Molded surface detection method for non-rigid irregular composite material component

Abstract

The invention discloses a molded surface detection method for a non-rigid irregular composite material component, and belongs to the detection field for part processing and manufacturing. The molded surface detection method for a non-rigid irregular composite material component can solve the problem that detection of a molded surface under the free state does not conform to the final usage state, and can guarantee that the component can exclude the deformation error of the component during the detection process. The molded surface detection method comprises the steps: 1 designing a set of detection molds with three plane references according to a mold processed by the component; 2 fitting the component with the detection molds through the edge, and covering the surface of the molds with a standard thickness film to closely fit the component with the detection molds through a vacuum pumping mode; 3 utilizing contact measurement means to acquire the data points on the surface of the component; and 4 by means of the three reference planes, establishing the reference, and obtaining the result after being fitting the reference with a theoretical model coordinate system. The molded surface detection method for a non-rigid irregular composite material component guarantees that the surface of the detected component is provided with uniformly distributed loading force, and perfectly solves the problem that uneven loading force causes tilting of an unstrained part.

Description

technical field [0001] The invention belongs to the field of part processing and manufacturing detection, and relates to the profile detection of composite material components. Background technique [0002] Non-rigid special-shaped composite material components are mainly used for hypersonic aircraft to isolate the high temperature generated by the high-speed friction between the outer surface of the aircraft and the air from the metal material body of the aircraft during high-speed flight, so as to ensure that the internal temperature of the aircraft is within an appropriate range. surface and so on. [0003] According to the use of this material, it can be judged that its own profile must be consistent with the profile of the aircraft surface, and in recent years, the aircraft profile tends to be profiled and closely fits the aircraft surface, so this material The components must have two characteristics: special-shaped and non-rigid. [0004] The final forming method of...

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Problems solved by technology

[0004] The final forming method of such components is generally based on the final shape of the mold, and then the final forming process is performed on the basis of the mold. After the processing is completed, it is removed from the mold. At this time, the component has no inspection. benchmark, and there is a deformation of 1-2 mm in the profile itself, the detection of the profile in a free state is obviously not in line with the final use state, and the result of the profile will inevitably be affected by its own deformation, resulting in out-of-tolerance

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