Compound Materials R Angle Spot Flaw Examination Technology And Supersonic C Scanning Examination Processing Technology Research

Composite materials for its good strength, stiffness, fatigue performance of materials canbe designed such advantages, more and more widely applied to aircraft structures. Compositematerials because of the diversity of the components, the complexity of the structure andprocess in the manufacturing process instability, whether it is in the structural design andmanufacture stage, or in materials technology research stage and service-use phase, easy toproduce defects or damage, in addition, composite materials in the service process will stressand environmental effects of lead inside the structure by varying degrees of damage.Therefore, for a composite test to become a very important task.More non-destructive testing of composite materials technology, but with thedevelopment of science and technology, since no one can be effectively used to structurecomplex, changeable components, defects in a wide variety of composite materials testingtechnology. Believed generally that, compound materials interior existence debonding, thecavity, flaws and so on micro crack, acoustics examination is one effective method. Becausethe supersonic examination technology is examined the mathematical relation which thephysical information and the compound materials inherent drawback information existencemay express precisely, therefore the majority of compound materials component may use thesupersonic method to carry on the flaw evaluation. The massive literature also indicated that,the supersonic examination technology supersonic C scanning examination technology is inparticular the present domestic and foreign compound materials lossless examination is mosteffective, applies the most widespread lossless examination technology, it can examine in thecompound materials reliably the lamination loose, the hole and so on the majority ofhazardous flaw.In this paper, the carbon fiber/resin composite (25%carbon fiber content) and plexiglassas was seized material produced in the detection of ultrasound c scanning process parameterstest sample, the thickness of the workpiece was seized on the receiving ultrasonic energy andThe probe sensitivity, to carry out the parameter optimization, testing, optimizing columnflow rate and probe scanning to obtain the optimum parameters of the composite ultrasonic cScan.This paper addresses the growing aerospace aircraft frequently used R corner classcomposite components, research R corner of ultrasound detection technology, the flooding in the sound beam probe penetrate Law, flooding and the inside is the law, and the waterflooding into the body outside the law, and the outer tip-contact method and the ultrasoundprobe array test pilot study to test the various methods of the feasibility and scope.Non-surface large flat class structure, in order to improve the detection efficiency,increase accuracy of detection in this research process, the trial of a mult-21ultrasonic Cscanning equipment, including hardware and software design of two parts, hardware,including mechanical scanning devices, signal excitation and conditioning device, thesoftware system including automatic control, signal acquisition and image processing, andreport output functions, record keeping of test results, test basis for the nondestructive testingof composite materials.