국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Thermostructural Evaluation of Joggle Region on the Shuttle Orbiter''s Wing Leading Edge
저자	Walker, Sandra P.;; Warren, Jerry E.
Keyword	CARBON-CARBON COMPOSITES;; COATINGS;; FINITE ELEMENT METHOD;; LEADING EDGES;; MATHEMATICAL MODELS;; NONDESTRUCTIVE TESTS;; PLANE STRAIN;; REENTRY EFFECTS;; SENSITIVITY;; SPACE SHUTTLE ORBITERS;; SPACE SHUTTLES;; SPALLATION;; THERMODYNAMIC PROPERTIES;; THREE DIMENSIONAL MODELS;; WING PANELS
URL	http://hdl.handle.net/2060/20120008794
보고서번호	NASA/TM-2012-217571
발행년도	2012
출처	NTRS (NASA Technical Report Server)
ABSTRACT	An investigation was initiated to determine the cause of coating spallation occurring on the Shuttle Orbiter''s wing leading edge panels in the slip-side joggle region. The coating spallation events were observed, post flight, on differing panels on different missions. As part of the investigation, the high re-entry heating occurring on the joggles was considered here as a possible cause. Thus, a thermostructural evaluation was conducted to determine the detailed state-of-stress in the joggle region during re-entry and the feasibility of a laboratory test on a local joggle specimen to replicate this state-of-stress. A detailed three-dimensional finite element model of a panel slip-side joggle region was developed. Parametric and sensitivity studies revealed significant stresses occur in the joggle during peak heating. A critical interlaminar normal stress concentration was predicted in the substrate at the coating interface and was confined to the curved joggle region. Specifically, the high interlaminar normal stress is identified to be the cause for the occurrence of failure in the form of local subsurface material separation occurring in the slip-side joggle. The predicted critical stresses are coincident with material separations that had been observed with microscopy in joggle specimens obtained from flight panels.