National Institute for Materials Science

Sumitomo Osaka Cement Co., Ltd.

Seiko Instruments Inc

Fdk Corporation

Mitsubishi Electric Corporation

Other

Toyo Ink Mfg. Co., Ltd.

University of California

Toyo Ink Manufacturing Company

Pioneer Corporation

University of Washington

Japan Science and Technology Agency

National Institute of Information and Communications Technology, Incorporated

Kayaba Industry Company, Ltd.

Sakai Chemical Industry Co., Ltd.

Kenji Kitamura

Shunji Takekawa

Sunao Kurimura

Yasunori Furukawa

Junichiro Ichikawa

Masaru Nakamura

Futoshi Yamamoto

Satoshi Oikawa

Hideki Hatano

Yasunari Mizoguchi

Katsuhiko Yamada

Takeya Shima

Takashi Kanou

Jun Osanai

Myeongkyu Lee

Satoru Tanaka

Takashi Yamaji

Kazuya Terabe

Shigeyuki Kimura

Ataru Chiba

Kunihisa Sekiguchi

Tatsuya Masamura

Hitoshi Maki

Venkatraman Gopalan

Xiaoyan Liu

Kazuta Takeno

Masahiro Tsuchiya

Hiroaki Takasu

Tetsuya Kawanishi

Yosuke Saito

Shigeki Kato

Kiyoshi Shimamura

Masayuki Izutsu

Takehiko Kitamori

Takeshi Yoshida

Takashi Fujii

Katsutoshi Kondou

Encarnacion Antonia Garcia Villora

Guozhong Cao

Kaoru Higuma

Shingo Mori

Takashi Kano

Makoto Kumatoriya

Akimitsu Mochizuki

Masayuki Ichioka

Hideto Noguchi

Hideki Yamada

Minoru Osada

Osamu Shiromaru

Mika Shiiki

Nobuo Iyi

Katsuki Tsuchiya

Mikio Geho

Masami Shirao

Shinichiro Chiku

Sumio Koiwa

Hiroshi Fudoji

Takenori Funatsu

Kazuma Mawatari

Toshiyuki Tsuchiya

Mika Takayanagi

Tsutomu Sawada

Takahiro Nagata

Takehiro Nishiyama

Yoichi Inuzuka

Ken Mizumukai

Yoshihisa Ito

Hiroshi Suenobu

Koji Takase

Koju Nonaka

Yutaka Kazoe

Shunichi Hishida

Yuriy Pihosh

Shoko Goto

Motoi Shitaka

Terence E Mitchell

Terrence E Mitchell

Yoshie Suzuki

Shigeyuki Tsunoda

Nobuo Ii

Tetsuo Mishina

Michiko Sato

Asuka Takahashi

Shun Mochizuki

Shunichi Hishita

Osamu Tabata

Xijun Li

Taki Matsumoto

Yoshiro Kaneko

Tamaki Shimura

A backup power supply device includes: a storage battery charged with power from an external power supply; charge switches for charging the storage batter; discharge switches that are made from a field-effect transistor and that discharge the storage battery to a load device; a control unit for controlling the charge switches and the discharge switches; and a discharge suppression section connected in series to the discharge switches. The discharge suppression section suppresses leakage of current from the storage battery only when the control unit charges the storage battery, and the battery voltage exceeds an input voltage and the difference voltage between the battery voltage and the input voltage is less than a prescribed value.

Backup power supply device

In an orbital attitude control device (), an ideal thrust axis direction calculator () calculates an ideal thrust axis direction based on information of a predetermined orbit, an ideal attitude calculator () calculates an ideal attitude of the satellite based on the ideal thrust axis direction and a solar direction, and a control torque calculator () calculates an ideal control torque that makes the attitude of the satellite follow the ideal attitude and a torque restraint plane in which the solar direction is orthogonal to a rotational axis of the solar array panel, defines an evaluation function obtained by weighting a distance from the ideal control torque and a distance from the torque restraint plane and then summing the weighted distances, and calculates the control torque that allows the drive constraint to be satisfied and the evaluation function to be minimized.

Orbital attitude control device, satellite, orbital attitude control method, and recording medium

A battery polarity determination circuit includes a battery accommodating unit including a first contact and a second contact to be in contact with respective electrode terminals of a battery, a control device that is connected via a resistor to a voltage lead-out point at which a voltage of the battery is led out and determines a polarity of the battery, a connection switching circuit capable of switching between a first connection state and a second connection state, and a diode having a cathode to be connected to a voltage read-in point at which the resistor and the control device are connected to each other, and an anode to be grounded, wherein the control device determines the polarity of the battery based on a voltage at the voltage read-in point according to the connection state of the connection switching circuit, and a forward voltage of the diode is set so that the voltage at the voltage read-in point is not less than a lower limit value of an absolute maximum rating of the control device.

Battery polarity determination circuit, charger, and electronic device

Battery charger

This chargeris provided with: a battery housing unitincluding a first contact Tand a second contact Twhich touch the respective electrode terminals of a battery BAT to be housed therein; a high-potential power supply lineand a low-potential power supply lineto which power for charging the battery BAT is supplied; a connection switching circuitcapable of switching between a first connection state in which the first contact Tis connected to the high-potential power supply lineand the second contact Tis connected to the low-potential power supply lineand a second connection state in which the second contact Tis connected to the high-potential power supply lineand the first contact Tis connected to the low-potential power supply line; and a control devicefor controlling the connection switching circuitto perform charging control on the battery BAT. The control deviceperforms preliminary charging on the battery BAT in the first connection state and, when a battery voltage VB does not exceed a set voltage VS, switches the connection state to the second connection state and performs preliminary and normal charging on the battery BAT.

Charger and charging method

An attitude control apparatus () includes an ideal thrust direction calculator (), an ideal attitude calculator (), a target attitude calculator (), and a torque calculator (). The ideal thrust direction calculator () calculates an ideal thrust direction of a thruster. The target attitude calculator () calculates a target attitude that is the attitude of a satellite in which a deviation from an ideal attitude is minimized within a movement limitation of an attitude control actuator () while a panel surface faces the sun. The torque calculator () calculates a torque for turning the satellite from an actual attitude to the target attitude and transmits a torque instruction to the attitude control actuator ().

Orientation control device, satellite, orientation control method, and program

A sorting mechanism includes a flap that selects a first path connecting from a battery outlet of a charging section to a battery inlet of a first compartment section as a path to introduce a first battery to the first compartment section in a case of housing the first battery in the first compartment section, and that selects a second path connecting from the battery outlet of the charging section to a battery inlet of a second compartment section as a path to introduce a second battery to the second compartment section in a case of housing the second battery in the second compartment section.

Automatic charger

A charger includes: a power supply device for charging a secondary battery; a power supply path that includes a first switch and a second switch, and supplies electric power from the power supply device to the secondary battery; a discharge circuit that includes a first resistor and a third switch, has one end connected to a connection point between the first switch and the second switch, and has the other end connected to a ground line; a short-circuit preventing circuit that includes a second resistor and a fourth switch, and is connected in parallel to the first switch; and a control device that controls open-close of each switch and acquires a voltage value V, wherein the control device detects a failure of each switch on a condition where the voltage value Vis different between a normal state and a failure state, in a combination of open-close control for each switch.

Charger having failure detection function and failure detection method

When calculating a gimbal angle trajectory that satisfies boundary conditions set by an attitude boundary condition setterof the ground station, a gimbal angle trajectory calculatorcalculates the gimbal angle trajectory that minimizes a period of an acceleration interval within a range that satisfies driving restrictions of a gimbal, based on a gimbal angle &#x3b8;of a start time and a gimbal angle &#x3b8;of a fixed interval of an attitude change. Also, the gimbal angle trajectory is calculated that minimizes a period of a deceleration interval within a range that satisfies the driving restrictions of the gimbal, based on the gimbal angle &#x3b8;of the fixed interval and a gimbal angle &#x3b8;of a completion time of the attitude change. The obtained &#x3b8;, &#x3b8;, &#x3b8;and an attitude change period &#x3c4; are transmitted to the artificial satellite as gimbal angle trajectory parameters, and the control moment gyros are controlled based on the gimbal angle trajectory parameters.

Artificial satellite, attitude control system, and attitude control method

A charging circuit includes a first power source circuit that supplies charging power to secondary batteries; a switch that controls the supply of the power; and a control device that performs switching control of the switch. The control device detects a voltage difference between the secondary batteries before starting charging; starts a timer and starts serial charging of the secondary batteries; on the condition that the voltage difference before the charging has been equal to or larger than a first threshold, if respective voltage values of the secondary batteries have both become equal to or larger than a second threshold before the timer expires, shortens a remaining time on the timer at that time point; and finishes the serial charging of the secondary batteries at the earlier of a time point when the secondary batteries have both become fully charged, or a time point when the timer has expired.

Charging circuit

In a satellite side, there are provided a satellite-side operation parameter storage and an operation planning unit; and on a ground side, there are provided a ground-side operation parameter setting unit, a ground-side operation parameter storage to store operation parameters the same as stored in the operation parameter storage of the satellite-side, and an operation plan estimation unit having the same function as that of the operation planning unit of the satellite side. The ground-side operation parameter setting unit determines operation parameters to be used for the operation plan; and when necessary, the ground-side operation parameter setting unit saves them to the ground-side operation parameter storage and uploads them to the satellite-side operation parameter storage. The ground-side operation plan estimation unit and the satellite-side operation planning unit each produce operation plans according to the same operation parameters.

Autonomous operation planning system for artificial satellite and operation planning apparatus therefor

A satellite comprises thrusters disposed with the firing directions each facing away from the mass center of satellite and different from each other. A control amount calculator calculates control amounts of the mean orbital elements from the mean orbital elements and the temporal change rates of the mean orbital elements set by an orbit determiner, and the target values. A distributor calculates firing timings and firing amounts of the thrusters for realizing the control amounts of the mean orbital elements by expressing a motion of satellite with orbital elements, solving an equation taking into account coupling of an out-of-plane motion and an in-plane motion due to thruster disposition angles and thruster firing amounts at multiple times, and combining one or more thruster firings controlling mainly an out-of-the-orbit-plane direction and one or more thruster firings controlling mainly an in-the-orbit-plane direction.

Orbit control device and satellite

A first proton-donating layer () is a layer having a proton-donative functional group on the surface, for example, a silicon oxide layer. A second proton-donating layer () is also a layer having a proton-donative functional group on the surface, for example, a silicon oxide layer. Negative surface charges are formed on the main surface section of a first base () and the main surface section of a second base (), and these negative charges increased the proton conductivity in an aqueous solution fed to a nano channel. Although, in the aqueous solution, proton migration through hopping between water molecules contributes to its diffusion, the negative charges formed on the main surfaces of the bases () attract protons in the aqueous solution, and the conduction of protons is efficiently achieved in 'high-speed transfer regions' formed in the vicinity of the proton-donating layers ().

Proton conductor and fuel cell

When the number of CMGs is represented by n (n is an integer of 4 or more), (n&#x2212;3) gimbal angles out of n gimbal angles corresponding to the n CMGs are set as free parameters, and an algebraic equation representing a relationship among three gimbal angles out of the n gimbal angles, the free parameters, and an angular momentum of all the CMGs is used to solve the algebraic equation while changing the free parameters within set ranges, to thereby obtain solutions of the gimbal angles of the plurality of CMGs required for achieving a given angular momentum.

Device for controlling attitude of spacecraft and method for calculating CMG gimbal angle

A substrate for surface enhanced Raman spectroscopy analysis (SERS) comprises a ferroelectric single crystal having polarization-inverted patterns of spontaneous polarizations including polarization-inverted portions and non-inverted polarization portions, and metallic dots positioned at only either one polarized surfaces of the polarization-inverted portions and the non-inverted polarization portions. The provided SERS substrate produces a high enhancement effect. A microfluidic device incorporating the SERS substrate is also provided.

Substrate for surface enhanced Raman spectroscopy analysis and manufacturing method of the same, biosensor using the same, and microfluidic device using the same

Growing community of inventors

Ibaraki, Japan

Kenji Kitamura