Patent classifications
B23B2215/04
MACHINING METHOD AND MACHINING SYSTEM
A machining system having plural machining devices installed at plural points in a robot arm. the machining system carrying out machining to a processed object made of metal be by using these machining devices, the machining system further having a control device that controls drive of the machining devices so as to offset processing reaction forces by at least one of a thrust force and a torque to be obtained when the machining devices carry out machining to the processed object simultaneously between the machining devices.
Supporting a contoured sheet of material during machining operations
A machining support configured to reduce spring back of a sheet following a machining operation on the sheet is presented. The machining support comprises a porous material with a plurality of surfaces including a support surface having a contour configured to contact and support the sheet; sealing material covering each of the plurality of surfaces except the support surface; and a vacuum port configured to provide a vacuum to the porous material.
Assembly apparatus
An assembly apparatus includes a retainer, a position measurement device, and a machining device. The retainer is configured to hold an assembly. The position measurement device is configured to measure a difference between an intended machining position and an actual machining position of a first coupling hole in a first assembly component. The first coupling hole is capable of being coupled to the assembly. The machining device is configured to form a second coupling hole capable of communicating with the first coupling hole in the assembly based on a reference position set on the assembly and the difference.
Surface area of fixtures
A method and apparatus. The apparatus comprises a first portion of a tool and a second portion of the tool. The first portion of the tool has a first surface. The first surface has a shape that is complementary to a first portion of a part. The second portion has at least one of a second surface configured to be recessed from a second portion of the part or a hollow portion.
System for hole making for aircraft skin by normal positioning and locking
The invention discloses a system for hole making for an aircraft skin by normal positioning and locking. The hole-making system includes a posture adjustment part, a normal positioning and locking part and a hole-making execution part. This system solves the problems that the device in the prior art has high complexity and cumbersome positioning and does not adapt to complex curved surfaces, thereby failing to satisfy the needs of efficient hole making in different space states. In the present invention, the expansion of an outer expansion sleeve in a bottom sleeve locks a normal direction for hole making, thereby ensuring the positioning accuracy of the normal direction. An axial position is locked by the mutual cooperation of an axial positioning groove of the bottom sleeve and an axial positioning rib of the outer expansion sleeve. A hole-making auxiliary cylinder contracts to counteract part of an axial force for hole making.
METHOD AND APPARATUS FOR MACHINING A WORKPIECE
A method for machining a workpiece is provided, wherein drilling of the workpiece and subsequent countersinking of the bore, obtained by the drilling, in the workpiece are performed by means of a drilling/countersinking tool in a machining process, wherein the drilling/countersinking tool in the machining process while being axially rotated is subjected to an axial feed movement relative to the workpiece that reaches a counterbore terminal position, and wherein the axial feed movement is superimposed by an axial vibration, wherein, when reaching a predefined frequency lowering position of the axial feed movement by the drilling/countersinking tool, the frequency of the axial vibration is lowered to a final machining frequency, and the machining process is continued at the final machining frequency as the maximum frequency of the axial vibration until the counterbore terminal position is reached.
DRILLING TOOL
Disclosed is a drilling tool intended to cooperate with a tooling including at least one guide orifice, including: a hollow nose part, through which a drilling member is intended to pass; and a gripping clamp, slidingly mounted on the hollow nose part, the sliding of the gripping clamp rearward along the hollow nose part leading to its radial expansion towards the outside. The distal end of the gripping clamp includes a bead protruding radially towards the outside, configured to ensure the stopping in translation of the drilling tool with respect to the tooling, by bearing against a wall of the tooling surrounding the guide orifice, when the gripping clamp is expanded radially towards the outside.
System and method for forming elongated perforations in an inner barrel section of an engine
Certain embodiments of the present disclosure provide an acoustic inlet barrel of an engine. The acoustic inlet barrel may include an inner barrel configured to provide a boundary for directing airflow through the engine. The inner barrel may include an inner face sheet separated from an outer face sheet by an acoustic core. The inner barrel may include a plurality of elongated, non-circular perforations formed through the inner face sheet.
TOOLS AND METHOD FOR FORMATION OF AN APERTURE IN A PANEL
A method includes drilling a first aperture in a panel that extends between a panel first surface and a panel second surface. The first aperture projects into the panel along a first centerline from the panel first surface. The first centerline is angularly offset from the panel first surface by a first angle. A first tool is arranged with the panel. The first tool includes a support structure, a locator and a drill guide. The locator is mounted to the support structure and projects into the first aperture. The drill guide is mounted to the support structure and is arranged adjacent the panel second surface. A second aperture is drilled in the panel using the drill guide. The second aperture projects into the panel along a second centerline from the panel second surface to the first aperture. The second centerline is coaxial with the first centerline.
DRILLING GRID, DRILL RIG AND METHOD FOR SUPERVISING AT LEAST ONE OPERATION FOR DRILLING AN AIRCRAFT STRUCTURAL PART
Said drilling grid comprises a main body designed to be attached to an aircraft structural part and having through-holes for positioning a machine for drilling the aircraft structural part. It further comprises a wireless communication device configured to communicate with a supervision system and a data processing unit designed to send to the supervision system, via the wireless communication device, information relating to the drilling grid and/or the drilling machine positioned in one of the positioning holes.