Abstract: A charging adapter in one aspect includes a first coupler, a second coupler, a power delivery path, a converter, a communication circuit, a charging control circuit, a control power supply, a first switch, a first internal path, a second internal path, a second switch, and a starter circuit. The charging control circuit performs a charging control of a battery pack. The charging control includes switching the converter to a first state or a second state. The converter in the first state receives a DC voltage from a power delivery adapter through the first coupler, converts the DC voltage into a charging voltage for charging the battery pack, and outputs the charging voltage to the second coupler. The converter in the second state receives the DC voltage from the power delivery adapter through the first coupler and outputs the DC voltage to the second coupler.

Abstract: The space structure control system includes: a space structure; an artificial satellite connected to the space structure; and a propulsion device installed on the artificial satellite and configured to control an orbit and an attitude of the artificial satellite, in which the space structure includes a film-like structure, a solar reflectance control device that controls a spatial pattern of a solar reflectance in a reflecting mirror provided in the film-like structure, and a shape retaining device that is connected to the film-like structure, the propulsion device rotates the film-like structure to generate a centrifugal force, the solar reflectance control device controls a solar reflectance in the reflecting mirror to control a solar radiation pressure to be applied to the reflecting mirror, a three-dimensional shape of the film-like structure is controlled based on the centrifugal force generated by the rotation of the film-like structure and the solar radiation pressure, and the shape of the film-like st

Abstract: An artificial satellite and artificial satellite system has power transmission and reception efficiency and includes an expandable solar panel that generates power, expandable power transmitting antennas, and expandable beam members to connect the solar panel and the power transmitting antennas to each other. The beam members are expanded from being provided in the artificial satellite, on a plurality of rotational symmetry axes of an imaginary polyhedron formed with substantially a center of the artificial satellite as an origin. The beam members are arranged at substantially equal distances in directions of the rotational symmetry axes.

Abstract: A design support device (10) acquires conditions and spatial information for constructing a component, searches a database (20) for combinations of parts that satisfy the acquired conditions, displays on a display device a display screen showing the retrieved combinations of parts, determines the arrangement of the parts in the component based on the spatial information and the shape and dimension of each of the parts constituting a combination selected from among the combinations displayed on the display device, and displays on the display device the information indicating the determined arrangement.

Abstract: A charging adapter includes a first coupler, a second coupler, a power delivery path, an arithmetic circuit, and a transmission circuit. The first coupler is detachably coupled to a power delivery adapter. The power delivery adapter outputs a DC voltage. The second coupler is detachably coupled to a battery pack. The power delivery path electrically couples the first coupler to the second coupler. The arithmetic circuit calculates a control parameter of the power delivery adapter based on a state of the battery pack coupled to the second coupler. The transmission circuit transmits the calculated control parameter to the power delivery adapter through the first coupler.

Abstract: An electromagnetic wave processing system mounted on a spacecraft including a plurality of antennas includes: a measurement apparatus configured to process measurement signals of electromagnetic waves acquired by the plurality of antennas; an attitude detection apparatus configured to detect an attitude of the spacecraft; a rotation control apparatus configured to control rotation of the spacecraft; and a calculation apparatus. The rotation control apparatus rotates the spacecraft about a center of gravity around a plurality of rotational axes with respect to an inertial space. The measurement apparatus performs measurement at a plurality of attitudes changed by the rotation. The calculation apparatus calculates an intensity distribution of electromagnetic waves acquired by the plurality of antennas using an interference waveform obtained by multiplying measurement signals obtained from different antennas in the measurement signals obtained at the plurality of attitudes.

Abstract: An overboard detection system includes a fob to be carried by a user on a watercraft, an overboard sensor to detect a user overboard event when the user carrying the fob falls overboard, and a communicator on the watercraft to wirelessly communicate with the fob and to transmit a rescue intention notification indicating a rescue intention to the fob carried by the user involved in the overboard event. The fob includes a transmitter operable to provide the rescue intention notification to the overboard user upon reception of the rescue intention notification.

Abstract: A system for controlling a watercraft includes a sensor to detect a position of a watercraft user, and a controller. When the watercraft user is not in an allowed area including a watercraft operating position, the controller is configured or programmed to stop a marine propulsion device or control the marine propulsion device to decelerate a watercraft. When the watercraft user is in a first region, the controller is configured or programmed to control the marine propulsion device in accordance with how a watercraft operator is operated. When the watercraft user is in a second region farther from the watercraft operating position than the first region but within the allowed area, the controller is configured or programmed to lock the watercraft operator. The controller is configured or programmed to disable an operation performed on the watercraft operator while the watercraft operator is locked.

Abstract: When a joystick is positioned within a first dead zone including a neutral position, a controller pauses a shifting action and steering of a propulsion device regardless of a tilt operation and a twist operation of the joystick. When the joystick is positioned within a second dead zone located rearward of the first dead zone, the controller pauses the shifting action of the propulsion device regardless of the tilt operation of the joystick and controls the steering of the propulsion device in accordance with the twist operation of the joystick.

Abstract: This invention provides an in-wheel motor capable of increasing steering operability and ride comfort of a vehicle. A stator 21 of an in-wheel motor 20 comprises a stator housing 21a and a stator housing cover 21b. The stator housing 21a is formed of a tubular-shaped housing annular portion 21a1, a housing flat-plate portion 21a2, a fold-back portion 21a3, and a flange portion 21a4. In the stator housing 21a, a housing recessed portion 211 is formed of the housing flat-plate portion 21a2 and the fold-back portion 21a3. The housing recessed portion 211 is provided with a hub bearing mounting portion 216 on which a hub bearing 26 is mounted. The stator housing cover 21b is provided with an upper arm attachment portion 217 and a lower arm attachment portion 218 for attaching an upper arm 31 and a lower arm 32 of a suspension device 30.

Abstract: To provide a simply-structured multilayer electrostatic actuator that exhibits a sufficient stroke and a sufficient contraction force in a specific drive range, and rapidly hardens upon an attempt to widen the interval between electrodes beyond the drive range. A multilayer electrostatic actuator (1) is configured by a plurality of actuator parts (2a, 2b, 2c) each including: a first film (3a1, 3b1, 3c1) having a plurality of first connection regions (7a1, 7b1, 7c1) formed on one surface in a predetermined pattern; and a second film (3a2, 3b2, 3c2) connected to the first film via the first connection regions, and having a plurality of second connection regions (7a2, 7b2, 7c2) formed on a surface opposite to the first film in the identical pattern. The actuator parts are connected and layered via the second connection regions.

Abstract: Provided is a non-aqueous secondary battery that includes a positive electrode, a negative electrode, a separator, and a non-aqueous electrolyte. The positive electrode includes LiNixCoyMnzO2 (0.7<x<0.9, 0<y<0.2, 0<z<0.2) as a lithium-containing metal oxide, and when the positive electrode before and after cycle testing of the non-aqueous secondary battery is analyzed by powder X-ray diffraction using Cu-K? radiation, the rate of change of the c-axis lattice constant is 1.0% or less. The non-aqueous electrolyte includes 5-20% by volume of acetonitrile and has an ion conductivity of at least 10 mS/cm and less than 15 mS/cm at 20° C.

Abstract: A stereostructure spacecraft of the present invention comprises multiple deployable beam members, multiple tension members, and a spacecraft for storing the deployable beam members and the tension members. The stereostructure spacecraft is formed by deploying the deployable beam members and the tension members around the spacecraft. The deployable beam members stored in the spacecraft are deployed and arranged equidistantly in directions of multiple rotational symmetry axes, the rotational symmetry axes being rotational symmetry axes of a virtual polyhedron that is formed to have a substantial center of the spacecraft as an origin. The tension members support two end portions of two adjacent deployable beam members with tension. The respective end portions of the deployable beam members are simultaneously supported by three or more of the tension members.

Abstract: A lighting device includes: a light source that is disposed on one surface; a first reflective portion that reflects light from the light source toward a first direction that is one direction along the one surface and a second direction that is along the one surface and crosses the first direction; and a second reflective portion that is disposed on a side of the first reflective portion in the second direction and reflects light from the first reflective portion toward the first direction.

Abstract: An artificial satellite system according to the present invention includes first and second artificial satellites. An antenna of the first satellite transmits a radio wave (transmission signal) to the second satellite. An antenna of the second satellite receives the transmission signal. A software defined radio of the second satellite generates a signal having the same frequency and phase as the transmission signal has. The antenna of the second satellite transmits a radio wave of a signal generated by the second satellite to the first satellite. The antenna of the first satellite receives the radio wave (reception signal) transmitted by the second satellite. A data processing device of the first satellite determines a relative distance between the first and second satellites by using the difference between a transmission time of the transmission signal and a reception time of the reception signal and the phase difference between the transmission and reception signals.

Abstract: A rotary electrical machine comprises a cylindrical stator that generates a magnetic field, a rotor that generates torque through the magnetic field, and a housing that accommodates the stator. The housing comprises a housing body covering an outer circumferential part of the stator, and a housing lid part attached to one end side of the housing body. The stator comprises a stator core having a plurality of teeth, and a stator coil mounted on the stator core, and the stator coil has a plurality of windings wound onto the plurality of teeth, and a crossover wire connecting at least two of the plurality of windings. The crossover wire comprises an insertion mechanism that is provided to the housing lid part and electrically connects end parts of the windings and an end part of the crossover wire through insertion contact.

Abstract: The space structure control system includes: a space structure; an artificial satellite connected to the space structure; and a propulsion device installed on the artificial satellite and configured to control an orbit and an attitude of the artificial satellite, in which the space structure includes a film-like structure, a solar reflectance control device that controls a spatial pattern of a solar reflectance in a reflecting mirror provided in the film-like structure, and a shape retaining device that is connected to the film-like structure, the propulsion device rotates the film-like structure to generate a centrifugal force, the solar reflectance control device controls a solar reflectance in the reflecting mirror to control a solar radiation pressure to be applied to the reflecting mirror, a three-dimensional shape of the film-like structure is controlled based on the centrifugal force generated by the rotation of the film-like structure and the solar radiation pressure, and the shape of the film-like st

Abstract: The present invention provides a nonaqueous electrolyte solution which contains: a nonaqueous solvent containing acetonitrile and vinylene carbonate; and a compound represented by general formula (1) R1-A-R2 (wherein A represents a divalent group that has a structure represented by one of formulae (1-2) to (1-5); and each of R1 and R2 independently represents an aryl group, an alkyl group which may be substituted by a halogen atom, while having from 1 to 4 carbon atoms, an alkyl group, a vinylidene group which may be substituted by a halogen atom, or an aryl group which may be substituted by a halogen atom; or alternatively, R1 and R2 may combine with each other and form, together with A, a ring structure that may have an unsaturated bond). With respect to this nonaqueous electrolyte solution, the total content of the vinylene carbonate and the compound represented by general formula (1) is not less than 0.

Abstract: A method for producing a microbial oil includes genetically modifying a labyrinthulid which belongs to the genus Parietichytrium or the genus Schizochytrium by disrupting and/or silencing a ?4 desaturase gene, a C20 elongase gene, and/or a C18 elongase gene, or by being transformed with an ?3 desaturase gene; culturing the labyrinthulid; and collecting the microbial oil from the labyrinthulid. The labyrinthulid has an activity of synthesizing DHA via a PUFA-PKS pathway in an amount of not more than 1/100 of a total amount of DHA synthesized in the labyrinthulid or no activity of producing PUFAs via the PUFA-PKS pathway, and the labyrinthulid has an activity of producing PUFAs via an endogenous elongase-desaturase pathway.