Abstract: A method of joining a first work-piece to a second work-piece is provided. Each of the first work-piece and the second work-piece include a top surface, an opposed bottom surface, and a side surface connecting the top surface and the opposed bottom surface. In one aspect, the method includes positioning the side surface of the first work-piece adjacent to the side surface of the second work-piece, and advancing a friction stir additive manufacturing tool across the top surface of the first work-piece and the top surface of the second work-piece along a weld line between the first work-piece and the second work-piece. As the friction stir additive manufacturing tool advances along the weld line, a filler material is deposited along the weld line and into a plurality of through holes formed in either or both of the first work-piece and the second work-piece.

Abstract: The disclosure relates to a lung function detection method, system and apparatus, and to a computer device and a storage medium. The method comprises: acquiring chest and abdomen surface point cloud data of a subject under test within a preset time period by means of a biological detection sensor; analyzing the chest and abdomen surface point cloud data, and determining lung ventilation change information of the subject under test; and according to the lung ventilation change information, determining a lung function detection result of the subject under test. The biological detection sensor is arranged within a preset range around the subject under test but does not come in contact with the subject under test.

Abstract: Systems and methods for securing an upright rocket. The rocket may be on a moveable platform, such as a landing area of a ship. The rocket may land on the deck, and the system may include cables that surround the landing area. The cables may be tightened about the rocket after the rocket has landed in an upright position. The system may include poles that telescope upward, such that the cables may tighten about the upright rocket at various heights along the body of the rocket.

Abstract: A friction stir additive manufacturing device configured to join a first work-piece and a second work-piece is provided. In one aspect, the device includes a rotating spindle configured to deposit a filler material over a weld line as the device is advanced along an interface between the first work-piece and the second work-piece. The device also includes a deposition head configured to receive at least a portion of the spindle, the deposition head configured to remain stationary relative to the rotating spindle. The deposition head includes a first semi-cylindrical portion having an inner radius and an outer radius relative to a first axis, and a second semi-cylindrical portion having an inner radius and an outer radius relative to a second axis that is perpendicular to the first axis. The second semi-cylindrical portion can include a chamfered inner surface configured to define a weld profile.

Abstract: A method of additive manufacturing a structure having integrated passages is provided. In one aspect, the method includes forming first and second parts, each part having a near net shape. The first and second parts are formed by moving a friction stir tool configured to deposit a filler material. An inner surface of each part can be machined to form a generally smooth surface. The first and the second parts are joined to form a structure. The structure is machined to form a generally smooth outer surface. The method includes machining a plurality of grooves extending into the generally smooth outer surface of the structure. A tube is placed into each of the plurality of grooves and a layer of material is deposited to secure the tubes within the plurality of grooves. The method can include machining the outer surface to a predetermined shape.

Abstract: A method of additive manufacturing a part having integrated passages is provided. In one aspect, the method includes forming a part having a near net shape by moving a friction stir tool to deposit a filler material in a predetermined formation. The tool can include a rotating spindle having a channel configured to hold the filler material. The method can include machining the near net shape part to form a plurality of grooves extending into a surface of the part, the plurality of grooves sized and shaped to each receive a tube. The method can include placing a tube into each of the plurality of grooves and moving the tool across the surface of the part and depositing additional material configured to secure the tubes within the plurality of grooves. The method can include machining the additional material deposited over the tubes to a predetermined shape.

Abstract: Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.

Abstract: Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.

Abstract: Disclosed is a method for designing a gradient minimal surface structure based on a surface density distribution.

Abstract: A method of joining a first work-piece to a second work-piece is provided. Each of the first work-piece and the second work-piece include a top surface, an opposed bottom surface, and a side surface connecting the top surface and the opposed bottom surface. In one aspect, the method includes positioning the side surface of the first work-piece adjacent to the side surface of the second work-piece, and advancing a friction stir additive manufacturing tool across the top surface of the first work-piece and the top surface of the second work-piece along a weld line between the first work-piece and the second work-piece. As the friction stir additive manufacturing tool advances along the weld line, a filler material is deposited along the weld line and into a plurality of through holes formed in either or both of the first work-piece and the second work-piece.

Abstract: Disclosed is a method for designing a gradient minimal surface structure based on a surface density distribution.

Abstract: Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.

Abstract: A friction stir additive manufacturing device configured to join a first work-piece and a second work-piece is provided. In one aspect, the device includes a rotating spindle configured to deposit a filler material over a weld line as the device is advanced along an interface between the first work-piece and the second work-piece. The device also includes a deposition head configured to receive at least a portion of the spindle, the deposition head configured to remain stationary relative to the rotating spindle. The deposition head includes a first semi-cylindrical portion having an inner radius and an outer radius relative to a first axis, and a second semi-cylindrical portion having an inner radius and an outer radius relative to a second axis that is perpendicular to the first axis. The second semi-cylindrical portion can include a chamfered inner surface configured to define a weld profile.

Abstract: Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.

Abstract: Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.

Abstract: A method of joining a first work-piece to a second work-piece is provided. Each of the first work-piece and the second work-piece include a top surface, an opposed bottom surface, and a side surface connecting the top surface and the opposed bottom surface. In one aspect, the method includes positioning the side surface of the first work-piece adjacent to the side surface of the second work-piece, and advancing a friction stir additive manufacturing tool across the top surface of the first work-piece and the top surface of the second work-piece along a weld line between the first work-piece and the second work-piece. As the friction stir additive manufacturing tool advances along the weld line, a filler material is deposited along the weld line and into a plurality of through holes formed in either or both of the first work-piece and the second work-piece.

Abstract: Systems and methods for securing an upright rocket. The rocket may be on a moveable platform, such as a landing area of a ship. The rocket may land on the deck, and the system may include cables that surround the landing area. The cables may be tightened about the rocket after the rocket has landed in an upright position. The system may include poles that telescope upward, such that the cables may tighten about the upright rocket at various heights along the body of the rocket.

Abstract: A forming-machine equipment testing method includes: determining, by a scheduling host computer, an equipment transport task for equipment after a task start time of the equipment is reached, determining, by the scheduling host computer, whether the equipment meets the equipment transport task, and in response to the equipment meeting the equipment transport task, instructing, by scheduling host computer, an intelligent transport device to transport the equipment to a corresponding target location, so as to control the equipment to execute an equipment test task at the target location.

Abstract: The present application provides a flow test tool, a negative pressure formation apparatus, and a battery manufacturing device. The flow test tool includes a base and a flow test module mounted on the base, the flow test module is provided with a plurality of test interfaces, and the test interface is connected to a fluid channel of a mechanism to be tested one by one.

Abstract: A gas infusion tank for a beverage machine includes a tank body defining a holding space for accommodating beverages. A mixing element includes a mixing chamber, an ascending pipe, and a descending pipe. A top of the ascending pipe is fluidly connected to the mixing chamber and a bottom of the ascending pipe has a liquid inlet. The liquid inlet is fluidly connected to the holding space. A top of the descending pipe is fluidly connected to the mixing chamber and a bottom of the descending pipe includes a liquid outlet in fluid communication with the nozzle. A gas intake hole connects the holding space with the mixing chamber.