Abstract: A display screen generation apparatus includes: an acquisition portion acquiring for each of a plurality of print products produced through a plurality of processes, progress of the processes; and a display portion generating a display screen that displays for each of the plurality of print products, the process waiting to be executed, the process being executed, the process already executed, and the process not intended to be executed in a distinguishable manner from each other.

Abstract: A VTOL aircraft (moving object) includes: a first communication path allowing a cabin (passenger compartment) and a component compartment to communicate with each other; and a second communication path for opening the component compartment to the outside of a fuselage. A portion of air in the cabin flows through a first circulation path and returns to the cabin, and the remaining air in the cabin flows through the first communication path and is introduced into the component compartment. A portion of air in the component compartment flows through a second circulation path and returns to the component compartment, and the remaining air in the component compartment flows through the second communication path and is discharged to the outside of the fuselage.

Abstract: An aircraft includes: rotors each driven by an electric motor; a PCU that converts AC power output from a generator into DC power; an inverter that converts DC power supplied from the PCU into AC power and outputs the AC power to the electric motor; a DC wire that connects the PCU and the inverter; and an AC wire that connects the inverter and the electric motor. The AC wire is disposed in a direction orthogonal to a direction in which rotation shafts of the generator and a gas turbine extend.

Abstract: A mixer is mounted in an aircraft. A rear end part of a cylindrical portion of the mixer is divided by a guide vane into a plurality of divided tubular portions. In the plurality of divided tubular portions, a notch nozzle is formed on an outer wall of the cylindrical portion. A plurality of guide holes are formed to extend from the outer wall of the cylindrical portion to a rear end surface of the guide vane.

Abstract: Freezing of an electrical component of a VTOL rotor is prevented. The aircraft 100 includes a fuselage 12, a VTOL rotor 20 including one or more blades 23 that is supported on the boom 18 to be spaced apart from the fuselage for generating thrust in a vertical direction during take-off and landing, a motor 21 that is stored in the boom and is configured to cause the one or more blades to rotate, and an inverter 22 for controlling the motor, a detection unit 80 configured to detect a temperature of at least one apparatus of the motor or the inverter, and a control unit 99 configured to run the at least one apparatus based on a thrust request for a plurality of VTOL rotors and a detection result of the temperature.

Abstract: A mixer is mounted in an aircraft. A rear end part of a cylindrical portion of the mixer is divided by a guide vane into a plurality of divided tubular portions. In the plurality of divided tubular portions, a notch nozzle is formed on an outer wall of the cylindrical portion. A plurality of guide holes are formed to extend from the outer wall of the cylindrical portion to a rear end surface of the guide vane.

Abstract: An aircraft comprises a fuselage, a front wing and a rear wing that extends laterally from the fuselage for generating lift during cruise, a boom extending in a front-back direction supported by these wings to be spaced apart from the fuselage, at least one VTOL rotor supported on the boom and having one or more blades for generating thrust in a vertical direction during take-off and landing, and a cooling system within the boom including two radiators stored between an inlet and an outlet provided on the boom, to cool an element with a low control temperature and an element with a high control temperature, for example, a motor and an inverter, respectively, among electric elements of the at least one VTOL rotor by using a first radiator that is positioned on the inlet side and a radiator that is positioned on the outlet side among the two radiators.

Abstract: A cooling system includes a rotor (VTOL rotor, cruise rotor) for generating at least one of lift or thrust of an aircraft, a component group formed of a plurality of electrical components for rotating the rotor, and a cooling circuit for cooling the component group, wherein a plurality of the component groups corresponding to a plurality of the rotors are provided, and the plurality of component groups are cooled by the same cooling circuit.

Abstract: A semiconductor manufacturing system according to an embodiment includes: a controller configured to control a semiconductor manufacturing apparatus; and a server configured to bidirectionally communicate with the controller via a communication line. The server includes a first processor configured to: transmit a backup file creation request (signal) that sets data specific to each controller as a backup file and transmit a backup file acquisition request (signal) requesting acquisition of the created backup file; and receive the created backup file. The controller includes a second processor configured to: receive a request (signal) from the server; and create the backup file when receiving the backup file creation request (signal).

Abstract: A semiconductor manufacturing system according to an embodiment includes: a controller configured to control a semiconductor manufacturing apparatus; and a server configured to bidirectionally communicate with the controller via a communication line. The server includes a first processor configured to: transmit a backup file creation request (signal) that sets data specific to each controller as a backup file and transmit a backup file acquisition request (signal) requesting acquisition of the created backup file; and receive the created backup file. The controller includes a second processor configured to: receive a request (signal) from the server; and create the backup file when receiving the backup file creation request (signal).

Abstract: A seeding device 1 includes a seeder 3 that jets out a jet flow 2 containing oil particles and gas therein, and a tubular body 5, 23 surrounding the jet flow 2. The distance X from a starting end S of the jet flow 2 to the tip end T of the tubular body 5, 23 is set so that the progressing rate of atomization of the oil particles at the tip end T of the tubular body 5, 23 is a predetermined rate or less.

Abstract: While a light sheet is generated at a designated region, images of fluid flowing through the designated region are formed at different times. For an inspection region of the plurality of inspection regions defined in the images that has a degree of difference exceeding a threshold between the local flow velocity vector v(a, b, T) at a certain time T and a reference flow velocity vector v(a, b, T±) at times T± that are different from the certain time T, the flow velocity vector v(a, b, T) at the reference time T is corrected with the reference flow velocity vector v(a, b, T±).

Abstract: A particle photographing device 2 includes: an illumination optical system 13 that illuminates particles with sheet-like illumination light based on laser light from an end of an optical fiber 7; an imaging portion 6 that images the illuminated particles; and a regulation portion 14 that changes the distance between the end of the optical fiber 7 and the illumination optical system 13.

Abstract: A particle photographing device 2 includes: an illumination optical system 13 that illuminates particles with sheet-like illumination light based on laser light from an end of an optical fiber 7; an imaging portion 6 that images the illuminated particles; and a regulation portion 14 that changes the distance between the end of the optical fiber 7 and the illumination optical system 13.

Abstract: A seeding device 1 includes a seeder 3 that jets out a jet flow 2 containing oil particles and gas therein, and a tubular body 5, 23 surrounding the jet flow 2. The distance X from a starting end S of the jet flow 2 to the tip end T of the tubular body 5, 23 is set so that the progressing rate of atomization of the oil particles at the tip end T of the tubular body 5, 23 is a predetermined rate or less.

Abstract: While a light sheet is generated at a designated region, images of fluid flowing through the designated region are formed at different times. For an inspection region of the plurality of inspection regions defined in the images that has a degree of difference exceeding a threshold between the local flow velocity vector v(a,b,T) at a certain time T and a reference flow velocity vector v(a,b,T±) at times T± that are different from the certain time T, the flow velocity vector v(a,b,T) at the reference time T is corrected with the reference flow velocity vector v(a,b,T±).

Abstract: A particle image velocimetry system is provided which supplies tracer particles to a flow field around an object (12) from tracer particle supply means, takes an image of reflected light by imaging means (32A, 32B) by irradiating the tracer particles twice with laser light at different times, and determines a velocity vector of the flow field based on the two images obtained of the tracer particles. The two images are each divided into a plurality of test regions, and when first peak value (fp)/second peak value (sp)?1.2 is satisfied by comparison between a first peak value fp and a second peak value sp of a cross-correlation value of a luminance pattern of tracer particles in each test region of the two images, it is determined that the reliability of the velocity vector is high. Thus, it is possible to enhance the precision of measurement of the state of flow by reliably determining erroneous vectors.

Abstract: A device for measuring a sound source distribution in three-dimensional space is provided in which tracer particles included around an object are irradiated with a two-dimensional laser sheet within an x-y plane at two times separated by a short time interval, images of the irradiated tracer particles are taken, and two in-plane velocity components of the tracer particles in the laser sheet and one out-of-plane velocity component perpendicular to the laser sheet are measured based on the images taken. Further, the velocity field of the three velocity components in three-dimensional space is measured by obtaining three velocity components within a plurality of planes spaced apart in a z-axis direction perpendicular to the laser sheet and stacking the three velocity components within the plurality of planes in the z-axis direction. The sound source distribution around the object is measured from the velocity field.

Abstract: An imaging device can take an image of a flow field including tracer particles includes a compound-eye lens formed from a large number of monocular lenses, which take images of images taken by an imaging lens. Each of the multiple monocular lenses functions as one imaging device. This can enable measurement precision to be enhanced by suppressing the influence of ghost particles, while reducing the equipment cost by minimizing the number of imaging devices. A space for installing the imaging device can easily ensured. If a large number of imaging devices are used, not only do they require time and manpower for setting up, but there is also a possibility that the measurement precision will be degraded due to displacement of an axis of the imaging devices caused by vibration, etc. When the imaging device having the compound-eye lens is used, setup is simplified, and measurement precision can be ensured.

Abstract: Tracer particles together with air are jetted from a nozzle of a seeder into a hood, the air is guided by a collision surface of the hood, deflected to a downstream side in an airflow direction in a wind tunnel, and flows out into the wind tunnel through an opening of the hood. Tracer particles having a large diameter fly straightly without being drifted by the deflected air and collide with the collision surface and are trapped thereon and are prevented from being supplied into the wind tunnel. Tracer particles having a small diameter are drifted by the deflected air, thereby deflected, and supplied into the wind tunnel without collision with and adhesion to the collision surface.