A method of forming an assembly in which a metal extension element is connected with a metal stub element, by an intermediate element. The intermediate element extends between first and second ends. The intermediate element is positioned to locate its first end spaced apart from the stub element. An inner end of the extension element is spaced apart from the second end of the intermediate element. Heating elements are located between the elements, to heat the proximal portions of the elements to a hot working temperature, at which the heated portions are subject to plastic deformation. The heating elements are removed, and while the intermediate element is rotating, the first end is urged against the stub element to bond the intermediate element with the stub element. While the extension element is rotating, the inner end is urged against the second end to bond the extension element and the intermediate element.

A method for manufacturing a clad steel pipe is provided, wherein the clad steel pipe is manufactured by using a clad steel plate as a raw material. The clad steel plate comprises a base layer (1) and a clad layer (2) roll-bonded with the base layer (1). The method for manufacturing a clad steel pipe comprises the steps of forming, welding, and deburring; both sides of the clad steel plate are bent towards the base layer (1) side of the clad steel plate, then the forming step is carried out, and after the forming step, the opening faces of the resultant pipe blank are all in a form of the clad layer (2). According to the method for manufacturing a clad steel pipe, a clad steel pipe is manufactured by using a clad steel plate as a raw material. Thus, continuance and high efficiency of a high-frequency longitudinal welding pipe unit is fully utilized, subsequent non-continuous processes are not necessary, and the corrosion resistance at the weld of the clad steel pipe is ensured.

An electromagnetic pulse additive device for a connection ring of a heavy-lift carrier rocket is provided. The device includes brackets, a gear disk rotatably matched with the annular ground rail through a plurality of rolls arranged in a circumferential direction of the gear disk, a first drive motor, an annular ground rail, and a guide rail in a semicircular shape arranged at top ends of the brackets. An output shaft of a first drive motor is fixedly provided with a first drive gear engaged with the gear disk. The guide rail is slidably provided with three lifting modules which respectively drive a bending module, an electromagnetic head arranged electromagnetic coil electrically connected with a capacitor and a discharge circuit, and a rotational friction and extrusion module including a second drive motor and a friction bar fixedly connected to an output shaft of the second drive motor to rise and fall.

An electromagnetic pulse additive device for a connection ring of a heavy-lift carrier rocket is provided. The device includes brackets, a gear disk rotatably matched with the annular ground rail through a plurality of rolls arranged in a circumferential direction of the gear disk, a first drive motor, an annular ground rail, and a guide rail in a semicircular shape arranged at top ends of the brackets. An output shaft of a first drive motor is fixedly provided with a first drive gear engaged with the gear disk. The guide rail is slidably provided with three lifting modules which respectively drive a bending module, an electromagnetic head arranged electromagnetic coil electrically connected with a capacitor and a discharge circuit, and a rotational friction and extrusion module including a second drive motor and a friction bar fixedly connected to an output shaft of the second drive motor to rise and fall.

A method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.

A method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.

An electromagnetic pulse additive device for a connection ring of a heavy-lift carrier rocket is provided. The device includes brackets, a gear disk rotatably matched with the annular ground rail through a plurality of rolls arranged in a circumferential direction of the gear disk, a first drive motor, an annular ground rail, and a guide rail in a semicircular shape arranged at top ends of the brackets. An output shaft of a first drive motor is fixedly provided with a first drive gear engaged with the gear disk. The guide rail is slidably provided with three lifting modules which respectively drive a bending module, an electromagnetic head arranged electromagnetic coil electrically connected with a capacitor and a discharge circuit, and a rotational friction and extrusion module including a second drive motor and a friction bar fixedly connected to an output shaft of the second drive motor to rise and fall.

An electromagnetic pulse additive device for a connection ring of a heavy-lift carrier rocket is provided. The device includes brackets, a gear disk rotatably matched with the annular ground rail through a plurality of rolls arranged in a circumferential direction of the gear disk, a first drive motor, an annular ground rail, and a guide rail in a semicircular shape arranged at top ends of the brackets. An output shaft of a first drive motor is fixedly provided with a first drive gear engaged with the gear disk. The guide rail is slidably provided with three lifting modules which respectively drive a bending module, an electromagnetic head arranged electromagnetic coil electrically connected with a capacitor and a discharge circuit, and a rotational friction and extrusion module including a second drive motor and a friction bar fixedly connected to an output shaft of the second drive motor to rise and fall.

Provided is a rotating body, including: a shaft; and a compressor impeller including: a main body having an insertion hole, which extends from one end to another end side and is configured to receive the shaft inserted therethrough; a boss portion formed at one end side of the main body; and a joint portion, which is formed on an inner peripheral surface of the insertion hole at the boss portion and is welded to the shaft.

Provided is a rotating body, including: a shaft; and a compressor impeller including: a main body having an insertion hole, which extends from one end to another end side and is configured to receive the shaft inserted therethrough; a boss portion formed at one end side of the main body; and a joint portion, which is formed on an inner peripheral surface of the insertion hole at the boss portion and is welded to the shaft.