Study and characterization of ceramic shell structures for high temperature space applications
Marta Albano ; Andrea Delfini ; Antonio Vricella ; ...Samantha Ianelli ; ...Alessandro Gabrielli ; et al.
Sep - 2017

Event Title : 68th International Astronautical Congress 2017
Published in: IAC Paper
Publisher: IAC
type: Conference Proceedings

68th International Astronautical Congress 2017MATERIALS AND STRUCTURES SYMPOSIUM (C2)Specialised Technologies, Including Nanotechnology (8)Author: Dr. Marta AlbanoAgenzia Spaziale Italiana (ASI), Italy, marta.albano@est.asi.itDr. Andrea DelfiniSapienza Universit`a di Roma, Italy, andrea.delfini@uniroma1.itDr. Antonio Vricella”Sapienza” University of Rome, Italy, antonio.vricella@uniroma1.itMs. Samantha IanelliItalian Space Agency (ASI), Italy, samantha.ianelli@asi.itDr. Alessandro GabrielliItalian Space Agency (ASI), Italy, alessandro.gabrielli@asi.itProf. Mario MarchettiUniversity of Rome ”La Sapienza”, Italy, mario.marchetti@uniroma1.itSTUDY AND CHARACTERIZATION OF CERAMIC SHELL STRUCTURES FOR HIGHTEMPERATURE SPACE APPLICATIONSAbstractThe use of laminated composite shells in many engineering applications has been expanding rapidlyin the past five decades due to their higher strength and stiffness to weight ratios when compared tomost metallic materials. Composite shells now constitute a large percentage of aerospace or submarinestructures. When shell structure is applied to space, the most challenging structures are the aeroshell usedfor the wing leading edge and nose of vehicles. The extreme temperatures on these components broughtthe technology on development of ceramic materials able to withstand the harsh re-entry environmentconditions. The aim of this paper is to study a shell structure for space applications such as leadingedges of a re-entry vehicle. The structure has to be reusable, lightweight and thin. A sandwich shellstructure will be designed, manufactured and tested. The components used for the design are the skinmade of carbon composite and the core made of carbon foam. The use of Carbon/Carbon compositesfor the design of shells allows structures to withstand temperatures over 1300C. The key factor for usingthis kind of material in re-entry applications is the high stability at high temperature, preserving itsmechanical properties. Carbon based foams main features are thermal stability (low CTE), lightweight,high insulating capacities. This core material shall withstand with high thermal loads and the mainpurpose is to drastically reduce of hundreds of degree the temperatures of the upper surface (typicallyabout 1000C) in order to protect the inner volume of the spacecraft. In this frame, the selection of thefoam for this specific application is utmost important. One of most critical aspects of sandwich structuresis the behaviour of adhesive between the different layers, which depends on the surface preparation andprocess optimization: the present intend to provide a study of a process for a good adhesion and excellentthermo-mechanical properties. A 3-D shell prototype manufactured via Chemical Vapour Infiltrationwill undergo to a stabilization process. The manufacturing process will be controlled via testing controlsamples which follows the prototype during its production cycle. The samples will be tested in orderto analyze the morphological and thermo-mechanical characteristics. Scanning Electron Microscopy andEnergy Dispersive X-ray analysis and space environment tests, such as atomic oxygen and outgassing,will be performed. These characteristics will be implemented in a numerical analysis in order to studythe thermos-mechanical behavior of the structure

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Notes : Paper code IAC-17,C2,8,4,x37921