Erstellung und Erprobung dreidimensional verformter Rumpf-Panels. T. 1 Schlussbericht

This report documents the project status reached by DA and ERNO in the period between 1.7.1990 and 31.12.1992 and contains a summary of the work performed and results obtained. Besides the extension of the database for storage of the test results, a specification was prepared for the thermo-mechanical tests to be performed by the IMA Dresden. In addition, various thermal mathematical models were prepared with a view to different targets. Structure-mechanical problems, especially of the hypersonic demonstrator HYTEX, were investigated. Critical components and load cases were calculated with finite element models and stability examinations. Within the framework of the technology program for high-temperature areas of the fuselage structure, solution concepts as well as requirement catalogs for the fuselage panels of the Saenger and the hypersonic technology experimental aircraft were elaborated in cooperation with the HYTEX team. Plane and cylindrical 3D-fuselage panels measuring 500 x 1000 mm were manufactured from titanium alloys for an application temperature of 500 C/1 h. A description is given of the special test facility of the IMA for thermo-mechanical tests with HT panel structures and the methodics and results of four thermo-mechanical tests on different titanium alloy structures are presented. Thermal loading consisted of unilateral heating of the test specimens to 500 C in 1000 s while mechanical loading was effected by compressive (buckling) loads in longitudinal direction of the panels at room temperature and at 500 C. (orig.)Available from TIB Hannover: RR 8098(94-001,1)+a / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekSIGLEBundesministerium fuer Forschung und Technologie (BMFT), Bonn (Germany)DEGerman