Abstract: A lubrication device for a helicopter including: an oil sump in which oil for lubrication is retained; a lubrication pump configured to suck the oil from the oil sump to discharge the oil; and a lubrication passage extending from the lubrication pump to a first lubrication target. The lubrication passage includes: a first supply port that supplies the oil to the first lubrication target; an oil reservoir provided upstream of the first supply port; and an opening provided upstream of the oil reservoir and above the oil reservoir. The first supply port is formed right above the first lubrication target.

Abstract: A permanent-magnet-synchronous electric motor control device includes: a reference voltage value calculation unit for calculating a reference voltage value; an output voltage value calculation unit for calculating an output voltage value on the basis of a voltage command; a current weakening command calculation unit for calculating a current weakening command on the basis of the reference voltage value and the output voltage value; a voltage command calculation unit for calculating the voltage command on the basis of the current weakening command; and a power converter for supplying power to a permanent-magnet-synchronous electric motor on the basis of the voltage command. The current weakening command calculation unit calculates the current weakening command in which a high-frequency component is amplified on the basis of the difference between the reference voltage value and the output voltage value.

Abstract: A lubrication device for a helicopter including: an oil sump in which oil for lubrication is retained; a lubrication pump configured to suck the oil from the oil sump to discharge the oil; and a lubrication passage extending from the lubrication pump to a first lubrication target. The lubrication passage includes: a first supply port that supplies the oil to the first lubrication target; an oil reservoir provided upstream of the first supply port; and an opening provided upstream of the oil reservoir and above the oil reservoir. The first supply port is formed right above the first lubrication target.

Abstract: A lubrication device for a helicopter including: an oil sump in which oil for lubrication is retained; a lubrication pump configured to suck the oil from the oil sump to discharge the oil; and a lubrication passage extending from the lubrication pump to a first lubrication target. The lubrication passage includes: a first supply port that supplies the oil to the first lubrication target; an oil reservoir provided upstream of the first supply port; and an opening provided upstream of the oil reservoir and above the oil reservoir. The first supply port is formed right above the first lubrication target.

Abstract: An electric power generating device for an aircraft, which is driven by an output of an aircraft engine, comprises an input shaft to which a driving force of the engine is transmitted; a transmission arranged with the input shaft; an electric power generator arranged with the input shaft and the transmission and driven by an output of the transmission; a driving force transmission mechanism disposed on a first end side of the input shaft in an axial direction thereof, the driving force transmission mechanism being configured to transmit the output from the transmission to the electric power generator; and a casing including a mounting section on the first end side of the input shaft in the axial direction, wherein the transmission includes an input section provided on a second end side of the input shaft in the axial direction, the input section being configured to receive as an input a rotational driving force from the input shaft, and an output section provided on the first end side of the input shaft in th

Abstract: In a toroidal continuously variable transmission including at least one transmission unit including: an input disc and an output disc disposed coaxially; and a power roller tiltably interposed between the input disc and the output disc and configured to transmit a driving force from the input disc to the output disc, an integrally rotating member disposed so as to be spaced apart in an axial direction from at least one disc of the input disc and the output disc of each transmission unit and configured to rotate together with the at least one disc, and an annular interposed member provided between the at least one disc and the integrally rotating member and configured to rotate together with the at least one disc, are provided, and the interposed member is formed with a balance adjustment portion capable of adjusting weight balance in a circumferential direction.

Abstract: A lubrication device for a helicopter including: an oil sump in which oil for lubrication is retained; a lubrication pump configured to suck the oil from the oil sump to discharge the oil; and a lubrication passage extending from the lubrication pump to a first lubrication target. The lubrication passage includes: a first supply port that supplies the oil to the first lubrication target; an oil reservoir provided upstream of the first supply port; and an opening provided upstream of the oil reservoir and above the oil reservoir. The first supply port is formed right above the first lubrication target.

Abstract: In a continuously variable transmission including: a first transmission unit including a first input disc and a first output disc disposed coaxially and a power roller tiltably interposed between these discs; and a second transmission unit disposed coaxially with the first transmission unit, including a second input disc and a second output disc disposed coaxially and a second power roller tiltably interposed between these discs, and disposed such that a back surface of the second input disc is opposed to a back surface of the first input disc, a tubular back surface cylinder wall is provided on each of the back surfaces of the first input disc and the second input disc so as to project therefrom.

Abstract: An electric power generating device for an aircraft, which is driven by an output of an aircraft engine, comprises an input shaft to which a driving force of the engine is transmitted; a transmission arranged with the input shaft; an electric power generator arranged with the input shaft and the transmission and driven by an output of the transmission; a driving force transmission mechanism disposed on a first end side of the input shaft in an axial direction thereof, the driving force transmission mechanism being configured to transmit the output from the transmission to the electric power generator; and a casing including a mounting section on the first end side of the input shaft in the axial direction, wherein the transmission includes an input section provided on a second end side of the input shaft in the axial direction, the input section being configured to receive as an input a rotational driving force from the input shaft, and an output section provided on the first end side of the input shaft in th

Abstract: An electric power generating device (1) capable of suppressing an increase of a frontal surface area of an aircraft engine includes a transmission (22) connected with a rotary shaft (9) of the engine (E), an electric power generator (34) driven by an output of the transmission (22), an input shaft (27) having a shaft axis extending in a direction crossing the rotary shaft (9) and connected with the rotary shaft (9), and a transmitting mechanism (21) connected with the input shaft (27) to drive the transmission (22) about an axis extending in a direction perpendicular to the input shaft (27). The transmission (22) and the electric power generator (34) are disposed spaced a distance from each other in a direction circumferentially of the rotary shaft (9).

Abstract: To provide an aircraft engine in which an accessory can be directly supported with no accessory gearbox intervening to thereby suppress an increase in size thereof, the aircraft engine (E) includes a take-out shaft (11) having a first end portion, connected with an engine rotary shaft (9) and extending in a radially outward direction, and also having a second end portion connected with an accessory (1), and a mounting pad (12) provided in an engine main body (EB) and to which the accessory (1) is fitted. The mounting pad (12) forms an outer perimeter of an opening (48) through which the take-out shaft (11) extends. The opening (48) is sealed by a covering (47), through which the take-out shaft (1) extends, and a sealing member (49) to seal between the covering (47) and the take-out shaft (11).

Abstract: In a continuously variable transmission including: a first transmission unit including a first input disc and a first output disc disposed coaxially and a power roller tiltably interposed between these discs; and a second transmission unit disposed coaxially with the first transmission unit, including a second input disc and a second output disc disposed coaxially and a second power roller tiltably interposed between these discs, and disposed such that a back surface of the second input disc is opposed to a back surface of the first input disc, a tubular back surface cylinder wall is provided on each of the back surfaces of the first input disc and the second input disc so as to project therefrom.

Abstract: In a toroidal continuously variable transmission including at least one transmission unit including: an input disc and an output disc disposed coaxially; and a power roller tiltably interposed between the input disc and the output disc and configured to transmit a driving force from the input disc to the output disc, an integrally rotating member disposed so as to be spaced apart in an axial direction from at least one disc of the input disc and the output disc of each transmission unit and configured to rotate together with the at least one disc, and an annular interposed member provided between the at least one disc and the integrally rotating member and configured to rotate together with the at least one disc, are provided, and the interposed member is formed with a balance adjustment portion capable of adjusting weight balance in a circumferential direction.

Abstract: An electric power generating device (1) capable of suppressing an increase of a frontal surface area of an aircraft engine includes a transmission (22) connected with a rotary shaft (9) of the engine (E), an electric power generator (34) driven by an output of the transmission (22), an input shaft (27) having a shaft axis extending in a direction crossing the rotary shaft (9) and connected with the rotary shaft (9), and a transmitting mechanism (21) connected with the input shaft (27) to drive the transmission (22) about an axis extending in a direction perpendicular to the input shaft (27). The transmission (22) and the electric power generator (34) are disposed spaced a distance from each other in a direction circumferentially of the rotary shaft (9).

Abstract: To provide an aircraft engine in which an accessory can be directly supported with no accessory gearbox intervening to thereby suppress an increase in size thereof, the aircraft engine (E) includes a take-out shaft (11) having a first end portion, connected with an engine rotary shaft (9) and extending in a radially outward direction, and also having a second end portion connected with an accessory (1), and a mounting pad (12) provided in an engine main body (EB) and to which the accessory (1) is fitted. The mounting pad (12) forms an outer perimeter of an opening (48) through which the take-out shaft (11) extends. The opening (48) is sealed by a covering (47), through which the take-out shaft (1) extends, and a sealing member (49) to seal between the covering (47) and the take-out shaft (11).

Abstract: The objective is to provide a method for rapidly, and highly accurately performing genetic detection of the cyclopiazonic acid-producing ability in a strain belonging to genus Aspergillus, etc. as well as a transformant (strain), etc. that does not produce cyclopiazonic acid or a precursor thereof, cycloacetoacetyl L-tryptophan (CAT). A polynucleotide encodes the following polypeptides: (1) a polypeptide comprising the amino acid sequence depicted in SEQ ID NO: 2; (2) a polypeptide comprising an amino acid sequence with one or several amino acids deleted, substituted or added in the amino acid sequence depicted in SEQ ID NO: 2 and having a polyketide synthase-nonribosomal peptide synthetase activity; or (3) a polypeptide having 90% or more homology (identity) as an overall average with the amino acid sequence depicted in SEQ ID NO: 2 and having a polyketide synthase-nonribosomal peptide synthetase activity.

Abstract: A saddle riding type vehicle capable of making turns by leaning a vehicle body includes a pair of rear wheels provided at opposite sides of the vehicle body, a pair of support mechanisms arranged to support the pair of rear wheels to be movable, independently of each other, up and down about a pivot axis relative to the vehicle body, an engine disposed forward of the pivot axis to produce a drive force, a differential mechanism arranged to distribute the drive force of the engine to the pair of rear wheels and to absorb a rotating speed difference between the pair of rear wheels at a time of making a turn, the differential mechanism including drive shafts arranged between the engine and the pivot axis, a pair of shaft drive mechanisms provided for the pair of rear wheels, respectively, and arranged to transmit the drive force of the differential mechanism to the pair of rear wheels, and a pair of constant velocity universal joints provided for the pair of shaft drive mechanisms, respectively, each including a

Abstract: A saddle riding type vehicle capable of making turns by leaning a vehicle body includes a pair of rear wheels provided at opposite sides of the vehicle body, a pair of support mechanisms arranged to support the pair of rear wheels to be movable, independently of each other, up and down about a pivot axis relative to the vehicle body, an engine disposed forward of the pivot axis to produce a drive force, a differential mechanism arranged to distribute the drive force of the engine to the pair of rear wheels and to absorb a rotating speed difference between the pair of rear wheels at a time of making a turn, the differential mechanism including drive shafts arranged between the engine and the pivot axis, a pair of shaft drive mechanisms provided for the pair of rear wheels, respectively, and arranged to transmit the drive force of the differential mechanism to the pair of rear wheels, and a pair of constant velocity universal joints provided for the pair of shaft drive mechanisms, respectively, each including a

Abstract: An outboard motor includes a case extending generally vertically and supported on a hull. An engine is supported at an upper end of the case. A propeller is supported by a lower end of the case. A drive shaft is supported within the case for rotation about a generally vertical axis. The driveshaft has an upper end operatively connected to the engine and a lower end operatively connected to the propeller. An upper portion of the case includes an elongate extruded portion having substantially the same cross-sectional shape along its length.

Abstract: An outboard drive includes a prime mover having an output shaft. A driveshaft is coupled with the output shaft. Both shafts having axes that extend at least generally parallel to each other. A propulsion device is coupled with the driveshaft. The prime mover rotates the output shaft to drive the propulsion device through the driveshaft. A speed change mechanism is positioned between the output shaft and the driveshaft. The speed change mechanism changes a rotational speed of the output shaft transmitted to the driveshaft.