Structural Design And Vibration Reduction Of An Aircraft Electrical Control Equipment

The electrical control equipment is a key component of aircraft control system. In theprocess of stage separation, head separation or warhead re-entry, it will work under the dynamicenvironment of strong vibration, shock and noise, and the structure must keep integrity in orderto work normally.The electrical control equipment is studied in this paper. Firstly, the structuralcharacteristics of the electrical control equipment and design methods are studied, then thestructure of the cabin and electrical control equipment are designed, and three designed plans ofgyro bearings are introduced.Based on Femap/Nastran software, finite element modeling and analysis of the electriccontrol equipment are executed. Firstly, finite element model is established, and then materialand load boundary conditions are respectively defined. Secondly, static analysis, mode analysis,frequency analysis and random analysis are respectively executed, and mechanicalcharacteristics of the electrical control equipment are obtained. Thirdly, vibration control deviceis designed based on vibration and damping theory, and random vibration tests are performed toselect the optimized plan.Finally, random vibration test for the whole product and shock test are performed to verifythe dynamic characteristics and impact resistance of the electrical control equipment structure.The test results show that the product can meet the design requirements.The equipment designed in this paper has been used to in a vehicle electrical control system,which has been proved to be successful in a flight test. Also the work in this paper is helpful anduseful in the design progress of aircraft electrical control equipment.