dropped from the aircraft arrives on the ground surface and a density distribution of the distribution material on the ground surface based on the information items input to the input section; and a display control section configured to display, on a display, the support information relating to the location and density distribution computed by the computation section. | 08-28-2014 |
20140196436 | OPERATION STABILIZATION METHOD AND OPERATION STABILIZATION APPARATUS FOR SUPERSONIC INTAKE - An object of the present invention is to provide a technique of enlarging a stable operating range of an intake in accordance with an operating condition of an engine without using a complicated control system so that a wide operating range of the engine can be covered. In an operation stabilization method for a supersonic intake according to the present invention, an enlarged duct between a cowl and a ramp of the intake is divided by a splitter plate such that an opening angle of the enlarged duct decreases. Further, in the operation stabilization method for a supersonic intake according to the present invention, when the duct is divided by the splitter plate, the splitter plate is disposed such that, from among a cowl side duct and a ramp side duct, cross-section variation in one duct, in which an effect of a flow is larger, is reduced within an allowable range of total pressure loss in the other duct. | 07-17-2014 |
20140093795 | REGENERATIVE FUEL CELL SYSTEM - The reservoirs | 04-03-2014 |
20140083105 | GAS TURBINE COMBUSTOR - An annular type gas turbine combustor having a plurality of fuel nozzle assemblies ( | 03-27-2014 |
20140011950 | RESIN-TRANSFER-MOLDABLE TERMINAL-MODIFIED IMIDE OLIGOMER USING 2-PHENYL-4,4' DIAMINODIPHENYL ETHER AND HAVING EXCELLENT MOLDABILITY, MIXTURE THEREOF, VARNISH CONTAINING SAME, AND CURED RESIN THEREOF AND FIBER-REINFORCED CURED RESIN THEREOF MADE BY RESIN TRANSFER MOLDING AND HAVING EXCELLENT HEAT RESISTANCE - A novel resin-transfer-moldable terminal-modified imide oligomer having a residue of a tetravalent aromatic tetracarboxylic acid and represented by general formula (1), and the imide oligomer contains an oligomer where n is 0 in an amount of 10% by mole or more. | 01-09-2014 |
20130214094 | NOSE FOR SUPERSONIC FLYING OBJECT - Provided is a nose for a supersonic flying object, which has a natural laminar flow nose shape capable of suppressing laminar-turbulent transition and drastically reducing a frictional drag. The nose for a supersonic flying object has a low resistive body shape symmetrical about a central axis as a base shape, wherein the base shape is approximately a cone shape having a linear, simple convex curve, or simple concave curve generatrix and a deformation element having a wavy shape is added to the base shape. | 08-22-2013 |
20130184141 | PROCESS FOR PRODUCING CERAMIC FIBER-REINFORCED COMPOSITE MATERIAL AND CERAMIC FIBER-REINFORCED COMPOSITE MATERIAL - To obtain a ceramic fiber-reinforced composite material, by melt-infiltrating a composite material substrate obtained by forming ceramic fibers into a composite with a matrix formed of an inorganic substance, with an alloy having a composition that is constituted by a disilicate of at least one or more transition metal among transition metals that belong to Group 3A, Group 4A or Group 5A of the Periodic Table and silicon as the remainder, and having the silicon content ratio of 66.7 at % or more. | 07-18-2013 |
20130100688 | LASER LIGHT REFLECTION METHOD AND DEVICE FOR AIRCRAFT-INSTALLED LASER APPARATUS - A laser light reflection device for an aircraft-installed laser apparatus with which, when a function check is performed on the aircraft-installed laser apparatus by emitting laser light from a parked aircraft to a body exterior, the emitted laser light can be reflected in a desired direction safely and efficiently. A reflection mirror is capable of autorotation about at least an in-plane horizontal axis thereof, and a support ring is attached to the reflection mirror to be capable of rotating about an in-plane vertical axis and the in-plane horizontal axis of the reflection mirror. A laser pointer unit formed by inserting a laser pointer into a sleeve pipe is attached to the support ring so as to be oriented toward an in-plane of the reflection mirror. A guide scope is attached to the support ring such that an optical axis thereof matches an optical axis of the laser pointer unit. | 04-25-2013 |
20130088705 | COLORED NOISE REDUCTION METHOD AND DEVICE FOR OPTICAL REMOTE AIRFLOW MEASUREMENT APPARATUS - A colored noise reduction method for an optical remote airflow measurement apparatus, which emits laser light into the atmosphere as a transmission signal and measures a wind speed of an airflow in a remote region on the basis of a Doppler shift amount of a frequency between the transmission signal and a reception signal, includes: considering a signal strength of scattered light to be substantially non-existent in a remotest region and beyond; calculating a noise distribution by performing processing to average the signal strength in respective Doppler frequency components divided at intervals of a certain frequency in the remotest measurement region and beyond, and performing subtraction processing in each of the Doppler frequency components on all signal strength distributions of the measurement region, which are obtained by dividing the noise distribution at intervals of a certain distance. | 04-11-2013 |
20120305673 | FUEL INJECTOR - A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the pilot injector includes: a center nozzle configured to eject air jet flowing straight in an axial direction on a central axis of the pilot injector; an inside swirler provided on a radially outer side of the center nozzle and configured to cause inflow air to swirl around the central axis; and a pilot fuel injecting portion configured to inject the fuel from between the center nozzle and the inside swirler to air flow in the center nozzle. | 12-06-2012 |
20120304649 | FUEL INJECTOR - A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the main injector includes: a first inflow channel through which the air having a major flow component in an axial direction is taken; a second inflow channel through which the air having a major flow component in a radial direction is taken and which causes the air therein to meet the air from the first inflow channel; and a main fuel injecting portion configured to inject the fuel only to the second inflow channel. | 12-06-2012 |
20120200163 | ELECTRIC ENERGY STORAGE APPARATUS CAPABLE OF AC OUTPUT - An electric energy storage apparatus can generate an AC output in a low-loss and low-noise manner without using a DC-DC converter or an inverter. The electric energy storage apparatus comprises: an electric energy storage module group formed by connecting in series electric energy storage modules each comprising one or more electric energy storage elements; a balancing circuit electrically connected to the electric energy storage module group and configured to adjust a voltage to be applied to each of the electric energy storage modules; a first switch group comprising switches each in a path connecting a first terminal and a terminal of one of the series-connected electric energy storage modules; and a second switch group comprising switches each in a path connecting a second terminal and a terminal of one of the series-connected electric energy storage modules. The electric energy storage apparatus may perform a switch changeover in the switch groups. | 08-09-2012 |
20120194138 | ELECTRIC ENERGY STORAGE SYSTEM WITH BALANCING CIRCUIT - An electric energy storage system is designed to equally utilize electric energy storage banks during charging/discharging, and keep fluctuation of an input voltage from a charger or an output voltage to a load, within an arbitrary range, while equally utilizing the electric energy storage banks during charging/discharging. The electric energy storage system comprises an electric energy storage module, a charger, a balancing circuit, a voltage detection section, taps led out, respectively, from one of opposite terminals of the electric energy storage module and/or the other terminal of the electric energy storage module and/or one or more of series-connection points between the electric energy storage units, through respective switches, and a switch control section for switching the switches such that one of the taps is connected to one of opposite terminals of the charger. The switch control section is operable to sequentially switch the switches according to progress of the charging. | 08-02-2012 |
20120193498 | DEPLOYABLE ANTENNA - A deployable antenna which has a larger aperture diameter by four-side links provided in at least three stages and which includes: six deployment link mechanisms ( | 08-02-2012 |
20120182544 | AIRBORNE LIDAR FOR DETECTING MATTER SUSPENDED IN AIR - An object of the present invention is to provide a device which detects matter suspended in air, represented by, for example, ice crystals, volcanic ash, in the forward direction of the flight of an aircraft. A method of detecting matter suspended in air of this invention is characterized in that, in airborne Doppler LIDAR using laser light, components of matter subjected to laser light reflection and scattering are remotely measured on a basis of an angular difference in planes of polarization of transmitted light which is laser light radiated into the atmosphere, and received light scattered by matter suspended in air in a remote region. | 07-19-2012 |
20120166148 | METHOD OF DESIGNING NATURAL LAMINAR FLOW WING FOR REYNOLDS NUMBERS EQUIVALENT TO ACTUAL SUPERSONIC AIRCRAFT - In designing supersonic aircrafts, a method of designing a natural laminar flow wing is provided which reduces friction drag by delaying boundary layer transition under flight conditions of actual aircrafts. A target Cp distribution on wing upper surface, suited to natural laminarization in which boundary layer transition is delayed rearward in desired Reynolds number states, is defined by a functional type having as coefficients parameters depending on each spanwise station, a sensitivity analysis employing a transition analysis method is applied to the parameters, and a search is performed for the optimum combination of parameters to delay transition rearward. | 06-28-2012 |
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 |