Abstract: Disclosed is a method for an all-laser hybrid additive manufacturing. After a matrix is obtained by means of selective laser melting forming, a subtractive forming is carried out on the matrix by means of a pulse laser to form a cavity, and the cavity is then packaged to obtain a forming material with an internal cavity structure. A laser precision packaging method is used in the method based on the melting of the laser selective region. Also disclosed is the apparatus, comprising a laser unit (2), a control unit (4) and a forming unit (6). The laser unit is in light path connection with the forming unit, and the control unit is electrically connected with the laser unit and the forming unit respectively. The laser unit comprises a first laser light source to and a second laser light source. The forming unit comprises a welding unit (68), and the welding unit is controlled by the control unit and is matched with the laser unit for the additive manufacturing.

Abstract: A turbine blade having a gas film cooling structure with a composite irregular groove. The turbine blade has a hollow structure, and a plurality of first grooves which are recessed grooves are provided on an outer surface thereof. A plurality of discrete holes A extending to an inner surface of the turbine blade are provided at the groove bottom of each first groove. The first groove is an irregular groove, and includes at least two portions in a depth direction. A portion having a depth H1 from the groove bottom of the first groove is a first portion, and the rest thereof is a second portion. At least one side surface of the second portion is formed by expanding in lateral direction from a corresponding side surface of the first portion.

Abstract: Disclosed are a method of flying on the moon and a device for flying using the method. A medium on a surface of a moon and a medium accelerating module are used in the flying method. The medium is transferred into the medium accelerating module, accelerated by the medium accelerating module, and ejected out of the medium accelerating module by using a power supply. A counterforce is generated in accordance with the momentum conservation, and the counterforce overcomes the lunar gravity and drives a load to take off. The method is suitable for the environment of the moon where flight by means of atmospheric buoyancy is impossible due to the shortage of atmosphere.

Abstract: A laser processing head (100) comprises a first-level nozzle (110) and a second-level nozzle (120) that communicate with each other, wherein the second-level nozzle (120) is arranged downstream of the first-level nozzle (110); an inner diameter of the second-level nozzle (120) gradually decreases in a laser transmission direction, and minimum inner diameter of the first-level nozzle (110) is larger than the inner diameter of a tail end of the second-level nozzle (120). The laser processing head (100) solves the contradiction between high energy density laser and the system reliability through gradual coupling. Also provided are a laser processing system and a laser processing method.

Abstract: A laser shock peening apparatus for the surface of a workpiece, said apparatus comprising a resonant cavity. When said apparatus is used to conduct laser shock peening, because of the presence of the resonant cavity, shock waves that would typically escape outward may instead be utilized, and composite shock waves may be formed as a result of the wave reflection and convergence effects of the resonant cavity. Said waves can then be used on the surface of a workpiece twice or multiple times, thereby greatly increasing energy utilization rates. In addition, a fluid-based confinement layer is limited to the inside of the resonant cavity and has a fixed shape, thereby effectively solving the problems of the poor stability of a fluid-based confinement layer and the difficulty with controlling the thickness of such a confinement layer.

Abstract: A turbine blade having a gas film cooling structure with a composite irregular groove. The turbine blade has a hollow structure, and a plurality of first grooves which are recessed grooves are provided on an outer surface thereof. A plurality of discrete holes A extending to an inner surface of the turbine blade are provided at the groove bottom of each first groove. The first groove is an irregular groove, and includes at least two portions in a depth direction. A portion having a depth H1 from the groove bottom of the first groove is a first portion, and the rest thereof is a second portion. At least one side surface of the second portion is formed by expanding in lateral direction from a corresponding side surface of the first portion.

Abstract: A laser shock peening apparatus for the surface of a workpiece, said apparatus comprising a resonant cavity. When said apparatus is used to conduct laser shock peening, because of the presence of the resonant cavity, shock waves that would typically escape outward may instead be utilized, and composite shock waves may be formed as a result of the wave reflection and convergence effects of the resonant cavity. Said waves can then be used on the surface of a workpiece twice or multiple times, thereby greatly increasing energy utilization rates. In addition, a fluid-based confinement layer is limited to the inside of the resonant cavity and has a fixed shape, thereby effectively solving the problems of the poor stability of a fluid-based confinement layer and the difficulty with controlling the thickness of such a confinement layer.

Abstract: Disclosed is a method for an all-laser hybrid additive manufacturing. After a matrix is obtained by means of selective laser melting forming, a subtractive forming is carried out on the matrix by means of a pulse laser to form a cavity, and the cavity is then packaged to obtain a forming material with an internal cavity structure. A laser precision packaging method is used in the method based on the melting of the laser selective region. Also disclosed is the apparatus, comprising a laser unit (2), a control unit (4) and a forming unit (6). The laser unit is in light path connection with the forming unit, and the control unit is electrically connected with the laser unit and the forming unit respectively. The laser unit comprises a first laser light source to and a second laser light source. The forming unit comprises a welding unit (68), and the welding unit is controlled by the control unit and is matched with the laser unit for the additive manufacturing.

Abstract: A laser shock peening apparatus for the surface of a workpiece, said apparatus comprising a resonant cavity. When said apparatus is used to conduct laser shock peening, because of the presence of the resonant cavity, shock waves that would typically escape outward may instead be utilized, and composite shock waves may be formed as a result of the wave reflection and convergence effects of the resonant cavity. Said waves can then be used on the surface of a workpiece twice or multiple times, thereby greatly increasing energy utilization rates. In addition, a fluid-based confinement layer is limited to the inside of the resonant cavity and has a fixed shape, thereby effectively solving the problems of the poor stability of a fluid-based confinement layer and the difficulty with controlling the thickness of such a confinement layer.

Abstract: The present disclosure discloses a method and apparatus for establishing a hard pipe in a network. The network includes multiple routers and a network management system. The method includes: acquiring, by the network management system, bandwidths of a plurality of links in the network; instructing, a router to allocate a fixed bandwidth from a bandwidth of the link of the network topology, where a link to which the fixed bandwidth is allocated forms a sublink, and the sublink and the router that allocates the sublink form a hard pipe stratum, which is used to carry a leased line service; and allocating, a static MPLS label set to the hard pipe stratum. A service packet that has an MPLS label in the static MPLS label set is forwarded by using the hard pipe stratum, thereby ensuring that a bandwidth of the leased line service is not occupied by a non-leased line service.

Abstract: The present application provides an HQoS control method, where the RSG is connected to multiple CSGs, and each CSG of the CSGs is connected to multiple base stations. The RSG configures a bandwidth limitation parameter for each CSG; creates different AAA domains for different IP address network segments, and configures a QoS scheduling parameter in each AAA domain; and determines, according to a configuration parameter of a first base station, a bandwidth limitation parameter of a CSG connected to the first base station, and determines a QoS scheduling parameter of the first base station, where the configuration parameter is used to indicate the CSG connected to the first base station and an AAA domain corresponding to the first base station. The present application greatly migrates a risk from excessively concentrated base station gateways, and ensures that a service packet securely traverses a layer 2 tunnel of a fixed network operator.

Abstract: Disclosed are the thermal protection and drag reduction method and system for an ultra high-speed aircraft. A cold source is and a cold source driving device are arranged inside a cavity of the ultra high-speed aircraft. A plurality of micropores are arranged on a wall surface of the cavity. The cold source driving device comprises an air pump, a cold source reservoir and a buffer. The air pump supplies compressed air to a cold source reservoir during operation. The cold source enters the buffer and is vaporized under the action of air pressure. High-pressure gas is ejected from the micropores to form a gas film on the outer surface of the cavity. The gas film not only can perform thermal protection on the ultra high-speed aircraft, but also can effectively reduce viscous drag between the aircraft and the external gas, by virtue of which the thermal barrier phenomenon is alleviated or eliminated. Therefore, security of the ultra high-speed aircraft is improved and service life is prolonged.

Abstract: A laser processing head (100) comprises a first-level nozzle (110) and a second-level nozzle (120) that communicate with each other, wherein the second-level nozzle (120) is arranged downstream of the first-level nozzle (110); an inner diameter of the second-level nozzle (120) gradually decreases in a laser transmission direction, and minimum inner diameter of the first-level nozzle (110) is larger than the inner diameter of a tail end of the second-level nozzle (120). The laser processing head (100) solves the contradiction between high energy density laser and the system reliability through gradual coupling. Also provided are an application of the laser processing head, a laser processing system and a laser processing method.

Abstract: The present disclosure discloses a method and apparatus for establishing a hard pipe in a network. The network includes multiple routers and a network management system. The method includes: acquiring, by the network management system, bandwidths of a plurality of links in the network; instructing, a router to allocate a fixed bandwidth from a bandwidth of the link of the network topology, where a link to which the fixed bandwidth is allocated forms a sublink, and the sublink and the router that allocates the sublink form a hard pipe stratum, which is used to carry a leased line service; and allocating, a static MPLS label set to the hard pipe stratum. A service packet that has an MPLS label in the static MPLS label set is forwarded by using the hard pipe stratum, thereby ensuring that a bandwidth of the leased line service is not occupied by a non-leased line service.

Abstract: A laser shock peening apparatus for the surface of a workpiece, said apparatus comprising a resonant cavity. When said apparatus is used to conduct laser shock peening, because of the presence of the resonant cavity, shock waves that would typically escape outward may instead be utilized, and composite shock waves may be formed as a result of the wave reflection and convergence effects of the resonant cavity. Said waves can then be used on the surface of a workpiece twice or multiple times, thereby greatly increasing energy utilization rates. In addition, a fluid-based confinement layer is limited to the inside of the resonant cavity and has a fixed shape, thereby effectively solving the problems of the poor stability of a fluid-based confinement layer and the difficulty with controlling the thickness of such a confinement layer.

Abstract: The present application provides an HQoS control method, where the RSG is connected to multiple CSGs, and each CSG of the CSGs is connected to multiple base stations. The RSG configures a bandwidth limitation parameter for each CSG; creates different AAA domains for different IP address network segments, and configures a QoS scheduling parameter in each AAA domain; and determines, according to a configuration parameter of a first base station, a bandwidth limitation parameter of a CSG connected to the first base station, and determines a QoS scheduling parameter of the first base station, where the configuration parameter is used to indicate the CSG connected to the first base station and an AAA domain corresponding to the first base station. The present application greatly migrates a risk from excessively concentrated base station gateways, and ensures that a service packet securely traverses a layer 2 tunnel of a fixed network operator.

Abstract: A process is provided for forming shaped air holes, such as for use in turbine blades. Aspects of the disclosure relate to forming shaped portions of air holes using a short pulse laser, forming a metered hole corresponding to each shaped portion, and separately finishing the shaped portion using a short-pulse laser. In other embodiments, the order of these operations may be varied, such as to form the shaped portions and to finish the shaped portions using the short-pulse laser prior to forming the corresponding metered holes.

Abstract: A heat exchange assembly for use in cooling an electrical component is described herein. The heat assembly includes a casing that includes an evaporator section, a condenser section, and a transport section extending between the evaporator section and the condenser section along a longitudinal axis. The casing is configured to bend along a bending axis oriented with respect to the transport section. The casing also includes at least one sidewall that includes at least one fluid chamber extending between the evaporator section and the condenser section to channel a working fluid between the evaporator section and the condenser section. A plurality of fluid channels are defined within the inner surface to channel liquid fluid from the condenser section to the evaporator section. At least one vapor channel is defined within the inner surface to channel gaseous fluid from the evaporator section to the condenser section.

Abstract: A heat exchange assembly for use in cooling an electrical component is described herein. The heat assembly includes a casing that includes an evaporator section, a condenser section, and a transport section extending between the evaporator section and the condenser section along a longitudinal axis. The casing is configured to bend along a bending axis oriented with respect to the transport section. The casing also includes at least one sidewall that includes at least one fluid chamber extending between the evaporator section and the condenser section to channel a working fluid between the evaporator section and the condenser section. A plurality of fluid channels are defined within the inner surface to channel liquid fluid from the condenser section to the evaporator section. At least one vapor channel is defined within the inner surface to channel gaseous fluid from the evaporator section to the condenser section.

Abstract: Radiations detectors with angled walls and methods of fabrication are provided. One radiation detector module includes a plurality of sensor tiles configured to detect radiation. The plurality of sensor tiles have (i) top and bottom edges defining top and bottom surfaces of the plurality of sensor tiles, (ii) sidewall edges defining sides of the plurality of sensor tiles, and (iii) corners defined by the top and bottom edges and the sidewall edges. The radiation detector module also has at least one beveled surface having an oblique angle, wherein the beveled surface includes beveling of at least one of top or bottom edges, the side wall edges, or the corners.