Design And Verification Of Static Strength Test Plan For Hinge Arm Of Civil Aircraft Cabin Door Under Multiple Working Conditions

The combination of additive manufacturing and structural topology optimization design is the future development trend of weight reduction in civil aircraft structural parts.However,structural parts using new processes and new methods must pass airworthiness certification before being applied to civil aircraft structures.There are no relevant standards and specifications for the test verification of parts,and the test plan needs to be designed separately.Therefore,this article takes the civil aircraft cabin door hinge arm of structural topology optimization using additive manufacturing as the research object,and designs its static strength test plan according to the airworthiness clause and conducts experimental verification.It has engineering value and practical significance for the application of additive manufacturing structural topology optimization hinge arm to civil aircraft structure.Firstly,according to the design criteria for the static strength test scheme of the hinged arm in actual use conditions.The static strength analysis of the hinged arm under each operating condition was carried out using the method of MC2 analysis and calculation using Ansys Workbench,which verified that its strength and rigidity met the airworthiness requirements.It further analyzes the factors affecting the loading accuracy,compares the loading method and optimizes the component force loading method,thus determines the test loading plan,and proposes the tooling design and assembly indicators.Secondly,the test device was designed according to the tooling design index and the determined loading plan,combined with the actual working conditions of the hinge arm,the need to independently design the loading device and support device was analyzed and corresponding design requirements were proposed.The loading device was designed as a spiral transmission loading,and the support device was designed as a test bench.After the design is completed,the finite element static strength check is carried out to verify that the strength and stiffness of the test device meet the requirements of use.Finally,the test program was designed to standardize the test process.Before the test,the maximum principal strain was determined as the comparison parameter between the test and the finite element results and the three strain rose measurement positions.The standard parts were used to calibrate the parameters of the strain gauge.The hinged arm was installed and the assembly index requirements were met.After completing the repeated static strength test by many people,the test data was processed through abnormal data inspection,compatibility test,goodness of fit test and other methods,and the average test strain was compared with the finite element strain value,and the deviation between the two was less than 10 percent.The test results show that the static strength test plan for hinge arm of civil aircraft cabin door under multiple working conditions in this paper is feasible.The static strength and rigidity of the hinge arm of the cabin door meet the working requirements under multiple working conditions.The experimentally verified finite element model can be used for further analysis of hinge arms and the design of static strength test schemes for similar structures.This study provides a basis for reliability data to promote the MC2 analysis and calculation to gradually replace the MC4 test in the process of civil aircraft airworthiness compliance verification.