Abstract: An aircraft engine apparatus (1) includes: a rotating shaft (6); a fan (10) driven by the rotating shaft; a fan case surrounding the fan; aircraft equipment (28) disposed upstream of the fan and, in a radial direction of the rotating shaft, disposed inward of a peripheral edge of the fan case; a casing (2) that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter (9) coupled to the rotating shaft and the fan; a second motive force transmitter (32) disposed inward of the first motive force transmitter in the radial direction of the rotating shaft and coupled to the rotating shaft and the aircraft equipment; and a support member (12) disposed between the first motive force transmitter and the second motive force transmitter, the support member coupling the casing and the aircraft equipment and supporting the aircraft equipment.

Abstract: A toroidal continuously variable transmission comprises an input disc and an output disc which are disposed to face each other; a power roller which is tiltably disposed between the input disc and the output disc and transmits a rotational driving force of the input disc to the output disc in a transmission ratio corresponding to a tilt motion angle of the power roller; a trunnion including a base on which the power roller is rotatably mounted, and a pair of side walls provided on both sides of the power roller in an axial direction of a tilt motion shaft of the power roller in such a manner that the pair of side walls extend upward from the base and face a peripheral surface of the power roller, and a beam mounted on the pair of side walls, the beam extending in the axial direction of the tilt motion shaft, on a side opposite to the base when viewed from a position of the power roller, wherein the beam includes a pair of contact portions, each of the contact portions being configured to contact an end surfac

Abstract: The present disclosures relates to a toroidal continuously variable transmission which includes: a rotating shaft; a pair of outside disks supported by a rotating shaft to rotate in synchronization with the rotating shaft; an inside disk supported by the rotating shaft to rotate relative to the rotating shaft; a pair of rolling bearing units, each including a radial rolling bearing capable of supporting an axial load to support the inside disk so that relative rotation with respect to the rotating shaft is possible; a plurality of power rollers arranged between the axial inside surfaces the outside disks and the axial outside surfaces of the inside disk to transmit power between them; and a preloading mechanism elastically pressing the outer ring of the radial rolling bearing in the axial direction.

Abstract: A position controller includes: an oil temperature acquisition unit that acquires information on an oil temperature of a hydraulic actuator; a position acquisition unit that acquires an actual value of an operation position of an object; a position control unit that calculates an operation command value for a control valve of the hydraulic actuator by closed-loop control so as to reduce a deviation between a target value of the operation position of the object and the actual value; and a gain setting unit that changes at least one gain of the closed-loop control so that sensitivity of the closed-loop control increases as the oil temperature decreases.

Abstract: A position controller that performs position control by outputting a drive signal to a control valve of a hydraulic actuator that changes an operation position of an object, includes: a position acquisition unit that acquires an actual value of an operation position of the object; a position control unit that calculates an operation command value for the control valve by closed-loop control so as to reduce a deviation between a target value of the operation position of the object and the actual value; and a vibration wave application unit that applies a vibration wave to a signal of the closed-loop control so that the operation command value vibrates at a predetermined frequency at start of the closed-loop control.

Abstract: A rotary-wing aircraft blade airfoil for use with a rotary-wing aircraft such as a helicopter. The airfoil satisfies the following four conditions: a first condition in which a blade thickness has its maximum value at a position within a range from 30% chord to 40% chord; a second condition in which a camber has its maximum value at a position within a range from 15% chord to 25% chord, and that a slope of the camber changes from decreasing into increasing at a position within a range from 45% chord to 55% chord; a third condition in which the upper blade height has its maximum value at a position within a range from 25% chord to 35% chord; and a fourth condition in which the lower blade height has its maximum value at a position within a range from 35% chord to 45% chord.

Abstract: A position controller includes: an oil temperature acquisition unit that acquires information on an oil temperature of a hydraulic actuator; a position acquisition unit that acquires an actual value of an operation position of an object; a position control unit that calculates an operation command value for a control valve of the hydraulic actuator by closed-loop control so as to reduce a deviation between a target value of the operation position of the object and the actual value; and a gain setting unit that changes at least one gain of the closed-loop control so that sensitivity of the closed-loop control increases as the oil temperature decreases.

Abstract: A position controller that performs position control by outputting a drive signal to a control valve of a hydraulic actuator that changes an operation position of an object, includes: a position acquisition unit that acquires an actual value of an operation position of the object; a position control unit that calculates an operation command value for the control valve by closed-loop control so as to reduce a deviation between a target value of the operation position of the object and the actual value; and a vibration wave application unit that applies a vibration wave to a signal of the closed-loop control so that the operation command value vibrates at a predetermined frequency at start of the closed-loop control.

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 aircraft engine apparatus (1) includes: a rotating shaft (6); a fan (10) driven by the rotating shaft; a fan case surrounding the fan from outside in a radial direction of the rotating shaft; a nose cone (13) disposed upstream of the fan; a casing (2) that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter (9) that transmits motive force of the rotating shaft to the fan; and a support member (12) disposed inward of the first motive force transmitter in the radial direction, the support member coupling the nose cone to the casing such that the support member supports the nose cone in a stationary state.

Abstract: The purpose of the invention is to achieve a structure that can be easily made smaller while maintaining transmission efficiency and durability. An inner disk 8b is supported around a sleeve 5a so as to be able to rotate relative to a rotational shalt 2b and the sleeve 5a by way of a pair of ball bearings 33 having a lace-to-face type contact angle. A pair of conical disc springs 36 are held between the inner face of an outer ring 35 of each of the pair of ball bearings 33 and an inner diameter side step face 30 on each of a pair of disk elements 7a, and a preload in the axial direction is applied to the pair of ball bearings 33 by elastically pressing the outer ring 35 to the outside.

Abstract: A toroidal continuously variable transmission comprises an input disc and an output disc which are disposed to face each other; a power roller which is tiltably disposed between the input disc and the output disc and transmits a rotational driving force of the input disc to the output disc in a transmission ratio corresponding to a tilt motion angle of the power roller; a trunnion including a base on which the power roller is rotatably mounted, and a pair of side walls provided on both sides of the power roller in an axial direction of a tilt motion shaft of the power roller in such a manner that the pair of side walls extend upward from the base and face a peripheral surface of the power roller, and a beam mounted on the pair of side walls, the beam extending in the axial direction of the tilt motion shaft, on a side opposite to the base when viewed from a position of the power roller, wherein the beam includes a pair of contact portions, each of the contact portions being configured to contact an end surfac

Abstract: An aircraft engine apparatus (1) includes: a rotating shaft (6); a fan (10) driven by the rotating shaft; a fan case surrounding the fan; aircraft equipment (28) disposed upstream of the fan and, in a radial direction of the rotating shaft, disposed inward of a peripheral edge of the fan case; a casing (2) that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter (9) coupled to the rotating shaft and the fan; a second motive force transmitter (32) disposed inward of the first motive force transmitter in the radial direction of the rotating shaft and coupled to the rotating shaft and the aircraft equipment; and a support member (12) disposed between the first motive force transmitter and the second motive force transmitter, the support member coupling the casing and the aircraft equipment and supporting the aircraft equipment.

Abstract: An aircraft engine apparatus (1) includes: a rotating shaft (6); a fan (10) driven by the rotating shaft; a fan case surrounding the fan from outside in a radial direction of the rotating shaft; a nose cone (13) disposed upstream of the fan; a casing (2) that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter (9) that transmits motive force of the rotating shaft to the fan; and a support member (12) disposed inward of the first motive force transmitter in the radial direction, the support member coupling the nose cone to the casing such that the support member supports the nose cone in a stationary state.

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: The present invention is related to a process oil using as a raw material a deasphalted oil obtained by deasphalting a vacuum residual oil of a crude oil and a manufacturing method of the process oil, the process oil having properties of: (a) a polycyclic aromatics (PCA) content of less than 3 mass %; (b) a viscosity (100° C.) of 40 to 70 mm2/s; (c) an aniline point of 85 to 100° C.; (d) a flash point of 250° C. or higher; (e) an aromatic hydrocarbon content of 40 to 55 mass %; and (f) a polar substance content of 10 to 15 mass %. The present invention is also related to a process oil and a manufacturing method of the process oil, the process oil obtained by mixing: an extract obtained by deasphalting and solvent-extracting a vacuum residual oil of a crude oil; and a lubricant base oil having a polycyclic aromatics (PCA) content of less than 3 mass %, and having properties of: (a) a polycyclic aromatics (PCA) content of less than 3 mass %; (i) a viscosity (100° C.

Abstract: The present invention is related to a process oil using as a raw material a deasphalted oil obtained by deasphalting a vacuum residual oil of a crude oil and a manufacturing method of the process oil, the process oil having properties of: (a) a polycyclic aromatics (PCA) content of less than 3 mass %; (b) a viscosity (100° C.) of 40 to 70 mm2/s; (c) an aniline point of 85 to 100° C.; (d) a flash point of 250° C. or higher; (e) an aromatic hydrocarbon content of 40 to 55 mass %; and (f) a polar substance content of 10 to 15 mass %. The present invention is also related to a process oil and a manufacturing method of the process oil, the process oil obtained by mixing: an extract obtained by deasphalting and solvent-extracting a vacuum residual oil of a crude oil; and a lubricant base oil having a polycyclic aromatics (PCA) content of less than 3 mass %, and having properties of: (a) a polycyclic aromatics (PCA) content of less than 3 mass %; (i) a viscosity (100° C.

Abstract: The present invention is related to a process oil using as a raw material a deasphalted oil obtained by deasphalting a vacuum residual oil of a crude oil and a manufacturing method of the process oil, the process oil having properties of: (a) a polycyclic aromatics (PCA) content of less than 3 mass %; (b) a viscosity (100° C.) of 40 to 70 mm2/s; (c) an aniline point of 85 to 100° C.; (d) a flash point of 250° C. or higher; (e) an aromatic hydrocarbon content of 40 to 55 mass %; and (f) a polar substance content of 10 to 15 mass %. The present invention is also related to a process oil and a manufacturing method of the process oil, the process oil obtained by mixing: an extract obtained by deasphalting and solvent-extracting a vacuum residual oil of a crude oil; and a lubricant base oil having a polycyclic aromatics (PCA) content of less than 3 mass %, and having properties of: (a) a polycyclic aromatics (PCA) content of less than 3 mass %; (i) a viscosity (100° C.

Abstract: The present invention is related to a process oil using as a raw material a deasphalted oil obtained by deasphalting a vacuum residual oil of a crude oil and a manufacturing method of the process oil, the process oil having properties of: (a) a polycyclic aromatics (PCA) content of less than 3 mass %; (b) a viscosity (100° C.) of 40 to 70 mm2/s; (c) an aniline point of 85 to 100° C.; (d) a flash point of 250° C. or higher; (e) an aromatic hydrocarbon content of 40 to 55 mass %; and (f) a polar substance content of 10 to 15 mass %. The present invention is also related to a process oil and a manufacturing method of the process oil, the process oil obtained by mixing: an extract obtained by deasphalting and solvent-extracting a vacuum residual oil of a crude oil; and a lubricant base oil having a polycyclic aromatics (PCA) content of less than 3 mass %, and having properties of: (a) a polycyclic aromatics (PCA) content of less than 3 mass %; (i) a viscosity (100° C.

Abstract: In this data processing device, a request for direct memory-access operation is detected as an interrupt signal. When such an interrupt is detected, a interrupt controller generates a vector corresponding to the interrupt sigal. On the basis of this vector, a DMA controller generates a control signal showing whether the interrupt signal is a normal interrupt or an interrupt for requesting the direct memory-access operation. A CPU includes a ROM for storing micro-code for achieving the direct memory-access operation. When the DMA controller generates a control signal corresponding to the interrupt signal, the CPU sequentially reads out the micro-codes, to execute the direct memory-access operation. Specifically, if an interrupt for requesting the direct memory-access operation is detected, different processing space from that used for a normal interrupt processing is accessed.