Abstract: An image processing apparatus according to an embodiment includes processing circuitry configured: to obtain a medical image to be labeled; to obtain first image data taken by implementing a first imaging method; to specify a feature related to a first organ in the first image data; to receive an imaged range that is in second image data to be taken by implementing a second imaging method and is related to a second organ; to specify a feature related to the imaged range of the second organ corresponding to the imaged range of the second organ in the first image data; and to estimate an imaging parameter that corresponds to the imaged range of the second organ corresponding to the second imaging method, on the basis of the feature related to the first organ and the feature related to the imaged range of the second organ in the first image data.

Abstract: An aircraft can include a wing. The wing can include a tip. A winglet can be pivotably connected to the wing proximate the tip. A connecting member can be operatively connected to the wing and the winglet. The connecting member can include a flexible material with a super elastic material member operatively connected to the flexible material. Thus, the connecting member can allow passive movement of the winglet responsive to real-time operational forces acting upon the aircraft. In some arrangements, the flexible material can be a fabric, and the super elastic material member can be a wire. In some arrangements, the super elastic material member can be configured to exhibit a non-linear stiffness profile. The non-linear stiffness profile can include a region of quasi-zero stiffness. The stiffness profile of the super elastic material member can be selectively varied, such as by controlling a temperature of the super elastic material member.

Abstract: An aircraft can include a wing. A morphing member can be operatively connected to the wing. The morphing member can include a base and a shape memory material member operatively connected to the base. The base can be made of a flexible material. When the shape memory material member is activated, a shape of the morphing member can change. As a result, one or more aerodynamic characteristics of the aircraft can be changed. In some arrangements, the flexible material can be a fabric, and the shape memory material member can be a shape memory alloy wire.

Abstract: An electric pump system and method of operating the same involves pumping a fluid through a fluid passageway defined in a mechanical pump from a pump inlet to a hollow shaft of a motor, through the hollow shaft to an internal motor cavity defined by a housing of the motor, and through another fluid passageway defined in the motor housing and mechanical pump that leads to a pump outlet. The system and method further involve pumping the fluid through another fluid passageway defined in the mechanical pump from yet another pump inlet to the pump outlet. The temperature of fluid exiting the hollow shaft can be assessed and used by an electronic control unit (ECU) of the electric pump system to control the same. The electric pump system can be part of a cooling and lubrication system for an electric vehicle transmission, gearbox, differential or transfer case, for example.

Abstract: Systems, methods, and computer-readable media for driving polyphase motors are provided. A system is provided that may include an inverter with more than three phases, a stator with more than three phases, and a rotor with a number of poles. The geometry, construction, magnet flux distribution, and/or reluctance distribution can be varied between rotor poles. A method is provided that may control a system by selectively activating inverter half-bridges or other suitable inverter components, and energizing stator coils with different amplitude, which may result in non-repeating stator combined magnetic flux distribution, which may electromagnetically couple and produce torque on individual rotor poles, such as based on a pre-determined efficiency map.

Abstract: An electric pump system and method of operating the same involves pumping a fluid through a fluid passageway defined in a mechanical pump from a pump inlet to a hollow shaft of a motor, through the hollow shaft to an internal motor cavity defined by a housing of the motor, and through another fluid passageway defined in the motor housing and mechanical pump that leads to a pump outlet. The system and method further involve pumping the fluid through another fluid passageway defined in the mechanical pump from yet another pump inlet to the pump outlet. The temperature of fluid exiting the hollow shaft can be assessed and used by an electronic control unit (ECU) of the electric pump system to control the same. The electric pump system can be part of a cooling and lubrication system for an electric vehicle transmission, gearbox, differential or transfer case, for example.

Abstract: A lower sump is disposed at a bottom of a housing for an electric motor/stator and drive train of an electric vehicle. The lower sump is configured to accumulate coolant/lubricant fluid that has passed through windings of the electric motor/stator. The lower sump includes a portion configured to receive part of one or more drive gears for the drive train. An upper sump is disposed above the electric motor/stator and drive train and is configured to accumulate at least a portion of the fluid that has been moved by the drive gear(s). One or more electronically-controlled exit or entrance valves are configured to be positioned between the upper sump and one or more spaces adjacent to the windings. The one or more exit or entrance valves are configured to release the fluid from the upper sump to flow through the space(s) adjacent to the windings into the lower sump.

Abstract: An aircraft can include a wing. A morphing member can be operatively connected to the wing. The morphing member can include a base and a shape memory material member operatively connected to the base. The base can be made of a flexible material. When the shape memory material member is activated, a shape of the morphing member can change. As a result, one or more aerodynamic characteristics of the aircraft can be changed. In some arrangements, the flexible material can be a fabric, and the shape memory material member can be a shape memory alloy wire.

Abstract: An aircraft can include a wing. The wing can include a tip. A winglet can be pivotably connected to the wing proximate the tip. A connecting member can be operatively connected to the wing and the winglet. The connecting member can include a flexible material with a super elastic material member operatively connected to the flexible material. Thus, the connecting member can allow passive movement of the winglet responsive to real-time operational forces acting upon the aircraft. In some arrangements, the flexible material can be a fabric, and the super elastic material member can be a wire. In some arrangements, the super elastic material member can be configured to exhibit a non-linear stiffness profile. The non-linear stiffness profile can include a region of quasi-zero stiffness. The stiffness profile of the super elastic material member can be selectively varied, such as by controlling a temperature of the super elastic material member.

Abstract: The present utility model discloses a downlight that belongs to the technical field of downlights and is suitable for embedded tubes of different specifications; the downlight includes a lamp cup; a drive board is arranged inside the lamp cup, and a light source board is arranged below the drive board; a lampshade is arranged below the lamp cup, and two symmetrically arranged mounts are arranged on the lamp cup; and a spring is rotatably embedded in the mount.

Abstract: Systems, methods, and computer-readable media for driving polyphase motors are provided.

Abstract: The present invention relates to the field of alkylation catalysts, and disclosed are a composite ZSM-5 molecular sieve, a preparation method therefor, a catalyst and an application thereof. A single crystal of the composite ZSM-5 molecular sieve comprises a main crystal and a twin crystal; the main crystal and the twin crystal are both ZSM-5 crystals; a crystal plane [010] of the main crystal is covered by a crystal plane [100] of the twin crystal; and the ratio of the number of sinusoidal pore openings to the number of straight pore openings on the outer surface of the single crystal of the composite ZSM-5 molecular sieve is (0.7-10:1), and the molar ratio Y1 of an Si element to an Al element within 10 nm of the surface is (300-2000):1. The single crystal of the composite ZSM-5 molecular sieve of the present invention has a large ratio of the number of sinusoidal pore openings to the number of straight pore openings, and is aluminum-poor on the surface and aluminum-rich on the inside.

Abstract: The present utility model discloses a downlight that belongs to the technical field of downlights and is suitable for embedded tubes of different specifications; the downlight includes a lamp cup; a drive board is arranged inside the lamp cup, and a light source board is arranged below the drive board; a lampshade is arranged below the lamp cup, and two symmetrically arranged mounts are arranged on the lamp cup; and a spring is rotatably embedded in the mount.

Abstract: An aircraft can include a first wing and a second wing. The first wing can extend laterally from an aircraft body to a first tip, and the second wing can extend laterally from the aircraft body to a second tip. The aircraft can include a first end effector and a second end effector, each including a fore winglet and an aft winglet. The fore and aft winglets of the first end effector can be pivotably connected to the first tip. The fore and aft winglets of the second end effector can be pivotably connected to the second tip. The fore and aft winglets of the first and second end effectors can be independently operable. The first and second end effectors can be independently operable. A processor can be operatively connected to control movement of the fore and aft winglets of the first and second end effectors.

Abstract: An aircraft can include a first wing and a second wing. The first wing can extend laterally from an aircraft body to a first tip, and the second wing can extend laterally from the aircraft body to a second tip. The aircraft can include a first end effector and a second end effector, each including a fore winglet and an aft winglet. The fore and aft winglets of the first end effector can be pivotably connected to the first tip. The fore and aft winglets of the second end effector can be pivotably connected to the second tip. The fore and aft winglets of the first and second end effectors can be independently operable. The first and second end effectors can be independently operable. A processor can be operatively connected to control movement of the fore and aft winglets of the first and second end effectors.

Abstract: A terminal with a foldable screen and an antenna assembly thereof are disclosed. The antenna assembly includes a foldable frame and seven antenna modules. The frame includes a first side frame; a second side frame opposite to the first side frame, a third side frame, and a fourth side frame. A first antenna portion is disposed at a corner connecting the first side frame to the third side frame. A second antenna portion is disposed at a corner connecting the second side frame and the third side frame. A third antenna portion is disposed on the second sub-frame. Fourth, fifth, and sixth antenna portions are sequentially arranged on the fourth side frame. A seventh antenna portion is disposed on the fourth sub-frame. At least 2*2 MIMO configuration of WIFI frequency band and 4*4 MIMO configuration of 5G NR frequency band below Sub-6G frequency band are formed by the antenna modules.

Abstract: The present disclosure provides an antenna system including a non-metallic housing. The non-metallic housing includes a top edge portion, a bottom edge portion provided correspondingly to the top edge portion, and a first long side edge portion and a second long side edge portion that connect the top edge portion with the bottom edge portion. The antenna system further includes seven antenna units provided on a periphery of the non-metallic housing. Compared with the related art, the antenna system provided by the present disclosure, by providing seven antenna units on the periphery of the non-metallic housing, achieves 3.3-3.6 GHz-4×4 MIMO, WIFI-2×2 MIMO, GPS, and 2G, 3G and 4G mobile communications.

Abstract: The present disclosure provides an antenna system, including: a metal housing including a radiation frame and a grounded back shell; a circuit board located in the metal housing and including a radio frequency feeding source and a tunable capacitor; and an antenna unit connected to the radio frequency feeding source and configured to be coupled to the radiation frame. A fracture is formed between each of two ends of the radiation frame and the grounded back shell. The tunable capacitor is connected to the radiation frame so as to change an electrical length of the antenna system by switching to different capacitances. Compared with the related art, the antenna system provided by present disclosure, by providing the tunable capacitor as a tuner of the antenna system, not only can achieve that the radiation frequency of the antenna system covers 790-960 MHz and 1710-2690 MHz, but also has good radiation performance.

Abstract: A mobile communication device is provided. The mobile communication device includes: a metal housing, a diversity antenna unit, an integrated antenna unit, a first main antenna unit, a second main antenna unit, and a main board. Compared with the related art, with the antenna system provided by the present disclosure, the diversity antenna unit, the integrated antenna unit, the first main antenna unit, and the second main antenna unit constitute 4×4 MIMO of an LTE Band3 and an LTE Band7, so that performance of the medium frequency and high frequency is improved; and the integrated antenna unit and the second main antenna unit constitute 2×2 MIMO of the Wi-Fi5G, so that performance of the Wi-Fi5G is improved.

Abstract: A terminal with a foldable screen and an antenna assembly thereof are disclosed. The antenna assembly includes a foldable frame and seven antenna modules. The frame includes a first side frame; a second side frame opposite to the first side frame, a third side frame, and a fourth side frame. A first antenna portion is disposed at a corner connecting the first side frame to the third side frame. A second antenna portion is disposed at a corner connecting the second side frame and the third side frame. A third antenna portion is disposed on the second sub-frame. Fourth, fifth, and sixth antenna portions are sequentially arranged on the fourth side frame. A seventh antenna portion is disposed on the fourth sub-frame. At least 2*2 MIMO configuration of WIFI frequency band and 4*4 MIMO configuration of 5G NR frequency band below Sub-6G frequency band are formed by the antenna modules.