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Simulating flight boundary conditions for orbiter payload modal surveyAn approach to simulate the characteristics of the payload/orbiter interfaces for the payload modal survey was developed. The flexure designed for this approach is required to provide adequate stiffness separation in the free and constrained interface degrees of freedom to closely resemble the flight boundary condition. Payloads will behave linearly and demonstrate similar modal effective mass distribution and load path as the flight if the flexure fixture is used for the payload modal survey. The potential non-linearities caused by the trunnion slippage during the conventional fixed base modal survey may be eliminated. Consequently, the effort to correlate the test and analysis models can be significantly reduced. An example is given to illustrate the selection and the sensitivity of the flexure stiffness. The advantages of using flexure fixtures for the modal survey and for the analytical model verification are also demonstrated.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Chung, Y. T.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Sernaker, M. L.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Peebles, J. H.
(McDonnell Douglas Aerospace, Space Station Div., Huntington Beach CA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 5 (A93-33876 1
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Space Transportation
Report/Patent Number
AIAA PAPER 93-1605
Accession Number
Funding Number(s)
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