COMPOSITE AIRFRAME TECHNOLOGY DEVELOPMENT FOR USE IN UNMANNED AERIAL SYSTEMS. PART I

Authors
  1. Francoeur, J.R.
  2. Hansen, J.S.
Corporate Authors
Defence Research Establishment Suffield, Ralston ALTA (CAN);Toronto Univ, Toronto ONT (CAN) Inst for Aerospace Studies
Abstract
A Finite Element Model based on Mindlin-Reissner plate theory, originally developed by Dr. G. R. Heppler, was extended to model a composite hybrid sandwich plate structure subject to a static load. The model was subsequently validated by a full scale deflection experiment. The first portion of this work discusses a sandwich material characterization test program which was conducted to determine the strength and failure behaviour of the sandwich structure. The second portion discusses a full scale deflection experiment which was conducted on the TATS-102 wing in order to validate the finite element model and design load specification. The wing was loaded to the design load specification without failure. The third portion discusses the analytical formulation of the model and the software documentation. The final portion is a discussion on the comparison between the experimental and analytical results. TRUNCATED
Keywords
Aerial targets;Airframes
Report Number
DRES-CR-39/86-PT-1 — Contract Report (Final)
Date of publication
15 Oct 1986
Number of Pages
130
DSTKIM No
87-00228
CANDIS No
49080
Format(s):
Hardcopy;Originator's fiche received by DSIS

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