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Damage Assessment Of Civil Aircraft Composite Structure And Its Airworthiness Compliance Verification Research

Posted on:2019-04-02Degree:MasterType:Thesis
Country:ChinaCandidate:Y S GaoFull Text:PDF
GTID:2382330596450252Subject:Transport Engineering
Abstract/Summary:PDF Full Text Request
Composite materials are more and more widely used in aviation structures due to their huge structural weight loss potential,higher specific strength,specific stiffness characteristics,and extensive material design.The development of a large airliner is gradual,the plane structure by the maturity of the aluminum alloy structure necessarily progress to the composite structure,in the face with the European and American countries composite aircraft structures under the present situation of the gap is bigger,need to master as soon as possible based on the manufacturing technology of composite material structure,detection method and efficient assembly process and authorized technology.In this paper,based on the national commercial aircraft manufacturing engineering technology research center of innovation fund project requirement,composite materials to civil aircraft struct ure damage evaluation method and its airworthiness compliance verification technology were studied.Firstly,this paper analyzes CCAR 25.305 and 307 to determine the airworthiness certification basis of composite structure.Based on AC107 B,the verification method of composite structure was determined.The static strength factors of aircraft composite structures were determined based on the ASTM document.At home and abroad,the existing research on composite bearing damage,based on the selection of the appropriate model to carry on the mechanical damage analysis and res idual strength as well as the damage law of composite laminated plate was analyzed and expounds the load damage and residual strength of the inner link.Secondly,the impact damage area of composite laminated plates under three different impact energy is obtained through impact test of the composite laminated plate and precast impact damage.The compression test of laminated plates was carried out using the INSTRON-8803 low-frequency testing machine.The load-displacement curve and residual compressive strength of composite laminated plates with three different impact energies were obtained.USES the structural mechanics of composite material structure damage failure analysis of laminated plates stress analysis model is established and a simulation analysis was made on failure analys is model,and then compared with the experimental results analysis,finally,the structural damage in composite laminated plate test and laminated plate model,on the basis of laminated plates with materials containing hole was pr edicted damage results.Analysis of tensile load and vertical surface load for laminated plates with materials containing a hole,and predict the residual strength and the displacement,to study its effect on the properties of laminated plates containing hole and change law of damage.Finally,put forward the large civil aircraft composite structure static strength test method and composite structural static strength test program,the aircraft horizontal fin box section of the static strength of full size for validation test.New material requirements and authentication were proposed,for the composite material structure airworthiness compliance verification,and domestic materials research provides a technical basis,which helps to expand the application of civil aircraft composite materials.
Keywords/Search Tags:Composite Structure, Damage, ANSYS, Static Strength, Airworthiness Verification
PDF Full Text Request
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